SE7500960L - - Google Patents
Info
- Publication number
- SE7500960L SE7500960L SE7500960A SE7500960A SE7500960L SE 7500960 L SE7500960 L SE 7500960L SE 7500960 A SE7500960 A SE 7500960A SE 7500960 A SE7500960 A SE 7500960A SE 7500960 L SE7500960 L SE 7500960L
- Authority
- SE
- Sweden
- Prior art keywords
- prechamber
- air
- fuel
- reaction zone
- sliding ring
- Prior art date
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
- F23R3/26—Controlling the air flow
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
-
- 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
-
- 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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/40—Movement of components
- F05D2250/41—Movement of components with one degree of freedom
- F05D2250/411—Movement of components with one degree of freedom in rotation
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A combustion apparatus for gas turbine engines particularly adapted to reduce emissions to meet automotive requirements. The fuel is laid on the wall of a cylindrical prechamber and evaporated from the wall by combustion air which is introduced through a swirler at the upstream end of the prechamber. The inner surface of the prechamber is artificially roughened by a grid of grooves to improve fuel evaporation. The fuel is laid on the wall from an annular manifold extending around the upstream end of the prechamber through tangential orifices leading from the manifold into the interior of the prechamber. The fuel manifold is cooled and shielded from heat by an air jacket. More air enters through entrance ports distributed around the prechamber toward its downstream end. The resulting lean fuel-air mixture is delivered past an annular flow dam at the outlet of the prechamber into a combustion or reaction zone which is abruptly enlarged from the prechamber. The structure causes turbulent flow, recirculation, and good mixing in the reaction zone. A dilution zone downstream at the reaction zone has a circumferential array of dilution air ports which are of such shape as to be varied nonlinearly in area by a sliding ring valve. The sliding ring valve is coupled to a second sliding ring valve which varies the area of the air entrance ports in the prechamber in reverse sense to the dilution air ports. A pilot fuel nozzle to aid in cold starts is mounted at the upstream end of the prechamber.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US439648A US3859787A (en) | 1974-02-04 | 1974-02-04 | Combustion apparatus |
Publications (2)
Publication Number | Publication Date |
---|---|
SE7500960L true SE7500960L (en) | 1975-08-05 |
SE393839B SE393839B (en) | 1977-05-23 |
Family
ID=23745561
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SE7500960A SE393839B (en) | 1974-02-04 | 1975-01-29 | COMBUSTION DEVICE |
Country Status (8)
Country | Link |
---|---|
US (1) | US3859787A (en) |
JP (1) | JPS5825931B2 (en) |
CA (1) | CA1013153A (en) |
DE (1) | DE2460709C2 (en) |
FR (1) | FR2259989B1 (en) |
GB (1) | GB1467499A (en) |
IT (1) | IT1026493B (en) |
SE (1) | SE393839B (en) |
Families Citing this family (64)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2253389A5 (en) * | 1973-12-04 | 1975-06-27 | France Etat | |
US3925002A (en) * | 1974-11-11 | 1975-12-09 | Gen Motors Corp | Air preheating combustion apparatus |
US3938324A (en) * | 1974-12-12 | 1976-02-17 | General Motors Corporation | Premix combustor with flow constricting baffle between combustion and dilution zones |
US3930368A (en) * | 1974-12-12 | 1976-01-06 | General Motors Corporation | Combustion liner air valve |
US3958416A (en) * | 1974-12-12 | 1976-05-25 | General Motors Corporation | Combustion apparatus |
US4045956A (en) * | 1974-12-18 | 1977-09-06 | United Technologies Corporation | Low emission combustion chamber |
US4058977A (en) * | 1974-12-18 | 1977-11-22 | United Technologies Corporation | Low emission combustion chamber |
US3973395A (en) * | 1974-12-18 | 1976-08-10 | United Technologies Corporation | Low emission combustion chamber |
DE2629761A1 (en) * | 1976-07-02 | 1978-01-05 | Volkswagenwerk Ag | COMBUSTION CHAMBER FOR GAS TURBINES |
GB1592858A (en) * | 1977-01-21 | 1981-07-08 | Rolls Royce | Combustion equipment for gas turbine engines |
