TR200500469T3 - Türbin lülesi. - Google Patents
Türbin lülesi.Info
- Publication number
- TR200500469T3 TR200500469T3 TR2005/00469T TR200500469T TR200500469T3 TR 200500469 T3 TR200500469 T3 TR 200500469T3 TR 2005/00469 T TR2005/00469 T TR 2005/00469T TR 200500469 T TR200500469 T TR 200500469T TR 200500469 T3 TR200500469 T3 TR 200500469T3
- Authority
- TR
- Turkey
- Prior art keywords
- central body
- pilot fuel
- turbine nozzle
- flow path
- combustion products
- 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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
- F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
-
- 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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
-
- 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
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
- Exhaust Gas After Treatment (AREA)
- Air Supply (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Bir gaz akis yolu içinde bir merkezi gövdeye (38) sahip olan, bir türbin motorunda kullanilan bir türbin lülesidir (32). bir alev tutucusu (42) akis yolu içinde merkezi gövdenin (38) disinda yer alir. Bir brülor (62), bir birinci pilot yakitinin yanma ürünlerinin atilmasi için merkezi gövde (38) içinde bir çikisa sahiptir. bir pilot yakiti borusu (100), atilan yanma ürünlerine bir ilave pilot yakitinin verilmesi için yerlestirilen bir çikisa sahiptir.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/426,671 US7093442B2 (en) | 2003-04-30 | 2003-04-30 | Augmentor |
Publications (1)
Publication Number | Publication Date |
---|---|
TR200500469T3 true TR200500469T3 (tr) | 2005-04-21 |
Family
ID=32990420
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
TR2005/00469T TR200500469T3 (tr) | 2003-04-30 | 2004-04-19 | Türbin lülesi. |
Country Status (13)
Country | Link |
---|---|
US (1) | US7093442B2 (tr) |
EP (1) | EP1473519A3 (tr) |
JP (1) | JP3974595B2 (tr) |
KR (1) | KR100610732B1 (tr) |
AU (1) | AU2004201209B2 (tr) |
CA (1) | CA2460659A1 (tr) |
DE (1) | DE04252295T1 (tr) |
IL (1) | IL161423A0 (tr) |
NO (1) | NO20041762L (tr) |
PL (1) | PL366887A1 (tr) |
SG (1) | SG144713A1 (tr) |
TR (1) | TR200500469T3 (tr) |
TW (1) | TWI238871B (tr) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2866675B1 (fr) * | 2004-02-24 | 2008-05-16 | Snecma Moteurs | Procede d'amelioration des performances d'allumage de dispositif de post-combustion pour turboreacteur double flux et dispositif de post-combustion a performance d'allumage amelioree |
US6983601B2 (en) * | 2004-05-28 | 2006-01-10 | General Electric Company | Method and apparatus for gas turbine engines |
US7174704B2 (en) * | 2004-07-23 | 2007-02-13 | General Electric Company | Split shroud exhaust nozzle |
US7437876B2 (en) * | 2005-03-25 | 2008-10-21 | General Electric Company | Augmenter swirler pilot |
US7467518B1 (en) | 2006-01-12 | 2008-12-23 | General Electric Company | Externally fueled trapped vortex cavity augmentor |
US8286416B2 (en) * | 2008-04-02 | 2012-10-16 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
US8578716B2 (en) * | 2008-03-22 | 2013-11-12 | United Technologies Corporation | Valve system for a gas turbine engine |
US8240126B2 (en) * | 2008-03-22 | 2012-08-14 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
US8402744B2 (en) * | 2008-03-22 | 2013-03-26 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
US8209987B2 (en) * | 2008-11-26 | 2012-07-03 | United Technologies Corporation | Augmentor pilot |
US8534071B1 (en) | 2012-04-06 | 2013-09-17 | United Technologies Corporation | Engine hot section vane with tapered flame holder surface |
US9879862B2 (en) | 2013-03-08 | 2018-01-30 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine afterburner |
CN113280366B (zh) * | 2021-05-13 | 2022-09-27 | 中国航空发动机研究院 | 一种基于自激扫掠振荡燃油喷嘴的加力燃烧室结构 |
Family Cites Families (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2693083A (en) * | 1951-03-26 | 1954-11-02 | Roy W Abbott | Combination flame-holder and fuel nozzle |
US2780915A (en) * | 1951-12-05 | 1957-02-12 | Solar Aircraft Co | Fuel distribution system for jet engine and afterburner |
