Note: Descriptions are shown in the official language in which they were submitted.
CA 02780754 2012-06-14
1
TURBINE HAVING COOPERATING AND COUNTER-ROTATING ROTORS
IN A SAME PLANE V
TECHNICAL FIELD
[0001] This present
disclosure relates to the field of energy
conversion, and more specifically, to a turbine having cooperating and counter-
rotating rotors.
BACKGROUND
[0002] Most combustion
engines and most compressors use one
or more pistons alternating within cylinders to produce torque or to compress
a
gas. The ubiquitous alternating piston engine generates volume variation,
which is required both in motor or compressor applications, in an inefficient
manner. Due to heavy losses inherent to its alternating mode, this engine
generates tremendous heat, suffers from important levels of friction,
vibrates,
generates shocks at high pressure levels and high temperatures, and is noisy.
The overall thermal efficiency of a typical alternating piston engine used in
an
automotive application is very low, typically in the range of 25%.
[0003] In a four-cycle
engine, the fact that the four strokes (intake,
compression, combustion, exhaust) take place within a same volume,
delimited by the movement of the piston within its cylinder, is a major
conceptual limitation to the efficiency of the motor: An ideal volume for one
stroke, for example admission, is not necessarily the ideal volume for another
stroke, for example expansion during combustion. At the top-dead center of its
revolution, the engine creates high pressure levels and high temperatures
while not producing any torque, leading to heavy heat transfer towards the
engine block, thereby reducing the efficiency of the engine. Moving parts such
as pistons and connecting rods need to be very rigid and heavy in order to
withstand heat shocks, pressure shocks, and constant
acceleration/deceleration cycles. Additionally, high pressure coupled with
high-
2064686 1
CA 02780754 2012-06-14
2
heat points within the cylinders form a condition that is prone to the
formation
of nitrous oxide (N0x), an important pollutant. The quasi-sinusoidal movement
produced by pistons, crankshafts and like components lead to an uneven
output torque produced by the engine. The addition of a heavy flywheel is
required for smoothing the output torque of such conventional engine. The
engine needs to evacuate a large fraction of the generated energy to the
atmosphere, with limited evacuation restriction. The engine is thus very noisy
because exhaust gases are pulsed and expelled from the engine at well above
atmospheric pressures. Compressor applications wherein, for example, an
electric motor drives one or more pistons, generally suffer from most of the
same inconveniences.
[0004] Rotary engines such as the well-known Wankel motor only
partially overcome the above-mentioned deficiencies of the alternating piston
engines. Rotary engines rely on heavy, eccentrically rotating pistons that
still
generate considerable vibrations due to the constant shift of the mass of the
rotating pistons. Moreover, in comparison to the traditional alternating
piston
engine, the Wankel engine suffers from important fuel and lubricating oil
consumption. This engine requires the use of seals for preventing burning
gases from reaching gases that are in their compression phase; failure of
these seals have plagued many rotary engine applications. Friction is also an
important problem of the Wankel engine.
[0005] Traditional turbines such as those used in aircrafts or in
thermal power plants are very complex and too costly for most applications.
These turbines need to operate at very high rotating speeds and are only
efficient within a very limited range of operating speeds in order to ensure
that
gases enter at a precise velocity. Due to its architecture comprising fans
operating in aerodynamic mode, it is not possible to create pressure within a
traditional turbine at a low rotating speed. Additionally, traditional
turbines
become fragile when exposed to non-ideal conditions; for example a turbine
used in nuclear or thermal power plant may be severely impacted when
2064686.1
CA 02780754 2012-06-14
3
subject to "unclean" vapor containing small droplets of water. These droplets
may severely erode the fans of the turbine.
[0006] Therefore, there is a need for an improved turbine capable
of compressing or pumping a fluid and/or generating torque, at improved
energy efficiency levels, the turbine having a low production cost.
SUMMARY
[0007] Therefore, according to the present disclosure, there is
provided a turbine for use in energy generation, energy recovery, motor, pump,
and compressor applications.
[0008] According to an aspect of the present disclosure, there is
also provided a turbine comprising a housing having a perimeter connected to
a top and a bottom, an input port and at least one output port. The turbine
also
comprises two counter-rotating spiral-shaped rotors enclosed within the
housing, each rotor having an axis of rotation. The rotors have a thickness
allowing slightly spaced or barely contacting relation with the top and the
bottom of the housing. The rotors also have four curved arms. The arms of a
first rotor are curved in a direction of rotation of the first rotor while the
arms of
a second rotor are also curved in the direction of rotation of the first
rotor. A
diameter of each one of the rotors extends in length for slightly spaced or
barely contacting relation of a tip of the arms to the perimeter of the
housing
over at least 90 degrees of rotation of the rotors. A distance between the two
axes is such that the tip of an arm of the first rotor comes in slightly
spaced or
barely contacting relation between two arms of the second rotor at some angle
of rotation. As the two rotors rotate, chambers are formed between some of the
arms of the two rotors and between some of the arms and the perimeter of the
housing, in continuously varying shapes. Volumes of the chambers delimited
by theses shapes are further delimited by the top and the bottom of the
housing. A first chamber defined between some arms of the two rotors and the
2064686 1
CA 02780754 2012-06-14
4
perimeter of the housing is in an expansion phase when a second chamber is
created and starts to expand between some arms of the two rotors. One of the
first and second chambers is in connection with the input port. The first and
second chambers are expanding while at least a third chamber is in connection
with the at least one output port.
[0009] The present disclosure further relates to a turbine
comprising a housing having an input port and at least one output port and two
rotors enclosed within the housing. The rotors are counter-rotating in a same
plane. A plurality of chambers are formed within the housing and delimited by
arms of the rotors. The arms of the rotors cooperate in their rotation to
create a
first chamber and a second chamber, the first chamber and the second
chamber concurrently expanding as the rotors rotate, the first chamber
starting
to expand earlier than the second chamber. One of the first and second
chambers is in connection with the input port. A third chamber is in contact
with
the at least one output port.
[0010] The present disclosure also relates to a motor, comprising a
combustion turbine. The combustion turbine comprises a housing having an
input port and at least one output port, two rotors enclosed within the
housing
and counter-rotating in a same plane, a plurality of chambers formed within
the
housing and delimited by arms of the rotors, an ignition mechanism, and an
output shaft is operably connected to at least one of the two rotors. The arms
of the rotors cooperate in their rotation to create a first chamber, the first
chamber and at least a second chamber concurrently expanding as the rotors
rotate, the second chamber starting to expand earlier than the first chamber,
one of the first and second chambers being in connection with the input port,
a
third chamber being in contact with the at least one output port. The motor
also
comprises a compression turbine operating in reverse mode from the
combustion turbine for admitting and compressing an air and fuel mixture and
for providing the compressed air and fuel mixture to the input port of the
combustion turbine. A synchronization shaft is operably connected to each
2064686 1
CA 02780754 2012-06-14
turbine. Torque from at least one of the two rotors is received at the output
shaft.
