CA2461680A1 - Fuel injector - Google Patents
Fuel injector Download PDFInfo
- Publication number
- CA2461680A1 CA2461680A1 CA 2461680 CA2461680A CA2461680A1 CA 2461680 A1 CA2461680 A1 CA 2461680A1 CA 2461680 CA2461680 CA 2461680 CA 2461680 A CA2461680 A CA 2461680A CA 2461680 A1 CA2461680 A1 CA 2461680A1
- Authority
- CA
- Canada
- Prior art keywords
- fuel
- fuel injector
- nozzle
- perimeter edge
- circular
- 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.)
- Abandoned
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The Invention relates to a fuel Injector (1) for the supply of fuel into a gas turbine rotor (B). It solves the technical problem of injecting fuel continuously into a rotating hollow rotor (B) without loss. This is achieved by shaping the nozzle (3) of the fuel injector (1) in such a way, that fuel escaping through the gap (2) between the static fuel injector nozzle (3) and the rotating fuel intake nozzle (8) is sucked into the hollow rotor (B) via an air intake port (15).
Description
DISCLOSURE
Description of the Invention with reference to the drawings Elongated tubular fuel injector 1 is made from metal alloy or another impervious material, is a central integral axial component of turbine stator A and it is separated from turbine rotor B by a close gap 2. Fuel injector 1 has a fuel injector nozzle 3 which is defined by an axial ring-shaped circular nozzle surface 4. Nozzle surface 4 is defined by a circular outer perimeter edge 5 and by a circular inner perimeter edge 6 which is identical with the perimeter edge 6 of fuel injector port 7. Rotor B has a fuel intake nozzle 8 which is defined by an axial ring-shaped circular nozzle surface 9 proximate to nozzle surface 4. Nozzle surface 9 is defined by a circular outer perimeter edge 10 and by a circular inner perimeter edge 11 which is identical with the perimeter edge 11 of fuel intake port 12. Close gap 2 is defined by nozzle surface 4 and nozzle surface 9.
Axial ring-shaped circular air supply port i 3 is defined by circular inner perimeter edge 5 and circular outer perimeter edge 14. Axial ring-shaped circular air intake port 15 is defined by circular inner perimeter edge 10 and circular outer perimeter edge 16. Fuel injector 1 is fastened into axial position inside axial sleeve 17 which is the structural hub of radial structure 18. Rotor B is fastened to drive shaft 19 which is held in position with active magnetic bearings 20 inside an industrial high rpm electric generator C. Housing 21 of electric generator C has fastened to it a radial structure 22. Radial structure 18 and radial structure 22 are rigidly connected with invar cage frames 23. Stator A
further comprises air supply manifold 24 and air supply regenerator tubes 25. Hollow rotor B
further comprises compressors 26, mixer ports 27, mixing chambers 28, ignitors 29, combustors 30 and peripheral jet nozzles 31 Description of how the invention works with reference to the drawings Fuel is continuously injected through injector port 6 via fuel intake port 12 into the rotating hollow rotor B. Fuel escaping through close gap 2 is sucked through air intake port 15 into the hollow rotor B. There is no loss of fuel. Fuel and combustion air are forced through compressors 26 and mixer ports 27 into and through mixing chambers 28, then bypass ignitors 29 into combustors 30 where they combust and eject through jet nozzles 31. The dynamic thrust of the jet drives turbine rotor B which drives electric generator C.
Brief description of the drawings In the drawings which represent the embodiment of the invention, fig. 1 is an axial longitudinal section through the fuel injector inside a gas turbine system.
fig. 2 is a cross section through the nozzle of the fuel injector inside a gas turbine system.
Description of the Invention with reference to the drawings Elongated tubular fuel injector 1 is made from metal alloy or another impervious material, is a central integral axial component of turbine stator A and it is separated from turbine rotor B by a close gap 2. Fuel injector 1 has a fuel injector nozzle 3 which is defined by an axial ring-shaped circular nozzle surface 4. Nozzle surface 4 is defined by a circular outer perimeter edge 5 and by a circular inner perimeter edge 6 which is identical with the perimeter edge 6 of fuel injector port 7. Rotor B has a fuel intake nozzle 8 which is defined by an axial ring-shaped circular nozzle surface 9 proximate to nozzle surface 4. Nozzle surface 9 is defined by a circular outer perimeter edge 10 and by a circular inner perimeter edge 11 which is identical with the perimeter edge 11 of fuel intake port 12. Close gap 2 is defined by nozzle surface 4 and nozzle surface 9.
Axial ring-shaped circular air supply port i 3 is defined by circular inner perimeter edge 5 and circular outer perimeter edge 14. Axial ring-shaped circular air intake port 15 is defined by circular inner perimeter edge 10 and circular outer perimeter edge 16. Fuel injector 1 is fastened into axial position inside axial sleeve 17 which is the structural hub of radial structure 18. Rotor B is fastened to drive shaft 19 which is held in position with active magnetic bearings 20 inside an industrial high rpm electric generator C. Housing 21 of electric generator C has fastened to it a radial structure 22. Radial structure 18 and radial structure 22 are rigidly connected with invar cage frames 23. Stator A
further comprises air supply manifold 24 and air supply regenerator tubes 25. Hollow rotor B
further comprises compressors 26, mixer ports 27, mixing chambers 28, ignitors 29, combustors 30 and peripheral jet nozzles 31 Description of how the invention works with reference to the drawings Fuel is continuously injected through injector port 6 via fuel intake port 12 into the rotating hollow rotor B. Fuel escaping through close gap 2 is sucked through air intake port 15 into the hollow rotor B. There is no loss of fuel. Fuel and combustion air are forced through compressors 26 and mixer ports 27 into and through mixing chambers 28, then bypass ignitors 29 into combustors 30 where they combust and eject through jet nozzles 31. The dynamic thrust of the jet drives turbine rotor B which drives electric generator C.
Brief description of the drawings In the drawings which represent the embodiment of the invention, fig. 1 is an axial longitudinal section through the fuel injector inside a gas turbine system.
fig. 2 is a cross section through the nozzle of the fuel injector inside a gas turbine system.
Claims
1. A tubular fuel injector (1) for injecting fuel continuously into a rotating hollow turbine rotor (B), having an axial ring-shaped circular injector nozzle (3), which nozzle has an axial ring-shaped circular surface (4), which surface is defined by a circular outer perimeter edge (5), which edge is identical with the defining circular inner perimeter edge (5) of an axial ring-shaped circular air supply port (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA 2461680 CA2461680A1 (en) | 2004-03-25 | 2004-03-25 | Fuel injector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA 2461680 CA2461680A1 (en) | 2004-03-25 | 2004-03-25 | Fuel injector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2461680A1 true CA2461680A1 (en) | 2005-09-25 |
Family
ID=35006190
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA 2461680 Abandoned CA2461680A1 (en) | 2004-03-25 | 2004-03-25 | Fuel injector |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2461680A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109386840A (en) * | 2017-08-10 | 2019-02-26 | 通用电气公司 | Volute burner for gas-turbine unit |
-
2004
- 2004-03-25 CA CA 2461680 patent/CA2461680A1/en not_active Abandoned
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109386840A (en) * | 2017-08-10 | 2019-02-26 | 通用电气公司 | Volute burner for gas-turbine unit |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FZDE | Dead |