THERMAL COMBUSTION ENGINE WHICH CONVERTS THERMAL ENERGY INTO MECHANICAL ENERGY AND USE THEREOF

MOTEUR THERMIQUE DESTINE A CONVERTIR DE L'ENERGIE THERMIQUE EN ENERGIE MECANIQUE ET UTILISATION DUDIT MOTEUR

English Abstract

The invention relates to a thermal combustion engine which converts thermal
energy into mechanical energy, comprising at least one vapour producing device
which at least partially vaporises a first liquid working medium by means of
thermal energy supplied to the combustion engine, at least one rotor (11)
which can be driven by means of a vaporised first working medium in order to
produce mechanical energy and rotated with respect to at least one stator (3)
around a first rotational axis, and at least one condensation device for
condensation of the vaporised first working medium after the rotor (11) has
been driven. The rotor (11) surrounds the stator in an essentially complete
manner. The invention also relates to the use of the inventive thermal
combustion engine.

French Abstract

Moteur thermique destiné à convertir de l'énergie thermique en énergie mécanique, qui comporte au moins un dispositif de production de vapeur destiné à vaporiser au moins en partie un premier milieu de travail liquide à l'aide d'énergie thermique apportée au moteur thermique, au moins un rotor pouvant être entraîné à l'aide du premier milieu de travail vaporisé, pour la production d'énergie mécanique, et rotatif par rapport à au moins un stator, autour d'un premier axe de rotation, et au moins un dispositif de condensation destiné à condenser le premier milieu de travail vaporisé après l'entraînement du rotor, le rotor entourant le stator de manière essentiellement complète. La présente invention concerne également l'utilisation d'un moteur thermique de ce type.

Claims

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1. A thermal combustion engine (1, 1', 1", 51, 51', 51") for converting
thermal
energy into mechanical energy, comprising at least one vapor generation device
(11a, 11a', 11a", 13, 13', 61a, 61a', 63, 63') for at least partially
vaporizing a first
liquid working medium (21, 21', 73, 73') using thermal energy supplied to the
thermal combustion engine (1, 1', 1", 51, 51', 51"), at least one rotor (11,
11',
11", 61, 61', 61"), which is drivable using the vaporized first working medium
(21, 21', 73, 73') to generate mechanical energy and is rotatable in relation
to at
least one stator (3, 3', 3", 53, 53', 53") around at least one axis of
rotation, and at
least one condensation device (11c, 11c', 11c", 15, 15', 61c, 61c', 65, 65',
65")
for condensing the vaporized first working medium (21, 21', 73, 73') after
driving
the rotor (11, 11', 11", 61, 61', 61"), the rotor (11, 11', 11", 61, 61', 61")
essentially completely surrounding the stator (3, 3', 3", 53, 53', 53") and
the rotor
(11, 11', 11", 61, 61', 61") essentially completely enclosing the vapor
generation
device (11a, 11a', 11a", 13, 13', 61a, 61a', 63, 63') and the condensation
device
(11c, 11c', 11c", 15, 15', 61c, 61c', 65, 65', 65").
2. A thermal combustion engine (1, 1', 1", 51, 51', 51", 101, 101', 101") for
converting thermal energy into mechanical energy, comprising at least one
vapor
generation device (11a, 11a', 11a", 13, 13', 61a, 61a', 63, 63', 115, 115',
115")
for at least partially vaporizing a first liquid working medium (21, 21', 73,
73',
137) using thermal energy supplied to the thermal combustion engine (1, 1',
1",
51, 51', 51", 101, 101', 101"), at least one tutor (11, 11', 11", 61, 61',
61", 117,
117', 117"), which is drivable using the vaporized first working medium (21,
21',
73, 73', 137) to generate mechanical energy and is rotatable in relation to at
least
one stator (3, 3', 3", 53, 53', 53", 103, 103', 103' around at least one axis
of
rotation, and at least one condensation device (11c, 11c', 11c", 15, 15', 61c,
61c',
65, 65', 65", 107, 107', 107") for condensing the vaporized first working
medium
(21, 21', 73, 73', 137) after driving the rotor (11, 11', 11", 61, 61', 61",
117, 117',

31
117"), the rotor (11, 11', 11", 61, 61', 61", 117, 117', 117") at least
partially
surrounding the stator (3, 3', 3", 53, 53', 53", 103, 103', 103").
3. The thermal combustion engine according to Claim 2,
characterized in that the rotor (11, 11', 11", 61, 61', 61", 117) essentially
completely surrounds the vapor generation device (11a, 11a', 11a", 13, 13',
61a,
61a', 63, 63', 115) and/or the condensation device (11c, 11c', 11c", 15, 15',
61c,
61c', 65, 65', 65").
4. The thermal combustion engine according to Claim 2 or 3,
characterized in that the stator (103, 103" essentially completely surrounds
the
vapor generation device (115) and/or the condensation device (107, 107').
5. The thermal combustion engine according to Claim 2,
characterized in that the vapor generation device (115") and/or the
condensation
device (107") is/are implemented in at least two parts and the rotor (117")
surrounds a first part of the condensation device (107a") and/or a first part
of the
vapor generation device (115a") and the stator (103") surrounds the other part
of
the vapor generation device (115b") and/or the condensation device (107b").
6. The thermal combustion engine according to one of Claims 1 through 5,
characterized by at least one first chamber (13, 13', 63, 63', 129, 129',
129")
forming the vapor generation device,
at least one second chamber (15, 15', 65, 65', 65", 131, 131', 131") forming
the
condensation device, and
at least one turbine chamber (25),
the first chamber (13, 13', 63, 63', 129, 129', 129") and the second chamber
(15,
15', 65, 65', 65", 131, 131', 131"), the first chamber (13, 13') and the
turbine
chamber (25, 25'), and/or the second chamber and the turbine chamber being at
least partially separated from one another using a thermally insulating wall
(17,
17', 17", 23, 24', 69, 69', 85, 85', 85", 121) in particular.

32
7. The thermal combustion engine according to Claim 6,
characterized by at least one first connection device, which connects the
first
chamber (13, 13', 63, 63') and the turbine chamber (25, 25') for passage of
the
vaporized first working medium (21, 21', 73, 73'), preferably comprising at
least
one first nozzle (27, 27', 27", 77, 77', 77", 139), the geometry and/or the
orientation of the nozzle opening preferably being adjustable, at least one
first
pipe (75, 75', 75") and/or at least one first opening, particularly
implemented in
the thermally insulating wall.
8. The thermal combustion engine according to Claim 6 or 7,
characterized by at least one second connection device, which connects the
turbine chamber and the second chamber for passage of the vaporized first
working medium, preferably comprising at least one second nozzle, the geometry
and/or the orientation of the nozzle opening preferably being adjustable, at
least
one second pipe, and/or at least one sewed opening, particularly implemented
in
the thermally insulating wall.
9. The thermal combustion engine according to Claim 7 or 8,
characterized by at least one first flow control and/or regulation device,
which is
operationally linked to the first connection device, and/or at least one
second flow
control and/or regulation device, which is operationally linked to the second
connection device, preferably in the form of a first and/or second valve.
10. The thermal combustion engine according to one of Claims 6 through 9,
characterized by at least one third connection device, which connects the
first
chamber (13, 13') and the turbine chamber (25, 25') for passage of the liquid
first
working medium (21, 21'), particularly in the form of a third opening (19;
20'),
preferably implemented in the thermally insulating wall (17, 17').
11. The thermal combustion engine according to one of Claims 6 through 10,

33
characterized by at least one fourth connection device, which connects the
turbine
chamber and the second chamber for passage of the liquid first working medium,
preferably in the form of at least one fourth opening, which is particularly
implemented in the thermally insulating wall.
12. The thermal combustion engine according to Claim 10 or 11,
characterized in that the liquid first working medium (21, 21', 73, 73')
prevents
the vaporized first working medium (21, 21', 73, 73') from exiting the first
chamber (13, 13', 63, 63', 129, 129', 129") through the third and/or fourth
connection device during a rotation of the rotor (11, 11', 11", 61, 61', 61",
117,
117', 117"), particularly blocks the third and/or fourth opening (19, 20'),
particularly because of the centrifugal force acting on the working medium
(21,
21', 73, 73', 137).
13. The thermal combustion engine according to one of Claims 10 through 12,
characterized by at least one third flow control and/or regulation device,
which is
operationally linked to the third connection device, and/or at least one
fourth flow
control and/or regulation device, which is operationally linked to the fourth
connection device, preferably in the form of a third and/or fourth valve,
particularly a check valve.
14. The thermal combustion engine according to one of Claims 6 through 13,
characterized in that the second chamber (15, 15') and the turbine chamber
(25,
25') are molded in one piece.
15. The thermal combustion engine according to one of Claims 6 through 14,
characterized by at least one flow guiding body (14', 16') implemented in the
first
chamber (13'), the second chamber (15'), and/or the turbine chamber (25').
16. The thermal combustion engine according to one of the preceding claims,