BRIEF DESCRIPTION OF THE DRAWINGS
[0011] Embodiments of the disclosure will be described by way of
example only with reference to the accompanying drawings, in which:
[0012] Fig. 1 is a perspective view of parts of a turbine according to
an embodiment;
[0013] Figs 2, 3, 4, 5 and 6 show schematic top views of the
turbine of Fig. 1 with rotors positioned at five consecutive
rotation angles;
[0014] Fig. 7 is a partial perspective view of a housing bottom
according to an embodiment;
[0015] Fig. 7a is a cutaway view of a housing bottom according to
an embodiment;
[0016] Fig. 7b is a partial view of the housing bottom of Fig.7,
showing placement of a rotating valve;
[0017] Fig. 8 is a graph of relative torque values as a function of
rotation angles;
[0018] Fig. 9 is a partial perspective view of a rotor according to an
embodiment;
[0019] Fig. 10 is a perspective view of an rotor according to
another embodiment;
[0020] Fig. 11 is a partial perspective view of an rotor according to
yet another embodiment;
[0021] Fig. 12 is a photograph of some components of a turbine
prototype;
[0022] Fig. 13 is a second photograph of components of the turbine
2064686.1
CA 02780754 2012-06-14
6
prototype;
[0023] Fig. 14 is a perspective view showing some parts of a motor
according to an embodiment;
[0024] Fig. 14a is a partial cutaway view of the motor of Fig. 14;
[0025] Fig. 14b is another partial cutaway view of the motor of Fig.
14;
[0026] Fig. 14c is a detailed view of a bottom part of the motor of
Fig. 14;
[0027] Fig. 15 is another perspective view showing additional parts
of the motor of Fig. 14;
[0028] Fig. 15a is yet another perspective view showing additional
parts of the motor of Fig. 14;
[0029] Fig. 16 is a perspective view showing details of the motor of
Fig. 14;
[0030] Fig. 17 is a perspective view showing the complete motor of
Fig. 14; and
[0031] Fig. 18 is a schematic view of an alternate embodiment of a
turbine.
DETAILED DESCRIPTION
[0032] The present disclosure is directed to a turbine that may be
used as a pump, a compressor, as an energy recuperation device for
generating torque, an air engine, a steam turbine, or as a part of a motor. A
basic turbine comprises a housing that encloses two counter-rotating and
cooperating spiral-shaped rotors. Each rotor has a plurality of curved arms,
or
blades, for example four (4) arms. While the rotors are counter-rotating, the
arms of both rotors are curved in a same direction. For example, the arms of a
first rotor and the arms of a second rotor may both be curved in a direction
of
rotation of the first rotor. The rotors rotate within a same plane, within the
2064686 1
CA 02780754 2012-06-14
7
housing. The rotors have a width, or depth that closely matches a distance
between two substantially parallel internal surfaces of the housing. The
internal
surfaces of the housing may be flat or substantially flat in order to maximize
areas of contact between these surfaces and the rotors. The rotors also have
an overall diameter, defined by a circumference covered by a full rotation of
a
tip of the curved arms. An internal perimeter of the housing may be generally
shaped as two partially overlapping circles having a circumference generally
matching the circumference of the rotors.
[0033] Because the width of the rotors closely matches the
distance between the two parallel internal surfaces of the housing, a relation
between the rotors may be characterized as "edging", in the sense that a
balance is attained between a minimal friction between the surfaces and a
minimal gaseous leakage. The tips of the arms of the rotors may thus come in
slightly spaced or barely contacting relation ¨ hereinafter edging contact ¨
with
the internal perimeter of the housing. Edging contact of a tip of a curved arm
may be made with the internal surface of the housing over at least 90 degrees
of rotation. The two rotors may also come in edging contact with each other. A
distance between axes of rotation of the two rotors is such that the tip of an
arm of one rotor comes in contact with the other rotor, in a void between its
own two arms, at some rotation angles.
[0034] In an embodiment, minimal friction is attained between
barely contacting parts of the turbine. In another embodiment, a slight
spacing
is maintained between the various parts of the turbine. Some spacing may
allow minimal leak between, for example, the arms of the rotors and the
parallel interface surfaces of the housing. Turbulence between fixed and
mobile parts minimizes further such leaks. This effect, which is well-known to
those skilled in the art of conventional high-speed turbines, is in fact
applicable
in the turbine of the present disclosure.
[0035] From the following description of various embodiments, the
skilled reader will observe that no strict tolerance of various dimensions of
the
2064686.1
CA 02780754 2012-06-14
8
components of the turbine is required, as some internal leakage is not
detrimental to the operation of the turbine. Additionally, some embodiments
disclosed hereinbelow reveal how leakage may be controlled and how adverse
aerodynamic effects may be circumvented.
[0036] The housing is generally sealed except for at least one input
port and one or more output ports. Multiple chambers, or cavities, are defined
within the housing by the cooperation of the rotors: the chambers have a
volume delimited in one dimension by the two parallel internal surfaces of the
housing and in the other two dimensions by varying combinations comprising
the arms of the rotors and the perimeter of the housing. Because the rotors
are
rotating, the chambers continuously change in size and in shape. As the rotors
rotate, new chambers are continuously created and expand while other
chambers reduce in size and disappear.
[0037] The creation of a new chamber may cause, as it expands, a
negative pressure. When the negative pressure is present at the input port, a
gas ¨ or more generally a fluid, including for example a gas comprising a part
of liquid droplets ¨ may be aspirated into the expanding chamber. Likewise, a
chamber that is reducing in size acquires a higher pressure and may expel gas
through an output port. A chamber that, at a given time, maintains a constant
size may also expel gas through an output port if the chamber has been
pressurized earlier. Hence, if an external mechanical force or torque is
applied
to the turbine and engages the rotors in a rotating motion, the turbine may
act
as a compressor or as a pump.
[0038] A pressurized fluid may alternatively be applied at the input
port. The pressurized fluid forces the expansion of a chamber by rotation of
the
rotors. The pressure of the fluid is reduced as the chamber expands and may
then be expelled at a lower pressure at an output port. Hence, the turbine may
be used to convert the pressure of the fluid applied at the input port into an
output torque. This property of the turbine may be used in an electrical power
plant.
