HYDROGEN TURBINE

TURBINE A HYDROGENE

English Abstract

The invention relates to a gas turbine for the efficient generation of power in anticipation of the emerging "hydrogen society". It solves the technical problem of converting hydrogen or another fuel gas into rotary power most directly. The solution presented is a high velocity gas jet turbine, a compact and light weight power plant. Hydrogen and air are pumped through a multiducted rotor (A) via a multiducted stator (B). Combustion occurs inside the rotor which drives itself with peripheral jets (13) and rotates an extending power shaft (15). The principal uses of this invention are the powering of electrical generators and other devices requiring rotary power, including watercraft, land vehicles and aircraft.

French Abstract

L'invention concerne une turbine à gaz permettant la génération efficace de puissance afin d'anticiper l'émergence de la « société de l'hydrogène ». Elle résout le problème technique de la conversion de l'hydrogène ou d'un autre gaz combustible en puissance rotative le plus directement. La solution présentée est une turbine à jet de gaz à grande vitesse, une centrale compact et légère. L'hydrogène et l'air sont pompés à travers un rotor multicaréné (A) par l'intermédiaire d'un stator multicaréné (B). La combustion se fait à l'intérieur du rotor, qui s'entraîne lui-même à l'aide des jets périphériques (13) et fait pivoter un arbre de travail extensible (15). Les principales utilités de cette invention sont l'alimentation de générateurs électriques et d'autres dispositifs exigeant une puissance rotative, notamment les véhicules marins, les véhicules terrestres et les véhicules aériens.

Claims

CLAIMS
The embodiment of the invention in which an exclusive property and privilege
is claimed are defined as
follows:
1) A saw-tooth-shaped rotor (A) for producing power, comprising:
Three identical bundles of three peripheral mixer ports (4) connecting three
stacked disc-shaped supply
manifolds (1) (2) (3), each of said supply manifolds having a central inlet
port (6) (7) (8), with three
identical peripheral volute-shaped elongated tubular combustor ducts (5), each
of said combustor ducts
connected with a peripheral tangential jet nozzle (13), wherein each jet
nozzle forms a tangential
opening radially protruding from the peripheries of the adjacent supply
manifolds or radially
protruding from the periphery of an adjacent combustor duct.
2) A sinusoidal toroid stator (B) housing a rotor as defined in claim 1,
comprising:
Multiple identical peripheral elongated tubular heat recovery ducts (23)
connecting two toroid air
supply manifolds (22) (24), all of said heat recovery ducts and both of said
supply manifolds together
defining a toroid heat regenerator manifold (25) and multiple identical
peripheral exhaust slots (26); all
of said heat recovery ducts and all of said manifolds and all of said exhaust
slots composed between an
axial gas supply tube (21) at one end and an axial circular air inlet port
(20) surrounding an extended
rotor-shaft (15) at the opposite end.
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Description