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characterized by at least one first blade wheel (7, 7', 7", 57a, 57a', 57a",
109),
surrounded by the stator (3, 3', 3", 53, 52', 53", 103, 103', 103"), to which
the
vaporized first working medium (21, 21', 73, 73', 137) may be supplied,
preferably via the first connection device (27, 27', 27", 75, 75', 75", 77,
77', 77",
139), for rotating the rotor (11, 11', 11", 61, 61', 61", 117, 117', 117")
relative to
the stator (3, 3', 3", 53, S3', 53", 103, 103', 103"), particularly axially,
radially,
and/or at a predefined angle in relation to the fast axis of rotation.
17. The thermal combustion engine according to Claim 16,
characterized by at least one flow guiding wheel (8", 125), which is
operationally
linked to the rotor (11", 117, 117', 117"), particularly connectable thereto
for
secure rotational driving, and is positioned upstream and/or downstream of the
vaporized working medium (21', 137) in relation to the first blade wheel (7",
109), the flow guiding wheel (8", 125) being positioned at least partially
concentrically to the first blade wheel (7', 109), particularly inside and/or
outside
the first blade wheel (7", 109).
18. The thermal combustion engine according to Claim 16 or 17,
characterized by at least one second blade wheel (57b, 57b', 57c', 57b", 57c",
111), which is surrounded by the stator (53, 53', 53", 103, 103', 103") and is
particularly positioned downstream of the vaporized working medium in relation
to the flow guiding wheel, at least one deflation wheel (79a, 79b, 79a', 79b',
79c', 79a", 79b", 79c"), which is operationally linked to the rotor (61, 61',
61"),
particularly connectable thereto for secure rotational driving, preferably
being
positioned upstream and/or downstream of the vaporized working medium (73,
73') in relation to the second blade wheel (57b, 57b', 57b", 57c', 57c"), the
deflection wheel particularly being positioned at least partially
concentrically to
the first and/or second blade wheel, particularly inside and/or outside the
first
and/or second blade wheel.
19. The thermal combustion engine according to one of Claims 16 to 18,

35
characterized in that the first blade wheel (7, 7', 57a, 57a', 57a"), the flow
guiding
wheel, the second blade wheel (57b, 57b', 57c', 57b", 57c"), and/or the
deflection
wheel (79a, 79b, 79a', 79b', 79c', 79a", 79b", 79c") are at least partially
positioned in the turbine chamber (25, 25').
20. The thermal combustion engine according to Claim 18 or 19,
characterized in that the second blade wheel has a second diameter deviating
from
a first diameter of the first blade wheel and/or a number and/or geometry of
the
blades deviating from the number and/or geometry of the blades of the first
blade
wheel.
21. The thermal combustion engine according to one of Claims 18 to 20,
characterized by multiple second blade wheels (57b', 57c', 57b", 57c") and/or
deflection wheels (79a, 79b, 79a', 79b', 79c', 79a", 79b", 79c"), the second
blade
wheels (57b', 57c') preferably having different diameters, different
geometries,
and/or a different number of blades from one another and/or the deflection
wheels
(79a', 79b', 79c') having different diameters, different geometries, and/or a
different number of blades from one another.
22. The thermal combustion engine according to one of Claims 16 to 21,
characterized is that the geometry and/or the position of at least one blade
of the
first blade wheel, of at least one second blade wheel, of the flow goading
wheel,
and/or of at least one deflection wheel is/are adjustable, preferably during
operation of the thermal combustion engine.
23. The thermal combustion engine according to one of the preceding claims,
characterized by at least one heating means for applying heat to the vapor
generation device (11a, 11a', 11a", 13, 13', 61a, 61a', 63, 63', 115, 115',
115",
129, 129', 129"), particularly the first chamber (13, 13', 63, 63', 129, 129',
129"),
preferably in the form of a fluid heating medium, particularly in the form of
hot
gases, such as combustion gases (29, 29', 71, 71', 135), a heat source, for

36
example, in the form of at least one heating spindle, which is integrated in a
wall
of the first chamber, which particularly comprises a material of high thermal
conductivity and/or is structured for high conductive thermal transport,
and/or is
implemented on the surface of this wall, at least one first flow device for a
heating
fluid (29, 29', 71, 71', 135), at least one first structure, which is
implemented on
an outside of the wall (11a, 11a', 11a", 61a, 61a', 115, 115', 115") of the
first
chamber (13, 13', 63, 63', 129, 129', 129") and may particularly have the
heating
fluid (29, 29', 71, 71', 135) flow through it, and/or at least one second
structure,
which is implemented on an inside of the wall (11a, 11a', 11a", 61a, 61a',
115,
115', 115") of the first chamber (13, 13', 63, 63', 129, 129', 129' and may
particularly have the preferably vaporized working medium (21, 21', 73, 73',
137)
flow through it.
24. The thermal combustion engine according to Claim 23,
characterized in that the first flow device is integrated in the wall, the
heating
means preferably being supplied to the first how device via a shaft of the
stator
and/or the heating paeans particularly being circulated in a preferably closed
heating loop which comprises the first flow device.
25. The thermal combustion engine according to one of the preceding claims,
characterized by at least one coolant to apply cold to the condensation device
(11c, 11c', 11c", 15, 15', 61c, 61c', 65, 65', 65", 107, 107', 107", 131,
131',
131"), particularly the second chamber (15, 15', 65, 65', 65", 131, 131',
131"),
preferably in the form of a fluid cooling medium, particularly in the form of
nitrogen or cold air (31, 31', 81, 81', 141), a cooling source, for example,
in the
form of at least one Peltier element, which is particularly implemented in a
wall
of the second chamber, which preferably comprises a material of high thermal
conductivity and/or is structured for high convective heat transport, and/or
is
implemented on the surface of this wall, at least one second flow device for a
cooling fluid (31, 31', 81, 81', 141), such as nitrogen or cold air, at least
one third
structure, which is implemented on an outside of the wall (11c, 11c', 11c",
61c,

37
61c', 107, 107', 107") of the second chamber (15, 15', 65, 65', 65", 131,
131',
131") and may particularly have the cooling Quid (31, 31', 81, 81', 141) flow
through it, and/or at least one fourth structure, which is implemented on an
inside
of the wall (11c, 11c', 11c", 61c, 61c', 107, 107', 107") of the second
chamber
(15, 15', 65, 65', 65", 131, 131', 131") and may particularly have the working
medium (21, 21', 137) flow through it.
26. The thermal combustion engine according to Claim 25,
characterized in that the second flow device is integrated in the wall, the
coolant
preferably being supplied to the second flow device via a shaft of the stator
and/or
the coolant particularly being circulated in a preferably closed cooling loop
which
comprises the second flow device.
27. The thermal combustion engine according to one of Claims 23 through 26,
characterized in that the heating fluid (29, 29', 71, 71') has a flow
direction in the
area of the heating means which runs essentially radially outward from the
first
axis of rotation to the external circumference of the rotor (11, 11', 11", 61,
61',
61"), and/or the cooling fluid (31, 31', 81, 81') has a flow direction in the
area of
the coolant which runs essentially radially from the outer circumference of
the
rotor (11, 11', 11", 61, 61') in the direction of the first axis of rotation.
28. The thermal combustion engine according to one of the preceding claims,
characterized by at least one supply device for supplying at least one
vaporized
second working medium, the first and second vaporized working media
preferably being identical.
29. The thermal combustion engine according to one of the preceding claims,
characterized by at least one removal device for removing at least a part of
the
vaporized and/or liquid first working medium.
30. The thermal combustion engine according to Claim 28 or 29,

38
characterized by at least one fifth flow control and/or regulation device,
which is
operationally linked to the supply device, and/or at least one sixth flow
control
and/or regulation device, which is operationally linked to the removal device.
31. The thermal combustion engine according to one of the preceding claims,
characterized by at least one control and/or regulation unit, which is
operationally
linked to the vapor generation device, the condensation device, the first
and/or
second nozzle of the first, second, third, fourth, fifth, and/or sixth flow
control
and/or regulation device, the first blade wheel, at least one second blade
wheel,
the flow guiding wheel and/or at least one deflection wheel, the heating
means,
the cooling means, and/or a sensor for measuring the rotational velocity of
the
rotor.
32. A use of a thermal combustion engine according to one of the preceding
claims as
a topping turbine, exhaust vapor turbine, back pressure turbine, extraction
turbine,
impulse turbine, and/or reaction turbine.