2064686.1
CA 02780754 2012-06-14
9
[0039] Referring to
Fig. 1, there is shown a perspective view of
parts of a turbine according to an embodiment. The turbine 100 comprises a
housing that further comprises a bottom part 110, a top part (not shown)
substantially parallel to the bottom part 110, a perimeter 120 having an
internal
surface 122, two rotors 130 and 140 having axes 138 and 148. The turbine
100 may operate in various positions, and those of ordinary skill in the art
will
appreciate that mentions of a "top" and a "bottom" of the turbine 100 are
relative to the turbine 100 as a whole and are made for convenience of
illustration. In an embodiment, a shape of the top part may mirror the shape
of
the bottom part 110. The rotors are counter-rotating: the rotor 130 may rotate
clockwise around its axis 138 and the rotor 140 may rotate counterclockwise
around its axis 148. The direction of rotation of the rotors could be
reversed,
depending on desired functions and characteristics of the turbine 100. The
rotors have a width W, or depth, corresponding substantially to a distance
between the bottom part 110 and the top part of the housing, allowing for some
tolerance for minimizing or eliminating friction. The exemplary turbine 100
also
comprises at least one input port (not shown, but visible on later figures)
and
one or more output ports. The exemplary turbine 100 comprises a central
output port 150 and two lateral output ports 152, 154. As shown, the output
ports 150-154 are located within the perimeter 120 of the housing. In other
embodiments, diverse numbers of output ports may be located in other parts of
the perimeter 120, in the bottom part 110, in the top part, or in various
placement combinations within the housing. A description of the operation of
the turbine 100 found hereinbelow provides insights on proper locations of the
input port and output port(s). The exemplary turbine 100 as shown further
comprises other parts, such as holes 160 within the perimeter 120 for the
passage of bolts (not shown) for holding the various parts of the housing
together, and apertures 162 adapted for the passage of liquid or gaseous
cooling fluids. Other elements may be present in the turbine 100, such as for
example sealing gaskets, for example o-rings, between the top part, perimeter
and bottom part, valves for opening and closing the input and output ports,
2064686 1
CA 02780754 2012-06-14
passages for coolants within and between the bottom part 110 and the top
part, as is well-known in the art. In an embodiment, the perimeter may be
integral with one of the top or bottom part of the housing. 0-rings and
grooves
may be used for sealing between fixes components, thereby reducing the
effect of machining tolerances upon components assembly. A volume adapted
to receive a cooling fluid may be, in the case of a vapor turbine, filled with
an
isolating material for preventing heat losses. The same space may also be
used for capturing vapor losses or condensation of the vapor. Leaks may thus
be recuperated from an outlet located near the bottom of the turbine.
[0040] The housing,
comprising the top part, the bottom part 110
and the perimeter 120, may be generally sealed, apart from the various input
and output ports. The rotors 130 and 140 are held in place at their axes 138
and 148 of rotation by rotating shafts (not shown), which prevent lateral
movement of the rotors 130 and 140 but allow rotational movement. In an
embodiment, each of the rotors 130 or 140 and its respective axe 138 or 148
may be machined as one single piece, providing higher resistance to
mechanical forces, higher reliability, limiting mechanical movement between
the rotors and their axes, and further allowing higher pressures within the
turbine 100. The rotors 130 and 140 do not significantly move perpendicularly
to the axes because their width W is more or less equal, within some
mechanical tolerance to the distance between the top and bottom parts.
External components such as bearings (not shown) connected to the rotating
shafts may further be used to maintain the rotors 130, 140 in place. In their
rotation, the rotors 130, 140 may come in edging contact with each other, with
the top part and the bottom part 110, and with the internal surface 122 of the
perimeter 120. In contrast with traditional engines, mechanical tolerances
between the rotors 130, 140 and the internal surface 122 may be relatively
relaxed: various "spaces", called "chambers" formed between the rotors
themselves or between the rotors and the housing may withstand a modest
level of leakage without adverse effect on the operation and performance of
the turbine 100. As illustrated on Fig. 1, the width W, or depth, of the
rotors
2064686 1
CA 02780754 2012-06-14
11
130, 140 and the surface 122 are perpendicular to the top part and bottom part
110 of the housing. In an embodiment, a shape of the rotors 130, 140 may
comprise some axial twisting along their width W. Variations from the shape of
the rotors 130, 140 as shown on Fig. 1 will readily come to mind to those of
ordinary skill in the art.
[0041] Referring now
concurrently to Figs 2, 3, 4, 5 and 6 are
shown schematic top views of the turbine of Fig. 1 with rotors positioned at
five
consecutive rotation angles. Figs 2-6 collectively illustrate a cycle, in
which
chambers are created, expand and eventually reduce in size and disappear.
The turbine 100 is reproduced in Figs 2-6 in schematic form. As shown, the
rotor 130 rotates clockwise and the rotor 140 rotates counter-clockwise. An
arbitrary reference angle Y is shown near the axis 138, set to a nominal 0-
degree (horizontal) value in Fig. 2. Arms, also called blades, of the rotors
are
identified by use of numerals 131-134 and 141-144. Various chambers are
created, expand, move and then disappear as a result of a cooperation of the
rotors 130 and 140 as they rotate. Considering Fig. 2, a chamber A is created
between an arm 144 and a void of the rotor 130, between arms 131 and 134.
Other chambers D, Cl, C2, 133 and 132 have been created earlier as the rotors
130 and 140 rotate. While chambers Cl and C2 may appear nearly identical
on Figs 2-5, it should be understood that chamber Cl and chamber C2 may
differ somewhat. Turning then to Fig. 3, which shows the turbine having
undergone about 22 degrees of rotation of its rotors compared to Fig. 2 (angle
Y is about equal to 22 degrees), the chamber A has increased in volume. On
Fig. 3, the chambers 133 and 132 of Fig. 2 have been combined and split again
into chambers 134 and 135. Following another about 28 degrees of rotation, the
chamber A is now much wider as shown on Fig. 4 (angle Y is about equal to
50 degrees). At the time shown in Fig. 4, the chamber A is no longer delimited
solely by arms of the rotors, but also by the perimeter 120. At the same time,
the chamber 135 has reduced in size while the chamber 134 is now split into
chambers 136 and 137. Adding some more rotation at Fig. 5 (angle Y is about
2064686.1
CA 02780754 2012-06-14
12
equal to 90 degrees), the chamber A is nearing is maximum volume.
Chambers Cl and 66 have merged into chamber C3. Then at Fig. 6 (angle Y is
about equal to 130 degrees), the chamber A has been split into two chambers
Al and A2 while chambers C2 and C3 have combined and split again into
chambers C4 and C5. Returning to Fig. 5, which shows 90 degrees of rotation
compared to Fig. 2, a new chamber B is being created. Chamber B has
increased volume in Fig. 6, which shows 90 degrees of rotation compared to
Fig. 3.