US2880573A (en) * | 1952-08-27 | 1959-04-07 | Gen Motors Corp | Afterburner fuel injection system |
US2979899A (en) * | 1953-06-27 | 1961-04-18 | Snecma | Flame spreading device for combustion equipments |
US2978865A (en) * | 1956-02-06 | 1961-04-11 | Curtiss Wright Corp | Turbo fan exhaust mixing device |
US2880574A (en) * | 1956-05-18 | 1959-04-07 | Curtiss Wright Corp | By-pass turbo jet engine construction |
US2847821A (en) * | 1956-06-21 | 1958-08-19 | Westinghouse Electric Corp | Fuel ignition apparatus for an afterburner in the bypass duct of a turbojet engine |
US2910828A (en) * | 1956-08-24 | 1959-11-03 | United Aircraft Company | Convergent-divergent variable area propulsion nozzle |
US2929203A (en) * | 1956-08-31 | 1960-03-22 | Westinghouse Electric Corp | Afterburning bypass aviation turbojet engine |
US3075353A (en) * | 1959-08-19 | 1963-01-29 | Gen Electric | Supersonic combustion |
US3712062A (en) * | 1968-04-17 | 1973-01-23 | Gen Electric | Cooled augmentor liner |
GB1305887A (tr) * | 1971-07-01 | 1973-02-07 | ||
US3938328A (en) * | 1971-11-08 | 1976-02-17 | The Boeing Company | Multicycle engine |
US4069661A (en) * | 1975-06-02 | 1978-01-24 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Variable mixer propulsion cycle |
US4185461A (en) * | 1978-01-10 | 1980-01-29 | The United States Of America As Represented By The Secretary Of The Air Force | Turbojet engine with combustor bypass |
US5136840A (en) * | 1982-09-30 | 1992-08-11 | General Electric Company | Gas turbine engine actuation system |
US4798048A (en) | 1987-12-21 | 1989-01-17 | United Technologies Corporation | Augmentor pilot |
US5099644A (en) * | 1990-04-04 | 1992-03-31 | General Electric Company | Lean staged combustion assembly |
US5385015A (en) | 1993-07-02 | 1995-01-31 | United Technologies Corporation | Augmentor burner |
US5396761A (en) * | 1994-04-25 | 1995-03-14 | General Electric Company | Gas turbine engine ignition flameholder with internal impingement cooling |
US5685140A (en) | 1995-06-21 | 1997-11-11 | United Technologies Corporation | Method for distributing fuel within an augmentor |
US5867980A (en) * | 1996-12-17 | 1999-02-09 | General Electric Company | Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner |
US6125627A (en) * | 1998-08-11 | 2000-10-03 | Allison Advanced Development Company | Method and apparatus for spraying fuel within a gas turbine engine |
US6463739B1 (en) * | 2001-02-05 | 2002-10-15 | General Electric Company | Afterburner heat shield |
-
2003
- 2003-04-30 US US10/426,671 patent/US7093442B2/en not_active Expired - Lifetime
-
2004
- 2004-03-11 CA CA002460659A patent/CA2460659A1/en not_active Abandoned
- 2004-03-17 TW TW093107094A patent/TWI238871B/zh active
- 2004-03-24 AU AU2004201209A patent/AU2004201209B2/en not_active Ceased
- 2004-04-02 PL PL04366887A patent/PL366887A1/xx not_active Application Discontinuation
- 2004-04-15 SG SG200402056-6A patent/SG144713A1/en unknown
- 2004-04-15 IL IL16142304A patent/IL161423A0/xx unknown
- 2004-04-16 KR KR1020040026022A patent/KR100610732B1/ko not_active IP Right Cessation
- 2004-04-19 EP EP04252295A patent/EP1473519A3/en not_active Withdrawn
- 2004-04-19 DE DE04252295T patent/DE04252295T1/de active Pending
- 2004-04-19 TR TR2005/00469T patent/TR200500469T3/tr unknown
- 2004-04-28 JP JP2004132325A patent/JP3974595B2/ja not_active Expired - Fee Related
- 2004-04-29 NO NO20041762A patent/NO20041762L/no not_active Application Discontinuation
Also Published As
Publication number | Publication date |
---|---|
EP1473519A2 (en) | 2004-11-03 |
KR100610732B1 (ko) | 2006-08-09 |
KR20040094313A (ko) | 2004-11-09 |
SG144713A1 (en) | 2008-08-28 |
PL366887A1 (en) | 2004-11-02 |
TWI238871B (en) | 2005-09-01 |
AU2004201209A1 (en) | 2004-11-18 |
US7093442B2 (en) | 2006-08-22 |
NO20041762L (no) | 2004-11-01 |
EP1473519A3 (en) | 2007-04-11 |
AU2004201209B2 (en) | 2005-10-27 |
IL161423A0 (en) | 2004-09-27 |
DE04252295T1 (de) | 2005-06-23 |
US20040216444A1 (en) | 2004-11-04 |
JP2004332729A (ja) | 2004-11-25 |
TW200424435A (en) | 2004-11-16 |
CA2460659A1 (en) | 2004-10-30 |
JP3974595B2 (ja) | 2007-09-12 |
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