Description

CA 02521654 2005-10-04
r
Thermal combustion engine which converts thermal energy into mecha~ucal energy
and
use thereof
Description
The present invention relates to a thermal combustion engine which converts
thermal
eaergy into mechanical energy and the use of such a thermal combustion engine.
Multiple thermal combustion engines are known from the related art. Thus, for
example,
DE 199 48 128 A1 discloses a device and a method for generating flow energy in
liquids
from heat, In this case, th,e device comprises a housing having a vapor intake
opening
connected to a vaporizer and a vapor outlet opening connected to a condenser.
Furthermore, the housing has a flow opeaing connected to a hydromotor and a
return
connection conuaected thereto. A rotor is positioned within. the housing,
which has
multiple cells, in each of which pistons are located. By supplying vapor under
pressure
through the vapor intake opening, removing the vapor from the vapor outlct
opening, and
rotating the rotor, a hydraulic liquid is pumped through the hydromotor.
However, this
device has the disadvantage that it has a complex construction and, because of
its
multicomponent structure, has a large overall volume and may therefore not be
implemented compactly. In additio~a, a pump is required in. particular in
order to return
the liquid condensed in the condenser back to the vaporizer.
l~thermore, US 2002/0194848 A1 discloses a vapor motor for driving a
generator. In
this case, the vapor motor comprises a rotary engine, which is integrated in a
closed

r
CA 02521654 2005-10-04
2
rrapor loop. The vapor loop comprises a vapor generator, a vapor injector for
injecting
vapor into the rotary engine, and a condenser for condensing the vapor which
exits out of
the rotary engine. A combustion is performed within the vapor motor in order
to supply
heat to a vapor generator which comprises a bundle of circular pipes. The
vapor exiting
out of the vapor generator is applied to the rotary engine and subsequently
flows through
a further bundle of pipes which are used for preheating combustion air. The
vapor thus
partially cooled is supplied to a condenser, and the water condensed in the
condenser is
subsequently supplied back to the vapor generator via a pump. However, this
vapor
motor also has the disadvantages of a complex conshuctioa and a lack of
compactness
because of the multiple components necessary, including a pump for conveying
water
condensed in the condenser into the vapor generator. Furthermore, the mtary
cagine is
subject to wear, because of which high mainte~ce costs result.
In addition, thermal combustion engines comprising vapor turbines are known
firom the
related art. Vapor generated in an external vapor generator is supplied to the
vapor
turbines in such a way that a rotor having a blade wheel, which is positioned
iu a housiuvg,
is driven. After passing through the blade wheel, the vapor coming out of the
housing is
condensed, and the working medium thus condensed is supplied back to the vapor
generator via a pump. However, these vapor turbines have the disadvantage that
additional components, particularly valves, control elements, or pumps, are
necessary in
order to achieve conversion of thermal energy into mechanical energy. Tn
particular,
thermal combustion engines of this type, which use a vapor turbine, have a
high power to
weight ratio, i.e., the weight in relation to the extractable power, because
of the large
number of individual components.
The object of the present invention is therefore to provide a thermal
combustion e~ ne
which overcomes the disadvantages of the related art. In particular, the
conversion of
thermal energy into mechanical energy is to be attained while achieving a low
power to
weight ratio, a high e~ciency, low pollutant and noise emissions, and a
simple, low-
maintenancey and low-wear constntction.

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3
This object is achieved according to the present invention in a fast
implementation in that
the thermal combustion engine comprises at least one vapor generation device
for at least
partially vaporizing a first liquid workdng medium using thermal energy
supplied to the
thermal combustion engine, at least one rotor, which is drivabke using the
vaporized fazst
working medium to generate mechanical energy and is rotatable around a first
axis of
rotation in relation to at least one stator, anti at least one condensation
device for
condensing the vaporized first working medium after driving the rotor, the
rotor
essentially completely surrounding the stator, and the rotor essentially
completely
enclosing the vapor generation device and the condenusation device.
Alternatively to the implementation descn'bed, the object according to the
present
invention is achieved in a second implementation by a thermal combustion
engine
comprising at least one vapor ge~aeration device for at least partially
vaporizing a first
liquid working medium using thermal energy supplied to the thermal combustion
engine,
at least one rotor, which is drivable using the vaporized first working medium
to generate
mechanical energy and is rotatable around a first axis of rotation in relation
to at least one
stator, and at least one condensation device for condensing the vaporized fast
working
medium after driving the rotor, the tutor at least partially surrounding the
stator.
rn. the second implementation, the rotor may essentially completely enclose
the vapor
generation device and/or the condeiasation device.
1n the embodiments specified above, the stator may essentially completely
enclose the
vapor generation device and/or the condensation device according to the
present
invention.
Alternatively to the two embodiments specified above, the vapor generation
device
and/or the condensation device may be implemented in at least two parts and/or
the rotor
may enclose a first part of the condensation device and/or a first part of the
vapor
generation device and the stator may enclose the other part of the vapor
generation device
and/or the condensation device.

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In this case, in an advantageous embodiment according to the present
invention, at least
one first chamber forming the vapor generation device, at least one second
chamber
forming the condensation device, and at least one turbine chamber are
provided, whereby
preferably the first chamber and the second chamber, the first chamber and the
turbine
chamber, and/or the second chamber and the turbine chamber at least partially
being
separated from one another using at least one, particularly thermally
insulating wall.
1n the above-mentioned alternative embodiment, it is suggested that the
thermal
combustion engine comprise at least one Sirst connection device, which
connects the first
chamber and the turbine chamber for passage of the vaporized first working
medium,
preferably comprising at least one first nozzle, the geometry and/or the
orientation of the
nozzle opening preferably being adjustable, at least one first pipe, and/or at
least one first
opening, which is particularly implemented in the thermally insulating wall.
Tn the two above-mentioned alternative embodiments, at least one second
connection
device, which connects the turbine chambex and the second chamber for passage
of the
vaporized first working modium, may also be provided, preferably comprising ai
least
one second nozzle, the geometry and/or the orientation of the nozzle 'opening
preferably
being adjustable, at least one second pipe, aad/or at least one second
opening, which is
particularly implemented in the Wermally insulating wall.
In the two above-meaotioned embodiments, at least one first flow control
and/or
regulation device, which is operationally linked to the first connection
device, and/or at
least one second flow control and/or regulation device, which is operationally
linked the
second connection device, preferably in the form of a first and/or second
valve, are also
suggested,
Advantageous embodiments of a thermal combustion engine according to the
present
invention have at least one third connection device which connects the first
chamber and
the turbine chamber for passage of the liquid first working medium,
particularly in the

CA 02521654 2005-10-04
form of at least one third opening, which is preferably implemented in the
thermally
iuasulating wall.
At least one fourth connection device, which connects the turbine chamber and
the
second chamber far passage of the liquid first working medium, preferably in
the form of
at least one fourth opening, which is particularly implemented in the
thermally insulating
wall, may also be provided in a thermal combustion engine according to the
present
invention.
In the two above-mentioned alternatives, it is suggested by the present
invention that the
liquid Srst working medium prevent .an exit of the vaporized first working
medium out of
the first chamber through the third andlor fourth connection device,
particularly block the
third and/or fourth opening, doting a rotation of the rotor, particularly
because of the
centrifugal force acting on the working medium.
Furthermore, at Ieast one third flow control and/or regulation device which is
operationally linked to the third connection device and/or at least one fourth
flow control
and/or regulation device, which is operationally linked to the fourth
connection device,
pxeferably in the form of a third and/or fourth valve, particularly a check
valve, is
suggcstod by the present invention.
The second chamber and the turbine chamber may particularly also be molded in
one
piece.
In the above-mentioned em~bodiuooents of the thermal combustion engine
according to the
present invention, at least one flow guiding body may be provided, which is
implemented
in the first chamber, the second chamber, and/or the turbine chamber.
An advantageous embodiment of a thenonal wmbustion engine according to the
present
invention is distinguished by at least one first blade wheel enclosed by the
stator, to
which the vaporized first working medium may be supplied, preferably via the
first

CA 02521654 2005-10-04
6
connection device, to rotate the rotor in relation to the stator, particularly
axially, radially,
and/or at a predeEwed angle in relation to the first axis of rotation.
The above-mentioned embodizn~ent of a thermal combustion engine according to
the
present invention may be distinguished by at least one flow guiding wheel,
which is
operationally linked to the rotor, particularly connectable thereto for secure
rotational
driving, and positioned upstream and/or downstream of the vaporized working
medium in
relation to the ~z~st blade wheel, the flow guiding wheel preferably being
positioned at
least partially concentrically to the first blade wheel, particularly inside
and/or outside the
first blade wheel. Positioning the #low guiding wheel upstream of the
vaporized working
medium in relation to the first blade wheel results in as increase of the
c~ciency in
particular.
The two above-mentioned embodiments of the thermal combustion engine according
to
the present invention may be distinguished by at least one second blade wheel,
which is
enclosed by the stator and is particularly positioned downstream of the
vaporized
working medium in relation to the flow guiding wheel, at least one deflection
wheel,
which is operationally linked to the rotor, particularly connectable thereto
for secure
rotational driving, preferably being positioned upstream and/or downstream of
the
vaporized working medium in relation to the second blade wheel, the deflection
wheel
particularly being positioned at least partially concentrically to the first
and/or second
blade wheel, particularly inside and/or outside the first and/or second blade
wheel.
In. the three above-mentioned alternative embodiments, the present invention
particularly
provndes that the first blade wheel, the flow guiding wheel, the second blade
wheel,
and/or the deflection wheel is/are at Least partially positiozxed in the
turbine chamber.
It is also suggested that the second blade wheel have a second dianueter
deviating from
the first diameter of the fizst blade wheel and/or a number and/or geom~y of
the blades
deviating from the number and/or geometry of the blades of the first blade
wheel.