[0042] It may thus be observed that a new chamber is created from
the cooperation of the rotors 130, 140 at every 90 degrees of rotation, or
four
times per revolution of the rotors. Over a complete revolution of the rotors,
chambers C, D, A and B have been created near the axis 138 of the rotor 130
and have gone through phases of expansion, splitting into distinct chambers
temporarily having a constant volume as for example chambers Cl and C2 of
Fig. 2, the chambers having been combined and having their sizes reduced
towards the end of their cycles.
[0043] Returning to Fig. 2, at the time when chamber A is created
and starts expanding, an earlier created chamber D, created at a time when
the rotors 130 and 140 had 90 less degrees of rotation, is nearing the end of
its own expansion phase. In Figs 3-6, chamber D has been split into two
chambers D1 and D2. As the rotors rotate between the rotation angles shown
on Figs 3-6, volumes of the chambers D1 and D2 remain essentially constant.
[0044] On Fig. 3, positions of the arms 141 and 144, spanning over
the chamber D2, exemplify a minimum 90-degree range of rotation of the
rotors over which the tip of the arms are in slightly spaced or barely
contacting
relation with the perimeter 120 of the housing. As shown, as the rotor 140
continues rotating counterclockwise, the tip of the arm 141 remains
substantially in contact with the perimeter 120 over more than 180 degrees.
However, in an embodiment, the perimeter may be altered such that contact is
lost between the tip of the arm 141 and the perimeter beyond the position
2064686 1
CA 02780754 2012-06-14
13
shown on Fig. 3 while preserving the functionality of the turbine 100.
[0045] Eventually, as the rotors continue turning, split chambers
such as D1 and D2 join again. For example, chambers C1 and C2 that have
constant volumes in Figs 2-4 start joining with remnants of an earlier chamber
113 at Fig. 5. At Fig. 6, a combination of chambers Cl, C2 and 133 are split
again in chambers C3 and C4.
[0046] As expressed hereinabove, the housing of the turbine 100 is
sealed except for an input port and one or more output ports. An input port
may be located in the bottom of the housing, as shown on Fig. 7, which is a
perspective view of a housing bottom according to an embodiment. The
housing bottom 110 comprises an input port 112. Alternatively, the turbine 100
may comprise more than one input port and the one or more input ports may
be located in the bottom of the housing, in the perimeter of the housing, or
in
the top of the housing. A plurality of input ports may be located in a
combination of the bottom, top and perimeter of the housing. Comparing Figs 2
and 7, the input port 112 may be located near the axis 138, at area location
where the chamber A is initially created and starts to expand. A cooling fluid
may circulate in canal 704 within the housing bottom, shown on Fig. 7a, for
capturing the absorbed heat. Fig. 7a also shows an array of holes 702, which
promote heat absorption within the housing.
[0047] The rotors 130 and 140 may be synchronized, for example
using synchronizing gears (not shown) located outside of the housing, and
connected to axes 138 and 148 via the rotating shafts. Synchronization helps
in minimizing friction between the rotors 130, 140 and in maximizing
mechanical torque upon the rotating shafts.
[0048] In an embodiment, as a chamber expands due to the
rotation of the cooperating rotors, a negative relative gas or fluid pressure
is
created in the expanding chamber. In another embodiment, a positive gas
pressure applied in a chamber forces the chamber to expand, creating a force
applied to the blades, or arms, of the rotors, creating a torque around the
axes
2064686.1
CA 02780754 2012-06-14
14
of the rotors. It will therefore be apparent to those of ordinary skill in the
art that
the turbine 100 may be used to convert energy present in a pressurized gas,
such as for example water vapor from a boiler in a thermal or nuclear power
plant, converting an energy from the pressurized gas into a mechanical torque
at the axes of the rotors, usable for example for driving an electric
generator.
[0049] An embodiment of a torque generator based on the turbine
100 will now be described. The torque generator operates according to the
cycle described in relation to Figs. 2-6. At a time where the rotational
position
of the rotors corresponds to Fig. 2, the input port 112 is open and provides
pressurized gas to the chamber A. Pressure in the chamber A pushes on the
arm 144, forcing rotation. As rotation increases, the pressure in chamber A
further pushes on the arm 131. This pressure on the arms of the rotors creates
a torque at the axes 138 and 148. As the rotors rotate, the chamber B starts
being created over the location of the input port 112 and the cycle continues.
Some of the chambers have stopped expanding, for example chambers Cl
and C2 on Figs 2-4. As such, any pressure within those chambers does not
create any torque on the rotors 130 and 140. This contrasts with expanding
chambers such as chamber A in Figs 2-5, wherein the expansion implies
pressure and torque on the arms of the rotors. Some of the chambers may
eventually start reducing in size, thereby creating compression and creating a
counteracting force on the rotors, for example chamber 135 in Figs 3-4. To
circumvent this effect, one or more output ports such as 150, 152 and 154,
shown on Fig. 1 are used in various combinations to release pressure from
chambers that are no longer expanding.
[0050] In an embodiment, because the pressure within those
chambers that are neither expanding nor compressing does not generate any
torque, a part of the energy contained within this pressure may be
recuperated.
Gas from the output ports 150, 152 may be fed into a secondary turbine that
also generates some torque. Alternatively, some of the gas from the output
ports 150, 152 may be recirculated throughout cooling passages within the
2064686.1
CA 02780754 2012-06-14
housing, thereby reducing the need for other cooling means. Furthermore,
when the gas absorbs some additional heat by passing in the cooling
passages, its volume expands, increasing an amount of residual enthalpy of
the gas, whereby energy can be harnessed by the secondary turbine. This
reduces any amount of energy required to cool the turbine 100 while also
increasing a net torque output. Those of ordinary skills in the art will
appreciate
that heat management within the turbine 100 may depend on its intended use.
For example, when the turbine 100 is used for generating torque from hot
water vapor, heat losses from the turbine 100 may be minimized so that a
maximum possible amount of energy is extracted from the vapor.
[0051] In an exemplary embodiment of a torque generator, the
turbine 100 is not negatively impacted if a gas entering the input port 112 is
contaminated with some liquid. As an example, "unclean" vapor containing a
significant amount of water droplets may be processed by the turbine 100
without significant adverse effect on the rotors 130, 140. The eventual
presence of small water droplets in vapor processed by the turbine 100 may at
once provide a level of air tightness between the rotors and the housing
while,
as rotational speeds of the turbine are relatively low, remaining harmless to
the
rotors, Some treatment of fixed and mobile components of the turbine 100 may
further counteract any erosion effects from such water droplets.