CA 02426353 2006-07-25
DESCRIPTION OF THE INVENTION
HYDROGEN TURBINE
TECHNICAL FIELD
The invention relates to a gas turbine for the efficient generation of power.
BACKGROUND ART
While in commonly known gas turbines gas exiting from a combustion chamber
drives the rotor with the
reactive force against the rotor blades where losses occur, the invention is a
pure reaction gas turbine
without rotor blades.
TECHNICAL PROBLEM AND ITS SOLUTION
The invention solves the technical problem of converting hydrogen or another
fuel gas into rotary power
most directly and thus improving efficiency. The solution is a multi-ducted
hollow rotor A. Hydrogen and
air are forced through the multi-ducted rotor A via a multi ducted stator B.
Combustion occurs inside the
hollow rotor A which drives itself with peripheral jets 13 rotating an
extending power shaft 15 at high
velocity.
BRIEF DESCRIPTION OF THE DRAWINGS
In the drawings which represent the embodiment of the invention,
Fig 1 is an end view of a gas turbine according to the present invention
Fig 2 is a side view of the gas turbine shown in Fig 1
Fig 3 is the opposite end view of the gas turbine shown in Fig I
Fig 4 is an axial central section of the gas turbine shown in Fig 1
Fig 5 is a central cross section of the gas turbine shown in Fig 1
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DESCRIPTION OF THE PARTS AND THEIR INTERCONNECTIONS with REFERENCE TO THE
DRAWINGS
ROTOR
Saw-tooth-shaped turbine rotor A is made from ceramic material or metal alloy,
comprising:
A central disc-shaped gas supply manifold 1 stacked between axial disc-shaped
air supply manifold 2 and
axial disc-shaped air supply manifold 3, all said inanifolds connected via
mixer ports 4 to three peripheral
volute-shaped elongated tubular combustor duct 5.
Gas supply manifold 1 has a central circular inlet port 6.
Air supply manifold 2 has a central ring-shaped inlet port 7.
Air supply manifold 3 has a central ring-shaped inlet port 8.
Mixer ports 4 have mixer grooves 9.
Combustor ducts 5 are composed of a mixing chamber 10, an electric ignitor 11,
a combustor 12 and a jet
nozzle 13.
Jet nozzle 13 forms a tangential opening radially protruding from the
peripheries of the adjacent supply
manifolds or radially protruding from the periphery of an adjacent combustor
duct.
Gas supply manifold 1, air supply manifold 2 and air supply manifold 3 may
have compressor vanes 14.
Rotor A is attached to one end of rotor shaft 15 which has attached, near its
opposite end, an air impeller
16.
Rotor shaft 15 is supported by bearings 17 inside central hub 18, which is the
structural centre of a radial
structural frame 19.
Structural frame 19 is integral to turbine stator B.
STATOR
Sinusoidal toroid turbine stator B is made from metal alloy, comprising:
An axial air inlet port 20 surrounding extended rotor shaft 15 at one end and
an axial gas supply tube 21 at
the opposite end, an air supply manifold 22 connected via multiple identical
peripheral heat recovery ducts
23 to air supply manifold 24, both said manifolds together with all said heat
recovery ducts defining heat
regenerator manifold 25 and multiple identical peripheral exhaust slots 26.
Air inlet port 20 may be covered with screen 27.
Gas supply tube 21 is fastened inside an axial sleeve 28 which is the
structural hub of a radial structural
frame 29.
Structural hub 18 has multiple identical radial cooling fins 30.
Supply manifold 22 may have multiple identical heat transfer fins 31.
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CA 02426353 2006-07-25
Heat recovery ducts 23 may be connected with multiple heat transfer fins 32.
Supply manifold 24 may have multiple identical heat transfer fins 33.
Gas supply tube 21 connects with gas supply manifold 1 via opening 34 and
inlet port 6 and is separated
from rotor A by close labyrinth gap 35.
Air supply manifold 22 connects with air supply manifold 2 via exit port 36
and inlet port 7 and is
separated from rotor A by close labyrinth gap 37.
Air supply manifold 24 connects with air supply manifold 3 via exit port 38
and inlet port 8 and is
separated from rotor A by close labyrinth gap 39 and close labyrinth gap 40.
Stnzctural frame 29 has attached to it an ignitor magnet 41.
Heat recovery ducts 23 have disconnect joints 42.
Structural frame 19 and stnzctural frame 29 are bolted into a vehicle or a
cage structure.
Rotor shaft 15 is connected, via a reduction gear, to an electric generator or
another device requiring rotary
power.
DESCRIPTION OF HOW THE INVENTION WORKS WITH REFERENCE TO THE DRAWINGS
An electric generator, functioning as a start-up motor powered by an outside
electrical source, accelerates,
via a gear, rotor A to a high velocity. Air impeller 16 sucks air through
inlet port 20, forces it through
supply manifold 22, heat recovery ducts 23 and supply manifold 24, via exit
port 36, exit port 38, inlet port
7 and inlet port 8 into supply manifold 2 and into supply manifold 3 of rotor
A. whereby some air escapes
through labyrinth gap 37, labyrinth gap 39 and labyrinth gap 40.
Simultaneously, hydrogen gas is injected
through supply tube 21, via opening 34 and inlet port 6 into supply manifold 1
of rotor A, whereby some
hydrogen escapes through labyrinth gap 35. Rotor A, with its momentum, forces
the hydrogen gas through
supply manifold 1 and the air through supply manifold 2 and supply manifold 3
via mixer ports 4 into
mixing chamber 10 of combustor ducts 5 where hydrogen gas and air mix. From
mixing chamber 10 the
combustion gas passes by the electric ignitor 11 into combustor 12 where it
combusts and ejects as jet
through jet nozzle 13 into regenerator manifold 25, generating tangential
thrust driving rotor A directly.
Exhaust air and steam are cooling while forced through regenerator manifold 25
and through exhaust slots
26 and expelled as air and water into the ambient environment. Rotor shaft 15
powers, via the reduction
gear, the electric generator.
EXAMPLE
In the preferred application, installed in a vehicle, the invention drives,
with shaft 15, an electric generator
and thus is a compact and light weight power plant for electric vehicles.
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Representative Drawing