CA2426353C - Hydrogen turbine - Google Patents
Hydrogen turbine Download PDFInfo
- Publication number
- CA2426353C CA2426353C CA002426353A CA2426353A CA2426353C CA 2426353 C CA2426353 C CA 2426353C CA 002426353 A CA002426353 A CA 002426353A CA 2426353 A CA2426353 A CA 2426353A CA 2426353 C CA2426353 C CA 2426353C
- Authority
- CA
- Canada
- Prior art keywords
- rotor
- ducts
- peripheral
- combustor
- hydrogen
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/32—Non-positive-displacement machines or engines, e.g. steam turbines with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
- F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
- F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
- F02C3/165—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant the combustion chamber contributes to the driving force by creating reactive thrust
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
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.
Description
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 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.
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 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.
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.
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.
Claims (2)
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.
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.
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002426353A CA2426353C (en) | 2003-04-25 | 2003-04-25 | Hydrogen turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002426353A CA2426353C (en) | 2003-04-25 | 2003-04-25 | Hydrogen turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2426353A1 CA2426353A1 (en) | 2004-10-25 |
| CA2426353C true CA2426353C (en) | 2007-05-29 |
Family
ID=33315161
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002426353A Expired - Fee Related CA2426353C (en) | 2003-04-25 | 2003-04-25 | Hydrogen turbine |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2426353C (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0608847D0 (en) * | 2006-05-05 | 2006-06-14 | Academy Projects Ltd | An Engine |
| ES2304226B1 (en) * | 2007-03-13 | 2009-08-13 | Javier Porcar Orti | MECHANICAL MOVEMENT GENERATOR SYSTEM FOR THE PRODUCTION OF ELECTRICAL ENERGY THROUGH THE APPLICATION AND COMBUSTION OF HYDROGEN. |
| CN102003284B (en) * | 2010-12-16 | 2013-03-06 | 梁屹 | Hydrogen-blended gas fuel engine |
-
2003
- 2003-04-25 CA CA002426353A patent/CA2426353C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CA2426353A1 (en) | 2004-10-25 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20210426 |