[0052] An embodiment of a compressor based on the turbine 100
will now be described. In this embodiment, the turbine 100 operates in a
reverse mode compared to the cycle described in relation to Figs. 2-6. The
direction of rotation of the rotors 130 and 140 is reversed and, the output
ports
150 and/or 152 and 154 become inputs through which a low pressure gas or
fluid enters the turbine 100. Torque is applied to the axes 138 and 148,
creating compression of the chambers that eventually meet the input port 112
or any other input port, which become outputs through which pressurized gas
is expelled. An understanding of the compressor embodiment of the turbine
100 may be had by considering Figs 2-6 in reverse order, wherein the rotor
2064686.1
CA 02780754 2012-06-14
16
130 rotates counterclockwise while the rotor 140 rotates clockwise. It will be
understood that this also implies that the chamber B is created before chamber
A, and that these chambers are contracting, rather than expanding, in a
sequence going from Fig. 6 down to Fig. 2. In this compressor, various gas
pressures are present in various chambers. Any gas leak from a higher
pressure chamber is recuperated in a lower pressure chamber, the leaked gas
being compressed again. It may thus be observed that leaks within the
compressor bring little adverse effects or losses.
[0053] In various embodiments of a torque generator or
compressor based on the turbine 100, valves such as alternating valves or
rotating valves may be used to control opening of the input port and of the
output ports. Fig. 7b shows a rotating valve 706, which is inserted within the
bottom 110. The valve may be attached to the rotor 134, optionally allowing a
small amount of relative motion therebetween. Rotation of the valve 706 opens
and closes the input port 112. Grooves (not shown) may be added to the
edges of the valve 706, generating a Bernouilli effect for limiting losses
between the bottom 110 and the valve 706.
[0054] Instead of a gas, an uncompressible liquid, for example
water, may flow through the turbine 100. Though the liquid does not compress,
its pressure on the rotors 130, 140 still generates torque. As such, the
turbine
100 may be used to generate torque from a flow of water, for example, in a
hydroelectric power plant. Likewise, the turbine 100 may be used for pumping
a liquid, when operating in reverse mode compared to the cycle described in
relation to Figs. 2-6.
[0055] Referring now to Fig. 8, which is a graph of relative torque
values as a function of rotation angles, a performance of the turbine 100 is
compared to that of a single-cylinder alternating piston motor. For comparison
purposes, it is assumed that the turbine 100 is used as a torque generator
rather than as a compressor. Full (100%) mechanical efficiency without any
mechanical loss is also assumed for the piston motor and for the turbine 100.
2064686.1
CA 02780754 2012-06-14
17
In the case of the turbine 100, it is assumed that a valve closes the input
port
112 when chamber A is in the position as shown on Figure 2, thereby
maintaining a constant pressure within the turbine 100. Torque values shown
on the vertical axis of graph 800 are relative in order to allow comparison of
any size turbine with an alternating piston motor of any size. The rotation
angle
of the horizontal axis represents, for the alternating piston motor, a
crankshaft
angle wherein the zero degree position corresponds to a point where the
piston is at the top of the cylinder, generally called "top dead center",
closely
following an ignition time of a spark plug that occurs a few degrees before
that
point. For the turbine 100, the zero degree position corresponds to the
creation
of a new expanding chamber in the turbine 100, for example a few degrees
prior to the rotor positions on Fig. 2.
[0056] Curve 810 represents a torque provided by a piston of a
conventional engine on its crankshaft. At a zero degree point, the piston is
at
the top of its course within a cylinder. Because of its position, there is no
lever
effect from the piston to the crankshaft. Even though a compression within the
cylinder is at its maximum and even though ignition occurs shortly before that
point, no torque is provided by the piston due to the lack of leverage. The
torque provided by the piston is at its maximum when the crankshaft has
rotated by 90 degrees. Of course, the piston of a conventional four-stroke
motor produces power only once per every two revolutions. Hence the peak
torque obtained at 90 degrees is followed by inefficient periods during the
next
three strokes following the combustion cycle. The piston actually absorbs
some torque during the exhaust, admission and compression strokes. As a
result, an overall torque curve from the piston is somewhat sinusoidal,
including periods during which the net torque output is negative.
[0057] The turbine 100 creates chambers that generate torque
over about 145 degrees of rotation, new chambers being generated four (4)
times per revolution, which implies that periods of time in which two
successive
chambers generate torque may overlap, the torque from the two chambers
2064686 1
CA 02780754 2012-06-14
18
being combined at the axes. Referring again to Fig. 2, Chamber A has just
been created; the 0-degree reference angle Y of Fig. 2 thus represents a few
degrees of rotation after a true 0-degree angle. The true 0-degree angle
represents a point where a new chamber is starting to be generated, initially
without any volume. Fig. 6 shows a point when chamber A has just been split
into chambers Al and A2, which no longer generate any torque, and thus
represent a few degrees after a true 145-degree point, this point being
defined
as where a chamber is no longer expanding, being split into two chambers.
Considering again Fig. 8, curve 820 shows a torque produced by the turbine
100 from a true 0-degree angle to a true 145-degree. It may be observed on
curve 820 that the turbine 100 provides a peak torque at about 60 degrees of
rotation, earlier than a conventional piston that peaks around 90 degrees of
rotation. Torque is produced until a chamber stops expanding, at about 145
degrees of rotation. Curves 822 and 824 represent torque produced by the
turbine 110 when pressurized gas or fluid is input into the turbine sometime
after the start of expansion of a chamber. In those cases, it can be seen that
the torque appears as soon as the gas enters the chamber, peaks sooner and
ends sooner as well. In curves 822 and 824, the rotation angles are relative
angles, relative to a time when gas input takes place. Gas may enter the
expanding chamber at a true rotation angle ranging from zero to about 50
degrees of rotation.
[0058] Of course, while the torque is still very significant at 90
degrees of rotation, another cycle is already beginning within the turbine
100,
as a new chamber is created with every quarter of a revolution. This compares
favorably with a piston in a four-stroke engine, igniting once ever 720
degrees
of rotation. As a result, an additional curve such as curve 820, 822 or 824 is
initiated and added at every 90 degrees of rotation of the turbine 100, and
the
net output torque of the turbine 100 is relatively constant and flat.
[0059] As mentioned hereinabove, mechanical tolerances between
the rotors 130, 140 themselves as well as between then rotors various
2064686 1
CA 02780754 2012-06-14
19
surfaces of the housing 110 may be relatively relaxed. A modest amount of
gaseous or fluidic leakage between the various chambers within the turbine
100 is not detrimental to its performance. In fact, any leakage occurs from
high
pressure chambers to lower pressure chambers, creating at least some
modest level of torque in those constant volume chambers, minimizing net
losses. If gases exiting the turbine 100 through the output ports 150, 152,
154
are fed to a secondary turbine, net losses are minimized even further. In
addition, Bernoulli effects may occur within the turbine 100 at high rotating
speeds. In order to circumvent these effects, optional embodiments of the
rotors such as shown on Figs. 9-11 may be used.