CA 02521654 2005-10-04
7
Advantageous embodiments of a thermal combustion engine according to the
present
invention are also distinguished by multiple second blade wheels and/or
deflection
wheels, the second blade wheels preferably having different diameters,
different
geometries, and/or differcnt numbers of blades from one another, and/or the
deflection
wheels having different diameters, different geometries, and/or different
numbers of
bladcs from one another.
The geometry and/or the position of at least one blade of the first blade
wheel, of at least
one second blade wheel, of the flow guiding wheel, and/or of at least one
deflection
wheel may also be adjustable, preferably during operation of the thermal
combustion
eagme.
Furthermore, the present invention suggests at least one heating means for
applying heat
to the vapor generation device, particularly the first chamber, preferably in
the form of a
fluid heating medium, particularly in the foam of hot gases, such as
combustion gases, a
heat source, in the Form of at least one heating spindle, for example, which
is integrated
in a wall of tbie first chamber, which particularly comprises a material of
high thermal
conductivity and/or is structured for high convective heat transport, andlor
is
implemented on the surface of this wall, at least one flow device for a
heating fluid
and/or at least one first structure, which is implemented on an outside of the
wall of the
first chamber and may particularly have the heating fluid flow through it,
and/or at least
one second structure, which is implemented on an inside of the wall of the
first chamber
and particularly may have the preferably vaporized working medium flow through
it.
In the above-mentioned embodiment, the first flow device may be integrated in
the wall,
the heating means preferably being supplied to the first flow device via a
shaft of the
stator andlor the heating means particularly being circulated i~u a preferably
closed
heating loop which comprises the first flow device.
Furthermore, the present invention suggests at least one coolant for applying
cold to the
candcnsation device, pazticularly the second chamber, preferably in the form
of a fluid

CA 02521654 2005-10-04
8
cooling medium, particularly in the fornn of nitrogen or cold air, a cooling
source, in the
form of at least one Peltier elenuent, for example, which is particularly
integrated in a
wall of the second chamber, which preferably comprises a material of high
thermal
conductivity and/or is structured for high convective heat transport, and/or
is
implemented on the surface of this wall, at least one second flow device for a
cooling
fluid, such as nitrogen or cold air, and/or at least one third- structure,
which is
implemented on an outside of the wall of the second chamber and may
particularly have
the cooling fluid flow through it, an~dlor a fourth structure, which is
implemented on an
inside of the wall of the second chamber and may particularly have the working
medium
flow through it.
In. the above-mentioned embodiments, the present invention also suggests that
the second
flow device be integrated in the wall, the coolant preferably being supplied
to the second
flow device via a shaft of the stator and/or the coolant particularly bring
circulated in a
preferably closed cooling loop comprising the second flow device.
In the four above-mentioned alternative embodiments, it is considered
advantageous in
the present invention that the heating fluid has a flow direction in the yea.
of the heating
means which runs essentially from the fizst axis of rotation tadially outward
to the
external circumference of the rotor, and/or the cooling fluid has a flow
direction in the
area of the cooling means which runs essentially radially from the outer
circumference of
the rotor in the direction of the first axis of rotation.
At least one supply device ~or supplying at least one vaporized second working
medium
may also be provided, the fizst and second vaporized workcing medium
preferably being
identical.
Furthermore, an advantageous embodiment of the present invention provides at
least one
removal device for removing at least a part of the vaporized and/or liquid
first working
medium.

CA 02521654 2005-10-04
9
At least one fifth flow control and/or regulation device, which is
operationally linked to
the supply device, and/or at least one sixth flow control and/or regulating
device, which is
operationally linked to tl~e removal device, are advantageously provided
Finally, the present invention suggests at least one control ~d/or regulation
unit which is
operationally linked to the vapor generation device, the condensation device,
the first
and/or second nozzle of the first, second, third, fourth, fifth, and/or sixth
flow control
andlor regulation device, the first blade wheel, at least one second blade
wheel, the flow
guiding wheel and/or at least one deflection wheel, the heating means, the
cooling means,
and/or a sensor fox measuring the rotational speed of the rotor.
Furthermore, the present invention provides the use of a thermal combustion
engine
according to the present invention as a topping turbine, exhaust vapor
turbine, back
pressure turbine, extraction turbine, impulse turbine, and/or reaction
turbine.
The present invention is therefore based on the surprising recognition that
the
impleme~atioa of a vapor turbine in the form of an external rotor motor, in
which a
vapor generation device and a condensation device arc integrated in the rotor,
results in a
constructively simpler construction of a thermal combustion engine being able
to be
implemented In particular, a thermal combustion engine may be provided which
dispenses with control elements andlor impellers, such as valves or pumps for
conveying
a working medium from a vaporizer to a condenser. Through the integration of a
vaporizer and condenser in a rotor which rotates around at least one stator
having a blade
wheel, automatic conveyance of working medium from the condenser to the
vaporizer is
achieved according to the present invention via the centrifugal force acting
on the
worIdng medium through the rotation. In addition, the rotational movement of
the rotor
and therefore the centrifugal force acting on the working medium ensures that
the
working medium itself closes a connection channel nmning from the condenser to
the
vaporizer in such a way that vapor generated in the vaporizer may only reach
the
condenser by exiting the vaporizer, hitting the blade wheel, and therefore
causing rotation
of the rotor. In particular, the centrifugal force acting on the working
medium due to the

CA 02521654 2005-10-04
lU
rotation of the rotor causes a transition of the vaporized workiuag medium
from the vapor
generator into the condenser to be possible only in the way described above
after passing
through the blade wheel, eves at higher pressures within the vapor generator
in relation to
the pressure in the condenser, because of the hydrostatic pressure caused by
the
centrifugal force. This means that a centrifugal force closure between the
condenser and
the vaporizer is implemented by the construction of a thermal combustion
engine
accordi~o~g to the present invention, This centrifugal force closure is also
used as a pump
for conveying working medium fi~om the condenser into the vaporizer. This
results in
additional feed pumps, etc. being able to be dispensed with. Tn addition, the
construction
of the vapor turbine as an external rotor motor allows a high e~ci~cy of the
thermal
combustion engine. Both heating of the machine on the vaporizer side, using
combustion
gases, fox example, and also cooling on the condenser side, using cold air,
for example,
are preferably performed in the countercurrent principle according to the
present
invention, arbitrary flow directions of the cooling and/or heating medium
otherwise being
possible. Efficient excitation of the combustion gases is achieved in this
case in that
combustion gases of higher tempec~ature heat the area in proximity to the axis
of the rotor
and therefore especially hot vapor exits out of the vapor generator, which is
then
particularly directed onto the blade wheel of the stator via nozzles. The
combustion gases
then flow in the radial direction from the axis of rotation of the rotor
outward to the
external circumference of the rotor, where the cooling combustion gases bring
to a boil
the liquid working medium, which is located there at the external
circumference of the
rotor because of centrifugal force. The vapor generated in this case travels
in the rotor in
the direction of the axis of rotation of the rotor and is continuously heated
because of the
temperature of the combustion gases, which becomes higher and higher in this
direction,
so that an isobaric expansion may occur, for example. On the condenser side,
the cooling
air flows from the external circumference of the rotor in the radial direction
toward the
axis of rotation of the rotor, outside the rotor. Thus, vapor which flows
radially outward
from the axis of rotation in the interior of the rotor is increasingly cooled
and condensed.
Therefore, the construction of the thermal, combustion engine according to the
present
invention as a vapor turbine in the external rotor principle allows the use of
a

r
CA 02521654 2005-10-04
11
countercurr~t principle both for heating a working liquid and also for cooling
it, which
results in an increase of the efficiency of the thermal combustion engine_
Further features and advantages of the present invention result from the
following
description, in which preferred embodiments of the present invention are
explained for
exemplary purposes on the basis of schematic figures.
Figure 1 shows a sectional view of a first embodiment of a thermal combustion
engine according to the present invention;
Figure 2 shows a sectional view of the thermal combustion engine of Figure 1
along the plane A A of Figure 1;
Figure 3 shows a sectional view of a second embodiment of a thermal combustion
engine according to the present invention;
Figure 4 shows a sectional view of the thermal combustion engine of Figure 3
along the plane B B of Figure 3;
Figure 5 shows a sectional view of a third embodiment of a thermal combustion
engine according to the presort i~avention;
Figure 6 shows a sectional view of the thermal combustion engine of Figure 5
along the plane B-B of Figure 5;
Figure 7 shows a sectional view of a fourth eaabodiaxent of a thermal
combustion
engine according to the present invention;
Figure 8a shows a sectional view of a fifth embodiment of a thermal combustion
engine according to the present invention;