US4246757A (en) * | 1979-03-27 | 1981-01-27 | General Electric Company | Combustor including a cyclone prechamber and combustion process for gas turbines fired with liquid fuel |
US4269466A (en) * | 1979-11-23 | 1981-05-26 | Amp Incorporated | Connector and strain relief for flat transmission cable |
US4263780A (en) * | 1979-09-28 | 1981-04-28 | General Motors Corporation | Lean prechamber outflow combustor with sets of primary air entrances |
DE2949388A1 (en) * | 1979-12-07 | 1981-06-11 | Kraftwerk Union AG, 4330 Mülheim | COMBUSTION CHAMBER FOR GAS TURBINES AND METHOD FOR OPERATING THE COMBUSTION CHAMBER |
FR2471480A1 (en) * | 1979-12-13 | 1981-06-19 | Snecma | INJECTION DEVICE FOR A COMBUSTION CHAMBER FOR A TURBINE ENGINE |
EP0035869B1 (en) * | 1980-03-05 | 1984-07-11 | Hitachi, Ltd. | A gas turbine combustor |
US4735044A (en) * | 1980-11-25 | 1988-04-05 | General Electric Company | Dual fuel path stem for a gas turbine engine |
US4467610A (en) * | 1981-04-17 | 1984-08-28 | General Electric Company | Gas turbine fuel system |
US4404806A (en) * | 1981-09-04 | 1983-09-20 | General Motors Corporation | Gas turbine prechamber and fuel manifold structure |
DE3209135A1 (en) * | 1982-03-12 | 1983-09-15 | Kraftwerk Union AG, 4330 Mülheim | GAS TURBINE COMBUSTION CHAMBER |
JP2644745B2 (en) * | 1987-03-06 | 1997-08-25 | 株式会社日立製作所 | Gas turbine combustor |
JPH0816531B2 (en) * | 1987-04-03 | 1996-02-21 | 株式会社日立製作所 | Gas turbine combustor |
JP2516822Y2 (en) * | 1988-08-04 | 1996-11-13 | 川崎重工業株式会社 | Gas turbine combustor |
DE4435266A1 (en) * | 1994-10-01 | 1996-04-04 | Abb Management Ag | burner |
US5669218A (en) * | 1995-05-31 | 1997-09-23 | Dresser-Rand Company | Premix fuel nozzle |
US5813232A (en) * | 1995-06-05 | 1998-09-29 | Allison Engine Company, Inc. | Dry low emission combustor for gas turbine engines |
GB2351343A (en) * | 1999-06-22 | 2000-12-27 | Alstom Gas Turbines Ltd | Telescopically-moveable combustion chamber |
US6539721B2 (en) * | 2001-07-10 | 2003-04-01 | Pratt & Whitney Canada Corp. | Gas-liquid premixer |
SE523082C2 (en) * | 2001-11-20 | 2004-03-23 | Volvo Aero Corp | Device at a combustion chamber of a gas turbine for controlling gas inflow to the combustion zone of the combustion chamber |
US7028484B2 (en) | 2002-08-30 | 2006-04-18 | Pratt & Whitney Canada Corp. | Nested channel ducts for nozzle construction and the like |
US7654088B2 (en) * | 2004-02-27 | 2010-02-02 | Pratt & Whitney Canada Corp. | Dual conduit fuel manifold for gas turbine engine |
US20060156733A1 (en) | 2005-01-14 | 2006-07-20 | Pratt & Whitney Canada Corp. | Integral heater for fuel conveying member |
US7565807B2 (en) | 2005-01-18 | 2009-07-28 | Pratt & Whitney Canada Corp. | Heat shield for a fuel manifold and method |
US7533531B2 (en) | 2005-04-01 | 2009-05-19 | Pratt & Whitney Canada Corp. | Internal fuel manifold with airblast nozzles |
US7540157B2 (en) | 2005-06-14 | 2009-06-02 | Pratt & Whitney Canada Corp. | Internally mounted fuel manifold with support pins |
US7559201B2 (en) | 2005-09-08 | 2009-07-14 | Pratt & Whitney Canada Corp. | Redundant fuel manifold sealing arrangement |
DE102005062079A1 (en) * | 2005-12-22 | 2007-07-12 | Rolls-Royce Deutschland Ltd & Co Kg | Magervormic burner with a nebulizer lip |
US7854120B2 (en) | 2006-03-03 | 2010-12-21 | Pratt & Whitney Canada Corp. | Fuel manifold with reduced losses |
US7607226B2 (en) | 2006-03-03 | 2009-10-27 | Pratt & Whitney Canada Corp. | Internal fuel manifold with turned channel having a variable cross-sectional area |
US7942002B2 (en) | 2006-03-03 | 2011-05-17 | Pratt & Whitney Canada Corp. | Fuel conveying member with side-brazed sealing members |
US7624577B2 (en) | 2006-03-31 | 2009-12-01 | Pratt & Whitney Canada Corp. | Gas turbine engine combustor with improved cooling |
US8096130B2 (en) | 2006-07-20 | 2012-01-17 | Pratt & Whitney Canada Corp. | Fuel conveying member for a gas turbine engine |
US8353166B2 (en) | 2006-08-18 | 2013-01-15 | Pratt & Whitney Canada Corp. | Gas turbine combustor and fuel manifold mounting arrangement |
US7765808B2 (en) | 2006-08-22 | 2010-08-03 | Pratt & Whitney Canada Corp. | Optimized internal manifold heat shield attachment |