[0060] Fig. 9 is a partial perspective view of a rotor according to an
embodiment. The rotor 140 is modified by use of various indentations 900-908
near a tip of the arms of the rotor. Fig. 10 is a perspective view of a rotor
according to another embodiment. In this case, the rotor 140 is modified by
use of different indentations 1000-1006 in mid-sections of the arms of the
rotor.
These geometries using tapered edges on the arms of the rotors facilitate
admission of a fluid into the chambers and minimize turbulence and adverse
aerodynamic effects. Though shown as sharp edges on Figures 9 and 10, the
indentations 900-908 and 1000-1006 may actually form smooth curved
surfaces, thereby benefiting from a Bernouilli effect for creating a
restriction to
flows between fixed and mobile surfaces. It may be observed that the use of
indentations 900-908 and 1000-1006 render unnecessary the presence of
joints, such as piston rings of conventional engines. Regardless, any leak
from
one chamber within the turbine 100 only allows gas to flow into a lower
pressure adjacent chamber. This gas, added to the lower pressure chamber,
generates some torque on the rotors 130, 140. As a result, leaks cause no
significant loss of efficiency and, because no joint is present, friction
losses are
also reduced.
[0061] Indentations 900-908 and 1000-1006 also allow avoiding
mechanical impacts between the rotors 130 and 140 or between the rotors
2064686.1
CA 02780754 2012-06-14
themselves and other components of the turbine 100. As shapes of some
turbine components may be plastically altered under high heat, high pressure
and/or high speed conditions, these indentations may prevent collisions
between moving parts and between moving and fixed parts. Some attenuation
in the geometry of the rotors 130 and 140, creating small gaps between tips of
their arms 131-134 and 141-144 and other fixed or mobile surfaces, may
further reduce any risk of mechanical shocks between the rotors.
[0062] Fig. 11 is a partial perspective view of a rotor according to
yet another embodiment. In that embodiment, ridges, grooves or similar
patterns 1100 are present on an upper surface 1102 and on a lower surface
(not shown) of the rotor 140. The pattern 1100 minimizes any gaseous or fluid
leakage between the rotor 140 and the top and bottom of the housing while
minimizing friction. In an embodiment, ridges, grooves or similar patterns may
alternatively or additionally be present on the upper surface 1102 and on the
lower surface of the rotor 140, with similar effects.
[0063] Fig. 12 is a photograph of some components of a turbine
prototype. In this embodiment, a top surface 1212 and a perimeter 1218 of the
housing are integrated in a same component 1210. The top surface 1212 and
the perimeter 1218 come in edging contact with the rotors. Also visible are
two
axes 1214 and 1216, input ports 1215a, 1215b, and 1215c, and output ports
1219a, 1219b and 1219c, all input ports and output ports being located within
the top surface 1212. A bottom part 1220 has a surface (underneath, not
shown) that comes in edging contact with rotors. The bottom part 1220 as
shown comprises two meshed synchronizing gears 1222, 1224 that connect to
the rotors through shafts (not shown). Fig. 12 also shows a cover 1230 for
protecting the meshed synchronizing gears 1222, 1224. On the synchronizing
gear 1224, non-circular orifices 1225 are provided in order to allow slight
angular adjustment of a rotor connected thereto.
[0064] Fig. 13 is a second photograph of components of the turbine
prototype. The cover 1230 is shown, as well as a bottom surface 1221 of the
2064686 1
CA 02780754 2012-06-14
21
bottom part 1220.
[0065] Owing to the capabilities of the turbine 100 to compress a
gas when a torque is applied and to create a torque when gas pressure is
applied, the turbine 100 may, in an embodiment, be used as a building block
for producing a motor. The motor acts as a four-cycle motor in which
admission and compression cycles are made in a first turbine while
combustion and exhaust cycles are continuously and concurrently made in a
second turbine, as in the case of a conventional gas turbine. Fig. 14 is a
perspective view showing some parts of a motor according to an embodiment.
An exemplary motor 1400 may use various types of combustible fuels to
generate power. The motor 1400 comprises two distinct turbines working in
opposite modes, a compression turbine 1410 and a combustion turbine 1460.
The compression turbine 1410 forms a "cold side" of the motor 1440, operating
in reverse mode, while the combustion turbine 1460 forms a "hot side",
operating in same mode as described in relation to Figs. 2-6. Though similar,
the compression turbine 1410 and the combustion turbine 1460 may differ in
terms of size, volumes, materials used for their manufacturing, cooling or
lubricating means, and the like. The compression turbine 1410 compresses air,
or an air and fuel mixture, and provides the compressed gas to the combustion
turbine 1460. Fuel may be mixed with air at various stages. A fuel supply
system may comprise a carburetor or an injector adding fuel to air for input
in
the compression turbine 1410, an injector, supplying fuel directly in the
combustion turbine 1460, or an injector supplying fuel in an intermediate
conduit (not shown) between the two turbines.
[0066] The compression turbine 1410 has a top part 1420 while the
combustion turbine 1460 has a bottom part 1470. Perimeters of the two
turbines 1410, 1460 are not shown in order to show rotors 1432, 1434 of the
compression turbine 1410 and rotors 1482, 1484 of the combustion turbine.
Though distinct, the two turbines 1410, 1460 may optionally share some
components. For example, a plate 1458 is at once a bottom part of a housing
2064686.1
CA 02780754 2012-06-14
22
for the compression turbine 1410 and a top part of a housing for the
combustion turbine 1460. The plate 1458 may comprise output ports (not
shown) for the compression turbine 1410, internally connected to one or more
input ports (not shown) for the combustion turbine 1460. As such, the plate
1458 may be a transfer plate for transferring the output of the compression
turbine 1410 directly into the input of the combustion turbine 1460.
[0067] In an embodiment an output port on the compression
turbine 1410 is within the plate 1458 and the output port communicates
directly
therethrough with an input port of the combustion turbine 1460, allowing the
compressed air or air and fuel mixture to enter the combustion turbine 1460.
In
this case, the combustion turbine 1460 comprises ignition means, such as a
spark plug (not shown), and ignition of the air fuel mixture takes place
within
the combustion turbine 1460. In another embodiment, one or more output ports
of the compression turbine 1410 are connected with one or more input ports of
the combustion turbine 1460 through an intermediate conduit, in which case
ignition may take place either within the intermediate conduit or within the
combustion turbine 1460. Regardless, combustion generates high pressure
within chambers of the combustion turbine 1460, this high pressure acting on
rotors to generate a torque.