CA 02521654 2005-10-04
12
Figure 8b shows a sxtional view of an alteration of the fifth embodiment of a
thermal combustion engine according to Figure 8a;
Figure 9 shows a sectional view of a sixth embodiment of a thermal combustion
engine according to the present invention;
Figure I O shows a sectional view of a seventh embodiment of a thermal
combustion
engine according to the present invention; and
Figure 11 shows a sectional view of an embodiment of a thermal combustion
engine
according to the present invention.
A first embodiment of a thermal combustion engine is illustrated in Figures 1
and 2 in the
form of a vapor turbine I, or rather a compact vapor turbines having an
integrated vapor
generation zone. The vapor turbine 1 comprises a stator 3, which in turn
comprises a
fixed shaft 5 and a blade wheel 7 connected to tbie shaft 5. A rotor 11 having
front walls
l la, l lc and a peripheral wall l lb is mounted so it is rotatable in
relation to the stator 3
via a bearing 9 and a seal 10 in such a way that the interior of the rotor I 1
is sealed. The
rotor 11 essentially comprises a first chamber 13 and a second chamber 15. The
chambers
13, 15 are separated from one another by a thermally insulating wall 17,
except for
openings 19 of the wall 17 in the area of the peripheral wall I lb of the
tutor 11. A
working medlutn 21, preferably water, may flow through the openings 19 from
the
second chamber 15 into the first chamber 13, as will be descn'bed later in
detail. Because
of the centrifugal forces acting on the working medium 21 during rotation of
the rotor 11,
the working medium 21 eoDocts at the peripheral wall l lb of the rotor 11, as
shown in
Figures 1 and 2. The first chamber 13 is also separated by a partition wall 23
from a
turbine chamber 25, in which the blade wheel 7 is positioned. Openings in the
form of
nozzles 27 are implemented within the partition wall 23. In the following, the
mode of
operation of the being turbine 1 will now be explained:

~
CA 02521654 2005-10-04
13
Combustion gases 29 of a heating device (not shown) are supplied to the rotor
11 on the
front wall l la positioned on the side facing toward the first chamber I3. As
may be seen
in Figure 1, the combustion gases 29 are supplied in such a way that they are
guided
along the rotor 11 from its axis of rotation radially outward In this case,
the first front
wall lIa of the rotor 11 is heated by the combustion gases 29, because of
which the
worlang medium 21 located in area of the fast chamber 13 is heated, which
finally results
in at least partial vaporization of the working medium 21 in the first chamber
13. The
first chamber 13 thus acts as a vapor generation chamber. By regulating the
heat supplied
using control and/or regulation of the quantity of supplied combustion gas 29
and/or its
temperature, the power output by the vapor turbine 1 and/or the speed thereof
may be
controlled and/or regulated.
kn order to allow sul~cieat heat exchange between the combustion gases 29 and
the
interior of the fimt chamber 13 or vapor generation chamber, heat exchanger
elements
(not shown) are located on the first front wall I 1 a of the rotor 11 in area
of the first
chamber 13, preferably both on the side facing toward the combustion gases 29
and also
on the side facing toward the first chamber 13, which the combustion gases 29
and/or the
working medium 21 vaporized in the first chamber 13 flow through. rn
particular, the
first front wall l la of the rotor 11 comprises a material having high thermal
conductivity.
The vaporized working medium 21 travels within the first chamber 13 from the
peripheral wall l lb to the axis of rotation of the rotor I1, A countercurrent
principle is
thus implemented in. the vapor turbine 1. This results in e~cient exploitation
of the
energy of the cozabustion gases 29, The combustion gases 29 of higher
temper~axure are
incident on the area of the first chamber 13 facing toward the axis of
rotation of the rotor
11, so that especially hot vapor arises in this area. The combustion gases 29
traveling in
the radial direction of the rotor 11 then cool down again and bring to a boil
the working
medium 21 in area of the peripheral wall l lb of the rotor 11. E~cient
exploitation of the
thermal energy of the combustion gases 29 is thus achieved.

CA 02521654 2005-10-04
14
The working medium 21 heated in area of the peripheral wall l lb of the rotor
11 Qows
through the first chamber 13 and/or vapor generation chamber in the direction
toward the
partition wall 23, while expanding in an isobaric way Therefore, an increased
internal
pressure arises within the first chamber 13, which is noticeable in that the
level of the
working medium 21 in the area of the first chamber 13 is lower than that in
the second
chamber 15. The vapor thus generated in the first chamber 13 flows through the
nozzles
27 and is expanded adiabatically at the same tiuae. As may be seen in Figure 2
in
particular, the nozzles 27 are not oriented radially, but rather are inclined,
so that an
optimum angle of inclination of the nozzles 27 is sellable, The vapor thus
hits the blade
wheel 7 in such a way that there is a recoil of the rotor 11 in relation to
the stator 3, which
generates and/or maintains a rotational movement of the rotor 11.
After the passage through the blade wheel 7, the vapor exits from the turbine
chamber 25
into the sa:ond chamber 15, which is used as the condensation chamber. The
vapor cools
there and the working medium 21 therefore condenses out in the area of the
sxond
chamber 15.
Because of the rotation of the rotor 11, condensed woz3ang medium 21 collects
on the
peripheral wall l lb of the rotor 11. In order to achieve cooling of the
vaporized working
medium 21 in. the second chamber 15, which acts as a condensation chamber,
cooling sir
31 is applied to the second front face 11c of the rotor 11. This supply is
also performed in
the countercurrent principle. Cold air flows as cooling air from the outside
of the rotor 11
in the radial direction toward the axis of rotation of the rotor 11. The
cooling air 31 is
heated at the same time. In contrast, the vaporized working medium 21, which
flows
tadially away from the axis of rotation of the rotor 11 in the interior of the
second
chamber 15, is increasingly cooled and condensed in this case. Since therefore
the
already heated cooling air 31 may absorb further heat energy in area of the
axis of
rotation of the rotor 11, a conductive heat exchange between the working
medium 21 and
the cooling modium 31 being supported by structuring of the wall 11 c (not
shown),
preferably in the form of heat exchanger elements, efficient heat dissipation
frora the
second chamber 15 is ensured. The working medium 21 condensed in the second

CA 02521654 2005-10-04
chamber 15 then $ows through the openings 19 in the wall 17 into the first
chamber 13,
where it is again vaporized.
Because of the centrifugal force acting on the worlQng medium 21, it is
accelerated
outarard and therefore closes the openings 19, so that the vapor from the
first chamber 13
may reach the second chamber IS exclusively through the nozzles 27. Even in
the event
of a larger pressure in the first chamiber 13 than the pressure in the second
chamber 15, a
secure closure of the openings 19 is ensured for tb~e vapor of the working
medium 21
generated in the first chamber 13, since the openings 19 are held closed by
the working
mediunr~ 21 because of the hydrostatic pressure caused by the centrifugal
force.
In order to allow the vapor turbine 1 to start up automatically, check valves
may be
positioned within the openings 19. These cause vapor which is initially
generated in the
first chamber 13 to ensure rotation of the rotor 11 by exiting through nozzles
27, so that
aRer beginning the rotation, closure of tb~e openings 19 by the working medium
21 is
ensured. In addition, closure devices, such as valves, may also be provided in
the nozzles
27 in order to achieve control of the rotational velocity of the rotor 11. The
valves in the
openings 19 and the nozzles 27 may particularly be connected to a control and
regulation
device (not shown) in this case. Furthermore, speed control and/or regulation
of the vapor
turbine 1 is possible through variation of the quantity of heat energy
supplied using the
combustion gases 29 and/or through variation of the angle of inclination of
the nozzles
27.
A second embodiment of a therzual combustion engine according to the present
invention
is shown in Figures 3 and 4 in the form of a vapor turbine 1', or rather a
compact vapor
turbine, having an integrated vapor generation zone. The vapor turbine 1'
essentially
corresponds in its basic construction to the construction of the vapor turbine
1 illustrated
in Figures 1 and 2. In contrast to the vapor turbine 1, in the vapor turbine
1', the
corresponding elements are provided with the identical reference numbers, but
with an
apostrophe. The vapor turbine 1' essentially differs from the vapor turbine 1
through a
different flow guide of the vaporized and/or liquid working medium 21'.
Similarly to the