US8033113B2 (en) | 2006-08-31 | 2011-10-11 | Pratt & Whitney Canada Corp. | Fuel injection system for a gas turbine engine |
US7703289B2 (en) | 2006-09-18 | 2010-04-27 | Pratt & Whitney Canada Corp. | Internal fuel manifold having temperature reduction feature |
US7775047B2 (en) | 2006-09-22 | 2010-08-17 | Pratt & Whitney Canada Corp. | Heat shield with stress relieving feature |
US7926286B2 (en) | 2006-09-26 | 2011-04-19 | Pratt & Whitney Canada Corp. | Heat shield for a fuel manifold |
US7716933B2 (en) * | 2006-10-04 | 2010-05-18 | Pratt & Whitney Canada Corp. | Multi-channel fuel manifold |
US8572976B2 (en) | 2006-10-04 | 2013-11-05 | Pratt & Whitney Canada Corp. | Reduced stress internal manifold heat shield attachment |
US20080104961A1 (en) * | 2006-11-08 | 2008-05-08 | Ronald Scott Bunker | Method and apparatus for enhanced mixing in premixing devices |
US7856825B2 (en) | 2007-05-16 | 2010-12-28 | Pratt & Whitney Canada Corp. | Redundant mounting system for an internal fuel manifold |
US8096104B2 (en) * | 2007-05-31 | 2012-01-17 | United Technologies Corporation | Fluidic vectoring for exhaust nozzle |
US8146365B2 (en) | 2007-06-14 | 2012-04-03 | Pratt & Whitney Canada Corp. | Fuel nozzle providing shaped fuel spray |
US8096132B2 (en) * | 2008-02-20 | 2012-01-17 | Flexenergy Energy Systems, Inc. | Air-cooled swirlerhead |
US8887390B2 (en) | 2008-08-15 | 2014-11-18 | Dresser-Rand Company | Method for correcting downstream deflection in gas turbine nozzles |
US9181813B2 (en) | 2012-07-05 | 2015-11-10 | Siemens Aktiengesellschaft | Air regulation for film cooling and emission control of combustion gas structure |
EP3015772B1 (en) * | 2014-10-31 | 2020-01-08 | Ansaldo Energia Switzerland AG | Combustor arrangement for a gas turbine |
CN114047103A (en) * | 2015-07-21 | 2022-02-15 | 弗卢德森斯国际有限公司 | System and method for detecting particles in liquid or air |
US10995699B2 (en) * | 2018-02-19 | 2021-05-04 | Mra Systems, Llc. | Thrust reverser cascade |
CA3099915C (en) * | 2018-05-15 | 2023-08-01 | Mark Daniel D'agostini | System and method of improving combustion stability in a gas turbine |
US10989413B2 (en) * | 2019-07-17 | 2021-04-27 | General Electric Company | Axial retention assembly for combustor components of a gas turbine engine |
CN112483260A (en) * | 2020-12-15 | 2021-03-12 | 通化师范学院 | Starting equipment of gas turbine |
US11428411B1 (en) | 2021-05-18 | 2022-08-30 | General Electric Company | Swirler with rifled venturi for dynamics mitigation |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3075352A (en) * | 1958-11-28 | 1963-01-29 | Gen Motors Corp | Combustion chamber fluid inlet construction |
DE1131947B (en) * | 1959-03-28 | 1962-06-20 | Maschf Augsburg Nuernberg Ag | Combustion process for gas turbine combustion chambers and equipment for carrying out the process |
US3780530A (en) * | 1969-10-23 | 1973-12-25 | United Aircraft Corp | Combustion chamber |
US3691762A (en) * | 1970-12-04 | 1972-09-19 | Caterpillar Tractor Co | Carbureted reactor combustion system for gas turbine engine |
JPS5134524B2 (en) * | 1971-12-09 | 1976-09-27 |
-
1974
- 1974-02-04 US US439648A patent/US3859787A/en not_active Expired - Lifetime
- 1974-10-23 CA CA212,069A patent/CA1013153A/en not_active Expired
- 1974-12-12 GB GB5374074A patent/GB1467499A/en not_active Expired
- 1974-12-18 DE DE2460709A patent/DE2460709C2/en not_active Expired
-
1975
- 1975-01-28 IT IT47881/75A patent/IT1026493B/en active
- 1975-01-29 SE SE7500960A patent/SE393839B/en not_active IP Right Cessation
- 1975-02-04 JP JP50014046A patent/JPS5825931B2/en not_active Expired
- 1975-02-04 FR FR7503466A patent/FR2259989B1/fr not_active Expired
Also Published As
Publication number | Publication date |
---|---|
US3859787A (en) | 1975-01-14 |
DE2460709A1 (en) | 1975-08-07 |
IT1026493B (en) | 1978-09-20 |
SE393839B (en) | 1977-05-23 |
JPS50140716A (en) | 1975-11-12 |
JPS5825931B2 (en) | 1983-05-31 |
GB1467499A (en) | 1977-03-16 |
FR2259989B1 (en) | 1980-01-11 |
DE2460709C2 (en) | 1982-12-16 |
FR2259989A1 (en) | 1975-08-29 |
CA1013153A (en) | 1977-07-05 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
NUG | Patent has lapsed |
Ref document number: 7500960-5 Effective date: 19891201 Format of ref document f/p: F |