[0068] As shown, the compression turbine 1410 comprises a shaft
1416 connected to the rotor 1434, a second shaft connected to the rotor 1432
being omitted from the figure. Alternatively, shafts 1456 and 1454 may extend
through the axes of rotors within the two turbines 1410 and 1460, substituting
for the shaft 1416 and acting as a shaft for the rotor 1432. The combustion
turbine 1460 is connected by use of the shafts 1456 and 1454 to two counter-
rotating synchronizing wheels 1462 and 1464. The synchronizing wheels 1462
and 1464 as shown are frictionally connected. The synchronizing wheel 1464
transmits output torque from the shaft 1454 to the synchronizing wheel 1462,
which in turn transmits a sum of this torque and of a torque from the shaft
1456
to a pick-up wheel 1466. The pick-up wheel is mounted on an output shaft
2064686 1
CA 02780754 2012-06-14
23
1468, from which a complete output torque from the motor 1400 may be used.
A fraction of the output torque from the motor 1400 may be used to drive the
compression turbine 1410, a remainder of the output torque forming a net
output of the motor 1400. The output shaft 1468 may extend towards a transfer
wheel 1412. The transfer wheel 1412 is operably connected to an input wheel
1414, further connected to the shaft 1416 and, therethrough, to the rotor
1434.
Of course, the rotor 1432 is also connected to a shaft (not shown), itself
connected to another input wheel (not shown) driven by the input wheel 1414.
While synchronizing wheels 1462 and 1464 act to synchronize the rotors 1482
and 1484 within the combustion turbine 1460, the combustion turbine 1460 is
further synchronized with the compression turbine 1410 via shafts 1468 and
1416 or, alternatively via shafts 1454 or 1456, which may all act as
synchronizing shafts. Phase adjustment of the compression turbine 1410 and
the combustion turbine 1460 may be obtained by adjusting the input wheel
1414 and the input wheel connected to the rotor 1432.
[0069] In the
exemplary embodiment of Fig. 14, the rotors 1432
and 1482 rotate in a same direction, opposite of the rotation of the rotors
1434
and 1484. Owing to the compression function of the compression turbine 1410,
it operates in reverse mode compared to the basic turbine function described
in relation to Figs. 2-6. In contrast, owing to its torque generating
function, the
combustion turbine 1460, operates directly according to the basic function of
Figs 2-6. It may therefore be observed that the rotors 1432, 1434 of the
compression turbine 1410 have arms that are curved in an opposite direction
compared to those of the rotors 1482, 1484 in the combustion turbine 1460.
When the output port on the compression turbine 1410 is within the plate 1458,
communicating directly therethrough with an input port of the combustion
turbine 1460, both turbines rotate synchronously. When output ports of the
compression turbine 1410 communicated with input ports of the combustion
turbine via an intermediate conduit, the two turbines may operate at distinct
speeds. For example, in an embodiment, the compression turbine 1410 may
be physically smaller and rotate at a higher speed, thereby providing ample
air
2064686.1
CA 02780754 2012-06-14
24
or air and fuel supply to the combustion turbine 1460.
[0070] Fig. 14a is a partial cutaway view of the motor of Fig. 14.
The figure shows the shafts 1454, 1456, 1468 and 1416 of Fig. 14, and a shaft
1417 connected to the rotor 1432.
[0071] Fig. 14b is another partial cutaway view of the motor of Fig.
14. One of the shafts, for example the shaft 1456 is shown with the
synchronizing wheel 1462. Also shown are the bottom part 1470 and the
common plate 1458. A bearing 1490 maintains the shaft 1456 in place.
Because there may be grease or oil (not shown) surrounding the bearing 1490
and because there are gases between the common plate 1458 and the bottom
part 1470, where the rotor 1484 (not shown on Fig. 14b) is located, o-rings or
similar sealing means may be placed within grooves 1492, 1494, and a canal
1496 may allow any condensation bypassing the o-rings to be guided outside
the motor 1400. This prevents contamination of the bearing oil or grease.
[0072] Fig. 14c is a detailed view of a bottom part of the motor of
Fig. 14. The bottom part 1470 may comprise, on its back (opposite from the
rotors 1482, 1484, a plurality of cooling fins 1471 for facilitating heat
transfer
between the combustion turbine 1460 and oil (not shown) circulating around
the bottom part 1470.
[0073] Fig. 15 is another perspective view showing additional parts
of the motor of Fig. 14. The motor 1400 further comprises a starter motor 1510
connected to a gear box 1512, which may comprise a one-way bearing, the
gear box 1512 being connected to the input wheel 1414. The input wheel 1414
further acts to synchronize rotors of the compression turbine 1410 by use of a
frictional contact to a second input wheel 1520. On Fig. 15a, covers 1530,
1532 are added on top of the various wheels 1412, 1414, 1520, 1462, 1464
and 1466. Oil may circulate between the covers 1530, 1532, and the top and
bottom parts 1420, 1470, respectively. Fig. 15a also shows carburetors 1540,
1542, a spark plug 1620, and a dynamo 1544.
2064686 1
CA 02780754 2012-06-14
[0074] Fig. 16 is a perspective view showing details of the motor
of
Fig. 14. A perimeter 1610 is attached to the bottom part 1470 of the
combustion turbine 1460. Two distinct spark plugs 1620, 1622 are shown,
though in an embodiment, a single spark plug 1620 or 1622 may be used. The
spark plug 1620 is affixed to the perimeter 1610 and its electrode (not shown)
may provide a spark within an expanding chamber of the combustion turbine
1660, igniting a compressed air and fuel mixture positioned for example as the
chamber A of Fig. 4. The spark plug 1622 is affixed to the bottom part 1470
and may provide a spark within another expanding chamber of the combustion
turbine 1460, igniting the compressed air and fuel mixture positioned for
example as the chamber A of Fig. 3. Of course, various placements of the
spark plugs and various angular rotations of the rotors of the combustion
turbine 1460 may be used depending on diverse factors such as a type of fuel,
a ratio of fuel per volume of air, a rotational speed of the motor, a
compression
ratio, and like parameters. As in the case of traditional engines, ignition
timing
may vary with various factors such as a revolution speed of the motor 1400.
Additional spark plugs (not shown) may also be placed within conduits or
spaces used for recuperation of pressurized gases, enabling a more complete
combustion.
[0075] It may be observed that ignition may occur within the
combustion turbine 1460 four times per rotation, as a new chamber is created
upon every 90 degrees of rotation of the rotors. Alternatively, ignition may
occur at similar rates, or continuously, within an intermediate conduit
between
the compression turbine 1410 and the combustion turbine 1460. In either case,
combustion pressure within the combustion turbine 1460 is consistently
= present. This compares to one ignition with every two revolutions within
a
traditional four-stroke cylinder. It may also be observed that, within the
combustion chamber 1460, pressure within a chamber consistently generates
torque, owing to the geometry of the rotors. As a result, a serious problem of
traditional combustion engines, in which maximum pressure at top-dead center
coincides with no torque output, does not occur. The motor 1400 thus operates
2064686.1
CA 02780754 2012-06-14
26
more efficiently, generates a smoother torque output, generates less heat, and
produces significantly less nitrous oxide (N0x).