CA 02521654 2005-10-04
16
vapor turbine 1, combustion gases 29' are supplied to the rotor 11' of the
vapor turbine 1'
on the fast wall lla' positioned on the side facing toward the first chamber
13'. This
supply is also performed, as may be infected from Figure 3, in the
countercurrent
principle. Working medium 21' provided inside the first chamber 13' is heated
by the
combustion gases 29'. In contrast to the vapor turbine 1, this vaporized
working medium
21' only flows through nozzles 2T into the turbine chamber 25' andlor the
second
chamber 15' after a deflection by nearly 180° using a flow guiding body
14'. This
deflection around the flow guiding body 14' particularly offers the advantage
that
entrained droplets of the working medium 21' may not follow the vapor flow
around the
flow guiding body 14' and thus may not reach the turbine chamber 25' and/or
the second
chamber 15' via the nozzles 27'. The errirained droplets flow with the vapor
flow in the
direction of the axis of rotation of the rotor 11', but move furthear in the
radial direction
and hit the flow body 14', where they are accelerated in the direction of the
peripheral
wall l lb' because of the acting centrifugal force. Furthermore, due to the
flow guiding
body 14', the vaporized working medium 21' may flow essentially up to the axis
of
rotation of the rotor 11' within the first chamber I3', and therefore maximum
heat
transfer of the energy of the combustion gases 29' to the working medium 21'
may occur.
After a deflection of the vaporized working medium 21', it flows through
nozzles 27' in -
the radial direction to the blade wheel 7'. The vaporized working modium 21'
then flows
within the second chamber 15' in proximity to the shaft 5' in the direction of
the front .
wall Ilc'. This flow guiding is particularly achieved by a flow guiding body
16'
positioned in the second chamber 15' in the area of the blade wheel 7'. This
flow guiding
ensures that the vaporized working medium 21' flows in the countercurrent
principle in
relation to the cooling air 31' on the inside of the front wall I 1 c' in the
direction of the
peripheral wall l lb'. In addition, the flow guiding within the vapor turbine
1' offers the
advantage that, in comparison to the vapor turbine 1, a blade wheel 7' may be
used which
has a larger diameter than the blade wheel 7 of the vapor turbine 1. The vapor
turbine 1'
may therefore be operatod at lower speeds.

CA 02521654 2005-10-04
17
?he working medium 21' condensed in the second chamber 15' collects on the
peripheral
wall l lb' because of the rotational forces and flows through channels 20'
back into the
first chamber 13'. The channels 20' are formed in this case by the peripheral
wall l lb'
and au essentially cylindrical partition wall 24', which particularly
comprises the flow
guiding bodies 14' and 16'. In this case, the partition wall 24' is
implemented as
thermally insulating particularly in the area of the chanuaels 20' in order to
avoid heating
of the working medium 21' within the charunels 20'.
A third embodiment of a thermal combustion engine according tv the present
invention is
shown in Figures 5 and 6 in the form of a vapor turbine 1", or rather a
compact vapor
turbine. The vapor turbine 1" essentially corresponds in its basic wustruction
to the
construction of the vapor turbine 1' illustrated in Figures 3 and 4. The
elements of the
vapor turbine 1" which correspond to those of the vapor turbine 1' have
identical
refere~ace numbers. 'l;he vapor turbine 1" differs from the vapor turbine 1'
essentially in
that a blade wheel 7" is provided, which is connected via at least one
connection element
6" to a shaft 5" of the stator 3". As may be seen in Figure 6 in particular,
the blade wheel
7" coneer~trically encloses a flow guiding wheel 8", which is connected via
coninection
elements 18" to the wall 1 T' and therefore to the rotor 11", as may be seen
from Figure 5
in particular. As shown in Figure 6, the blade wheel T' has blades 28", while
the flow
guiding wheel 8" comprises blades 30". Through this arrangement of the flow
guiding
wheel 8" in relation to the blade wheel 7", a further increase of the e~ciency
of the vapor
turbine 1" is achieved in comparison to the vapor turbine 1'. The working
medium 21'
exiting out of the aozzles 2T' first hits the blades 28" of the blade wheel
T', through
which the rotor 11" is driven in relation to the stator 3" to which the blade
wheel 7" is
connected. The woriang medium exitW g out of the blade wheel 7" hits the
blades 30" of
the flow guiding wheel 8", which is connected to the rotor 11 ". Therefore,
the remaining
energy present in the worlang medium is also at least partially converted into
movement
energy of the rotor 11" by the flow guiding wheel 8".
The vapor turbines 1, 1', 1" illustrated in Figures 1 through 6 are single-
stage radial
turbines, since only one blade wheel 7, 7', T' is provided in each case and,
in. addition,

CA 02521654 2005-10-04
18
the vapor hits the blade wheels 7, 7', 7" in the radial direction. In.
contrast to this, a fourth
embodiment of a thermal copabustion engiae according to the present invention
is
illustrated in Figure 7 in the form of the vapor turbine 51, or rather a
multistage axial
turbine, which is constructed as an impulse turbine, i.e., according to the
Curtis principle.
Impulse turbines are understood as vapor turbines in which the intake and
outlet pressure
of the vapor of a working mediuux iuato and/or out of the running blades of a
blade wheel
are equal. Therefore, the blades of an impulse turbine are driven using the
energy from
the velocity reduction of the vapor in the running blades. In particular, the
vapor turbine
51 has velocity stages, i.e., the velocity of the vapor is exploited in
stages. In order to
achieve higher theanodynamic e~ciency, it is also provided in impulse turbines
of this
type that pressure stages are generated, i.e., a pressure gradient is divided
into multiple
stages. This offers the advantage that vapor velocities which are too large
may be
avoided.
The vapor turbine 51 has a stator 53 which surrounds a shaft 55. Blade wheels
57a and
57b are positio~aed spaced apart from one another on the shaft 55. A rotor 61
is provided
in the vapor turbine 51 so it is rotatable in relation to the stator 53 via a
bearing 59 and
seals 60. The rotor 61 has a first front wall 61a, a peripheral wall 61b, and
a second front
wall 61c. Furthermore, a first chamber 63, which is used as a vapor generation
chamber,
and a second chamber 65, which is used as a condensation chamber, are
implemeated
inside We rotor 61. In addition, the vapor turbine 51, in contrast to the
vapor turbine 1,
has an equalizing chamber 67 for collecting liquid working medium 73. The fast
chamber 63 and the equalizing chauxber 67 are separated from one another via a
thermally insulating wall 69.
Similarly to the vapor turbines 1, 1', 1", in the vapor turbiune 51,
combustion gases 71 are
supplied to the first front wall dla of the rotor 61 in the countercurrent
principle. At least
a part of the working mediu~oa 73 is thus vaporized within the first chamber
63. The
working medium 73 thus vaporized is firstly supplied via lines 75, at the ends
of which
nozzles 77 are positioned, to the first blade wheel 57a. Because of the
expansion of the

CA 02521654 2005-10-04
19
vapor in the area of the nozzle 77 and the incidence of the vapor on the first
blade wheel
57a, there is a rotational movement of the rotor 61.
In order to be able to completely exploit the energy residing in the vaporized
working
medium, in 'the vapor turbine 51, the vapor directed axially to the first
blade wheel 57a
enters a deflection wheel 79a, which rotates together with the rotor 61, after
the passage
through the blade wheel 57a. This deflection wheel particularly acts as a
running wheel
and converts the energy residing in the vapor into work energy. Furthermore,
the vapor
flow is deflected in the deflection wheel 79a before this flow is incident on
a second
blade wheel 57b, which is also connected to the shaft 55, again essentially in
the axial
direction in relation to the axis of rotation of the rotor 61. ARer passing
through the
second blade wheel 57b, the vapor reaches a second deflection wheel 79b, also
particularly used as a running wheel, which is also connected to the rotor 61.
The vapor
then enters the second chamber 65, where it is cooled and condensed because of
the
cooling of the second front wall 61 c of the tutor 61 using cooling air 81.
The condensed
working medium 73 than flows out of the second chamber 65 via the equalization
chamber 67 into the first chamber 63. 1n this case, the working medium 73
flows through
channels 83 which are implemented between the peripheral wall 61b and an
essentially
cylindrical partition wall 85. The partition wall 85 is used for thermal
insulation of the
area in which the blade wheels 57a, 57b and the deflection wheels 79a, 796 are
located
and, in addition, the peripheral wall 61b andlor the channels 83. For this
purpose, the
partition wall 85 has a low thermal conductivity. In particular, the partition
wall 85 may
be implemented as hollow, and may particularly comprise an insulation
material.
A fiftb embodiment of a thermal combustion engine according to the present
invention is
illustrated in Figure 8a in the form of a multistage vapor turbine 51'. The
basic
conshuction of the vapor turbine 51' essentially corresponds to that of the
vapor turbine
51 illustrated in Figure 7. Therefore, essentially identical components of the
vapor turbine
51' have identical reference numbers as those of the vapor turbine 51, but
with an
apostrophe. In contrast to the vapor turbine 51, the vapor turbine 51' has
three blade
wheels 57a', 57b', and 57c'. Accordingly, the vapor turbine 51' also has three
deflection

CA 02521654 2005-10-04
wheels 79a', 79b', and 79c', which are each connected to tb~e rotor 61'.
Furthermore, the
vapor turbine S 1' dii~ers $om the vapor turbine 51 in that, because of the
goomctry of the
noule 77', the blade wheels 57a', 57b', 57c', and deflection wheel 79a', 79b',
and 79c',
it is a reaction turbine. Since the vapor flows through the blade wheels 57a',
57b', 57d'
[sic] at an inclined. angle in relation to the axis of rotation of the rotor
61', the vapor
turbine 51' is additionally a diagonal turbine. The construction as a reaction
turbine
means that the vapor exits out of the nozzle 77' at a relatively high,
pressure, and the
vapor pressure is reducod in the blades of the blade wheels 57a', 57b', and
57c'.
Therefore, there is an energy conversion of the vapor in the blades of the
blade wheels
57a', S7b', 57c', which is composed of the volocity conversion of the vapor
and, in
addition, the back pressure occurring upon relaxation of the vapor. Therefore,
multiple
Pressure stages are implemented 'within the vapor turbine S 1', which have a
low staged
pressure gradient and therefore achieve a favorable flow design and a good
dynamic
efficiency.
~uthermore, an alteration of the vapor turbine S1' illustrated in Figure 8a is
shown in
Figure 8b in the form of the vapor turbine S1". The basic construction of the
vapor
turbine 51" essentially corresponds to that of the vapor turbine S l' and
identical elements
of the vapor turbine 51" in comparison to the vapor turbine S 1' have
identical reference
numbers. The vapor turbine S1" essentially differs from the vapor turbine S1'
thmugh a
digcrent geometric design of the blade wheels 57a", 57b", 57c", the deflection
wheels
79a", 79b", and 79c", and the partition wall 85". The blade wheels 57a", 57b",
57c" each
diger from one another through different diameters. In addition, the geometry
of the
blades of the blade wheels 57a", 57b", 57c" differs to produce velocity and/or
pressure
stages within the vapor turbine S I ". Correspondingly, the shape of the
partition wall 85"
and the shape of the second chamber 65" are adapted to these different
diameters. In
addition, the lines 75" and the nozzles 77" are also adapted to the different
geometry of
the blade wheel 57a" in comparison to the vapor turbine 51'. Finally, the
deflection
wheels 79a", 79b", and 79c" are implemented in such a way that the blades
which they
comprise guide the working medium 73" flowing through the blade wheels 57a",
57b",
57c" diagonally in relation to the axis of rotation of the rotor 6I ".

CA 02521654 2005-10-04
21
The embodiments of a thermal combustion engine accordnag to the present
invention
illustrated in Figures 1 through 8b are jointly distinguished in that the
rotor essentially
completely surrounds the vapor generation device in the form of the chambers
13, 13',
63, 63' and the condensation device in the form of the chambers 15, 15', 65,
65'.
Embodiments according to the present invention of a thermal combustion engine
will
now be described on the basis of Figures 9 through 11, in which the vapor
generation
device and/or the condensation device is essentially completely and/or
partially
surrounded by the stator. These thermal combustion engines also have the
advantages
that they have a low power to weight ratio, a high effcieucy, low pollutant
and noise
emissions, and a simple, low maintenance, and Iow-wear construction. In
particular,
these thermal combustion engines, which are constructed as external rotor
motors, also
have the advantage that the centrifugal force causes a centrifugal force
closure to be
implemented between the condenser and the vaporiser, so that additional feed
pumps
may be dispensed with.
A sixth embodiment of a thermal combustion engine is illustrated in Figure 9
in the form
of a vapor turbine 101, or rather a compact vapor turbine, having an
integrated vapor
generation zone. The constzuction of the vapor turbine 101 is similar to that
of the vapor
turbine 1" illustrated in Figures 5 and 6. Thus, the vapor turbine 101
comprises a stator
103, which in turn comprises a fixed shaft 105. In contrast to the embodiments
according
to the present invention illustrated in Figures 1 through 8s, a front wall I07
of the vapor
turbine 101 is connected to the shaft 105, and thus fornns a part of the
stator 103.
Furthermore, the shaft 105 is connected via the front wall 107 to a first
blade wheel 109
and a second blade wheel 111. In contrast, a periphezal wall 113 and a front
wall 115 are
mounted so they are rotaxable in relation to the stator 103. These walls 113,
115 thus form
a rotor 117. Furthermore, partition walls 119, 121, and 123 are connected to
the rotor for
secure rotational driving. Furthermore, a flow guiding wheel 125 is positioned
on the
partition wall 121. This flow guiding wheel 125 is mounted so that it is
rotatable on the
shaft 105 via a bearing 127. However, mounting the flow guiding wheel 125 on
the shaft
105 is not absolutely necessary. In particular, the rotor 117 may be mounted
sufficiently

CA 02521654 2005-10-04
22
via the sealing devices 133, so that the bearing 127 may be dispensed with.
The interior
of the vapor turbine 101 is subdivided using the preferably thermally
insulating wall 121
into a first chamber 129 and a second chamber 131. In this case, the chamber
129 acts as
a vapor generation chamber, while the chamber 131 acts as a condensation
chamber. The
second chamber 131 is sealed in the area of the transition of the front wall
107 to the
peripheral wall 113 by a sealing device 133. The sealing device 133 may be
implemented
in a form generally known to those skilled in the art. Thus, the sealing
device 133 may
particularly comprise sealing elements, in the forax of O-rings and/or a
labyrinth systems,
for example. However, it is important for the mode of operation of the vapor
turbine I01
that the sealing device 133 ensures a seal of the second chamber 131 and
simultaneously
allows a rotation of the rotor 117 in relation to the stator 103. Therefore,
in the vapor
turbine 101, the vapor generation device is the form of the chamber 129 is
essentially
completely surrounded by the rotor 117, while the condensation device in the
form of the
second chamber 131.having the front wall 107 is essentially completely
surrounded by
the stator 103.
In the follorxing, the mode of operation of the vapor turbine 101 will be
explained.
Similarly to the embodiments described above, combustion gases 135 arc
incident on the
front wall 115 in the countercurrent principle. This causes heating of the
first chaanber
129, which results in a working medium 137 being vaporized. The working medium
13?
enters the second chamber 131 between the partition walls I21, 123 and through
the
nozzles 139. The vaporized working medium hits the first blade wheel 109
there, which
results in driving of the rotor I 17 in relation to the stator 103. After
passing through the
fizst blade wheel 109 connected to the stator 103, the vaporized working
medium hits the
flow guiditpg wheel 125 connected to the tutor 117, thmugh which the rotor 117
is driven
further. After exiting the flow guiding wheel I25, the worlang medium finally
at least
partially hits the second blade wheel 111 connected to the stator 103 via the
front wall
107. 1n order to achieve condensation of the working mediwoa in the area of
the second
chamber 131, cooling air 141 flows along the side of the front wall 107 facing
away from
the chamber 131 in the countercun~ent principle. The condensed working medium
collects
in the area of the peripheral wall 113 because of the rotational movement of
the rotor