[0076] Fig. 17 is a perspective view showing the complete motor of
Fig. 14, cooling means being omitted. Those skilled in the art will understand
that the motor could be cooled by one or several types of cooling means:
water-cooled, oil-cooled, re-circulated coolant, chiller, heat exchanger, air
cooling with blades, etc. The motor 1400 has passages 1710, 1720 for oil
circulation between the two turbines, ensuring proper heat transfer and
ensuring proper lubrication of the various moving components external to the
turbines. In an embodiment, oil circulation may alternatively take place
through
orifices within the plate 1458. The combustion side has three output ports
(not
shown) connected to exhaust pipes 1730, 1732, 1734. In an embodiment, not
all three output ports and exhaust pipes may be present. Covers 1740 and
1742 protect the various wheels 1462, 1464, 1466, 1412, 1414 and 1520,
thereby completing the motor.
[0077] Of course, variations from the basic structure of the motor of
Figs 14-17 could be considered. In an embodiment, two turbines may be
separated and not share common components such as the common shafts
1456 and 1460 or the common plate 1458. Alternatively, one of the shafts
1456 or 1454 may act as a synchronizing shaft and as an output shaft, thereby
substituting for at least some of the functions of the shaft 1468. In another
embodiment, the synchronizing wheels 1462, the pick-up wheel 1464, the
transfer wheel 1412, the input wheel 1414 and second input wheel 1520 may
be meshed gears, similar to gears 1222, 1224 shown on Fig. 12. Further, sizes
of the rotors in the two turbines 1410 and 1460 may differ. For example,
rotors
that are larger in diameter or in width (or depth) may be used in the
compression turbine 1410. In an embodiment using distinct shafts in the axes
of the rotors for the two turbines, distinct rotation speeds of the turbines
may
be attained. Using a larger compression turbine 1410 or using a higher
rotation
speed in the compression turbine 1410 provides more of the compressed air
2064686.1
CA 02780754 2012-06-14
27
and fuel mixture to the combustion turbine 1460. This supercharges the motor
1400, using much simpler means compared to traditional turbochargers or
superchargers used with alternating piston engines. In a variation, a larger
combustion turbine 1460 may extract more energy from combustion and leave
less residual pressure in exhaust gases. Of course, building a motor using the
turbine 100 as a basic building block is not limited to using two turbines, as
various numbers of compression turbines could be used with various numbers
of combustion turbines, in various combinations. For example, an additional
turbine may be connected to the output ports of the combustion turbine in
order to recuperate parts of its residual heat and pressure.
[0078] The motor 1400 may operate with ordinary gas, methanol,
ethanol, diesel fuel, and the like, some adaptations being made to adapt to a
chosen fuel type. As is well-known to those of ordinary skill in the art, in
the
case where diesel fuel is used, fuel pressure, compression levels, ignition
means, electronic control means, and the like differ from the case where
ordinary gas is used.
[0079] Fig. 18 is a schematic view of an alternate embodiment of a
turbine. A turbine 1800 comprises four distinct rotors 1810, 1812, 1814 and
1816 located in a same plane within a perimeter 1820, the four rotors having a
same depth and a same diameter. The central rotor 1810 may rotate clockwise
while the peripheral rotors 1812-1816 may rotate counter-clockwise. A
relationship within a pair comprising the rotor 1810 at the center of the
turbine
1800 and any of the surrounding rotors is similar to that of the pair of
rotors
130, 140 of Figs 1-6, except that a chamber created between arms of two
rotors is eventually confined in part by a third rotor, after some level of
expansion. While a behavior of the various chambers is more complex than in
the case of the turbine 100, the turbine 1800 operates in a similar manner.
Input ports (not shown) may be present in a top part (not shown) or in a
bottom
part (not shown) of the turbine 1800, near an axis of rotation of the central
rotor
1810, where new chambers are created by the rotation of the rotors. Output
2064686.1
CA 02780754 2012-06-14
28
ports (not shown) may be present in the top part, bottom part, or in the
perimeter 1820, for examples in areas such as 1822 or 1824 where chambers
are neither contracting nor expanding. While Fig. 18 shows an embodiment
having four rotors, another embodiment could comprise three rotors,
comprising one central rotor and two diametrically opposed peripheral rotors.
A
number of rotors surrounding the central rotor guides their positioning around
a
perimeter of the turbine. A torque output from a multi-rotor turbine 1800 is
even
more constant when compared to that of a conventional piston engine because
of a phase difference between the various chambers being created around the
central rotor.
[0080] Those of ordinary skill in the art will realize that the
description of the turbine and of the motor are illustrative only and are not
intended to be in any way limiting. Other embodiments will readily suggest
themselves to such skilled persons having the benefit of this disclosure.
Furthermore, the disclosed turbines and motors can be customized to offer
valuable solutions to existing needs and problems related to the manufacturing
costs and lack of efficiency of current compressors, turbines, pumps for
incompressible fluids, and motors.
[0081] In accordance with this disclosure, the turbine components
described herein may be implemented using various materials such as diverse
metals and alloys, plastic, polymers, ceramics, and combinations thereof.
Notably, a rotor and a rotating valve attached thereto may be made using
distinct materials or distinct surface treatment. Selection of materials used
for
manufacturing the various components of the turbine would be based on
considerations such as operating pressure, operating speed, operating
temperature, nature of the fluids within the turbine, expected durability of
the
turbine, cost considerations and similar considerations.
[0082] In the interest of clarity, not all of the routine features of
the
implementations of turbines and motors are shown and described. It will, of
course, be appreciated that in the development of any such actual
2064686.1
CA 02780754 2012-06-14
29
implementation of the turbine, numerous implementation-specific decisions
must be made in order to achieve the developer's specific goals, such as
compliance with application-, system- and business-related constraints, and
that these specific goals will vary from one implementation to another and
from
one developer to another. Moreover, it will be appreciated that a development
effort might be complex and time-consuming, but would nevertheless be a
routine undertaking of engineering for those of ordinary skill in the field of
energy conversion having the benefit of this disclosure.
[0083] Although the
present disclosure has been described
hereinabove by way of non-restrictive illustrative embodiments thereof, these
embodiments can be modified at will within the scope of the appended claims
without departing from the spirit and nature of the present disclosure.
2064686.1