CA 02521654 2005-10-04
23
117, dog elements, preferably in the form of blades, being positioned in the
area between
the front wall 10? and the partition wall 119, which rotate together with the
rotor 117,
and are particularly attachod thereto. These dog elements are not absolutely
necessary,
however, but elevate the operational reliability of the centrifugal force
closure by the
working medium 137. The working medium 137 then flows back into the first
chamber
129 between peripheral wall 113 and partition wall 119. The worlang medium 137
also
ensures in the vapor turbine 101 that a closure is achieved betyveen the first
chambPx 129
and the second chamber 131 in the area of the partition wall 119 and the
peripheral wall
113, so that the working medium 137 must always go from the first chamber 129
into the
second chamber 131 by the path via the nozzle 139. The vapor turbine 101
offers the
advantage that the front wall 107 does not exocute a rotational movement,
because of
which there is particularly laminar flow of the cooling air 141 along the
front wall 107.
Therefore, the efficiency of the condensation device in the form of the second
chamber
131, and thus the efficiency of the vapor turbine 101, are increased.
Furthermore, this
construction of the vapor turbine 101 makes the supply of a cooling medium
into the
front wall 107 easier. 'thus, the front wall 107 may be perneated by flow
devices (not
shown) in the form of channels. These channels paay particularly be part of a
closed
cooling loop, in which a cooling fluid, such as water, is circulated. Because
the front wall
107 is connected to the shaft 105 of the stator 103, this cooling medium may
be supplied
through a channel positioned on the shaft 105 or permeating the shaft. Through
this
further cooling possibility, the efficiency of the vapor turbine 101 may be
increased
further.
A, seventh embodimtent of a thermal combustion eng'me according to the present
invention is illustrated in Figure 10 in the form of a vapor turbine 101', or
rather a
compact vapor turbine, having an integrated vapor generation zone. The
construction of
the vapor turbine 101' essentially corresponds to that of the vapor turbine
101, which is
illustrated in Figure 9. In particular, the vapor turbine 101' may have the
dog devices in
the area of the partition wall 119 and the front wall 107 descn'bed in regard
to the vapor
turbine 101. Elements of the vapor turbine 101' identical tv the vapor turbine
101 have
identical reference numbers, while different elements are provided with
identical

CA 02521654 2005-10-04
24
reference numbers and a single apostrophe. The construction of the vapor
turbine 101'
essentially differs from the construction of the vapor turbine 101 in that
both the
condensation device and also the vapor generation device are essentially
completely
surrounded by a stator 103'. The stator 103' comiprises a shaft 1 OS' w'buch
is connected to
both the front wall 107 and also a front wall 115'. The front wall 115' is
therefore not
surrounded by the rotor 117'. The rotor 117' essentially comprises the
peripheral wall
113' which is connected to the partition walls 119, 121, 123_ Furthermore, the
flow
guiding wheel 125 is attached to the partition wall 123. To seal the first
chamber 129',
which is used as the vapor generation device, the peripheral wall 113' is
connected via
sealing device 143' to the front wall 115'. Through this construction of the
vapor turbine
101', in addition to the front wall 107, the final wall 11S' also remains
fixed during
operation of the vapor turbine 101'. The efficiency of the vapor generation
device 129' is
thus increased, since the combustion gases 135 supplied to the front wall 11
S' are not
eddied. Therefore, better heat exchange wrath the first chamber 129' is
achieved and thus
the efficiency of the entire vapor turbine 101' is fiurther increased. A
further increase of
the efficiency of the vapor turbine 101' may be achieved in that the front
wall 115' has a
further flow device in the form of channels permeating the front wall 115',
through which
a heating medium, preferably supplied via the shaft 105', is circulated. Flow
devices in
the form of channels may be provided is the front wall 107 analogously as
descn'bed
previously on the basis of the vapor turbine 101.
Finally, an eighth embodiment of a thermal comibustion engine according to the
present
invention in the form of a vapor turbine 101" is illustrated in Figure 11. The
construction
of the vapor turbine 101" is comparable to that of the vapor turbine 101'
illustrated in
Figure 10. Identical eldnents of the vapor turbine 101" have identical
reference numbers
as the elements of the vapor turbine 101', while differing elemeats have
identical
reference numbers, but with a quotation mark The two vapor turbines 101' and
101"
differ from one another essentially in that the front walls 10T' and 115" are
essentially
implemented in two parts. Thus, the front wall 107" comprises the parts 107a"
and
107b". In this case, the front wall part 107b" is connected to the shaft 105",
while the
front wall part 107a" is connected to the peripheral wall 113". This offers
the advantage

CA 02521654 2005-10-04
that the sealing devices 133" arc not positioned in the area of the working
medium 137,
and a seal may thus be achieved more easily. Analogously, the front wall 115"
is
implemented in two parts, in the form of the first &rnnt wall part 115a" and
the second
front wall part 115b". The $ont wall part 115a" is connected to the peripheral
wall 113",
while the front wall part 115b" is connected to the shaft 105". Because of
this
construction, both the first chamber 129", having the front wall 115", which
is used as the
vapor generation device, and also the second chamber 131", having the front
wall 107",
which is used as the condensation device, are surrounded partially by both the
rotor 117"
and also the stator 103".
In further embodiments of the present invention (not shown), the vaporized
working
medium exiting out of the first chamber may E~rst hit the blade wheel(s), with
a flow
guiding wheel operationally linked to the rotor interposed. Particularly if a
single blade
wheel is used to exploit the energy residing iua the vaporized working medium,
a flow
guiding wheel operationally linked to the rotor, which particularly acts as a
blade wheel,
may be downstream from this blade wheel. In addition, the arrangerue~ of the
deflection
wheel, the flow guiding wheel, and/or the blade wheel is not restricted to an
axial
arrangement in rotation to one another. In order to implement high compactness
of the
thermal combustion engine of the present invention, these wheels may
particularly be
positioned at least partially radially in relation to one another.
In fiuthcr embodiments of the presart invention (not shown), the thermal
combustion
engine may be implemented in the form of back pressure turbines and/or
extraction
turbines, in which vapor generated through additional extraction devices in
the vapor
generation chambers may be taken from the vapor turbines.
A use of the thermal combustion ~gine according to the present invention in
the form of
a topping and/or exhaust vapor turbine may also be performed, in that
additional vapor
may be supplied to the thermal combustion engine externally, in addition to
the vapor
generated within the thermal combustion engine.

CA 02521654 2005-10-04
26
rn regard to the exemplary embodiments of the present invention described
above, it is to
be noted that, as may be seen in particular on the basis of the vapor turbine
1' illustrated
in Figures 3 and 4, the working medium may have a flow course within the
thermal
combustion engine which is tailored to the particular requirements of the
thermal
combustion engine. Thus, it is poss'ble in particular that the working medium
may flow
axially, radially, or even transversely in sections, particularly both
radially toward any axis
of the thermak combustion engine and also away from this axis. The present
inve~a~tion is
thus particularly not restricted to the flow paths of the working medium
illustrated as
examples.
The features of the present invention disclosed in the above description, in
the figures,
and in the claims may be essential for implementing the present invention in
its various
embodiments both individually and in any arbitrary combination.

CA 02521654 2005-10-04
27
List of reference hero
1, 1 , 1" vapor turbine
3, 3', 3" stator
5, 5', 5" shaft
6" connection element
7, 7', 7" blade wheel
8" flow guiding
wheel
9, 9' bearing
10, 10' seal
11,11', 11" rotor
lla, llc, lla', llc', front wall
lla", llc"
11b, l lb', l lb" peripheral wall
13, 13' chamber
14' flow guiding
body
15, 15' chamber
16' flow guiding
body
17, 17', 17" wall
18" connection element
19 opening
20' channel
21, 21' working medium
23 partition wall
24' partition wall
25, 25' turbine chamber
27, 27', 27" nozzle
28', 28" blade
29, 29' combustion gas
30" blade
31, 31' cooling sir
51, 51', 51" vapor turbine

r
CA 02521654 2005-10-04
28
53, 53', 53" ~~r
55, 55'
57a, 57b, 57a', 57b', 57c',
57a", 57b", 57c" blade wheel
59, 59' big
60, 60' seal
61, 61', 61" rotor
61a, 61c, 61a', 61c' front wall
61b, 61b'
peripheral wall
63, 63' chamber
65, 65', 65" chamber
67, 6T equalization chamber
69, 69'
71, 71' combustion gas
73, 73' working medium
75, 75', 75" line
77, 77', 7T' nozzle
79a, 79b, 79a', 79b', 79c',
79a", 79b", 79c" deflection wheel
81, 8I' c~~g ~.
83, 83' channel
85, 85', 85" partition wall
101, 101', 1 O1" vapor turbine
103, 103', 103" ~~r
105, 105', 105"
107, 107" front wall
107a", 107b" front wall part
109 blade wheel
111 blade wheel
113, 113', 113" peripheral wall
115, 115', 115" front wall

CA 02521654 2005-10-04
29
115 a' ; 11 Sb" front wall part
117, 117', 117" rotor
119, 121,123
partition wall
125
flow guiding wheel
127, 127' big
129, 129', 129" chamber
13I, 13I', 131" clamber
133, 133"
135 combustion gas
137 working medium,
139 noz~Ie
141 ~~ ~,
143', 143" sealing elecuent

Representative Drawing