UA84262C2 - Авиационный газотурбинный двигатель - Google Patents
Авиационный газотурбинный двигательInfo
- Publication number
- UA84262C2 UA84262C2 UA20040605016A UA20040605016A UA84262C2 UA 84262 C2 UA84262 C2 UA 84262C2 UA 20040605016 A UA20040605016 A UA 20040605016A UA 20040605016 A UA20040605016 A UA 20040605016A UA 84262 C2 UA84262 C2 UA 84262C2
- Authority
- UA
- Ukraine
- Prior art keywords
- flow
- lining
- mixing
- inlet
- turbine engine
- Prior art date
Links
- 238000001816 cooling Methods 0.000 abstract 2
- 239000003381 stabilizer Substances 0.000 abstract 2
- 239000000446 fuel Substances 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
- F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- 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
-
- 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)
- Turbine Rotor Nozzle Sealing (AREA)
- Jet Pumps And Other Pumps (AREA)
- Spray-Type Burners (AREA)
Abstract
Изобретение относится к охлаждению обшивки форсажной камеры авиационного двухконтурного газотурбинного двигателя. Обшивка смешивания (3) потоков форсажной камеры расположена внутри кожуха (4). Между кожухом и обшивкой находится кольцевой канал (5), предназначенный для движения вторичного холодного потока (F2). Передние по потоку топливные инжекторы (6) расположены на входе в диффузор (2), а стабилизаторы пламени (7) расположены позади них. Обшивка смешивания (3) потоков на участке между плоскостями передних инжекторов и задних стабилизаторов пламени имеет двойную кривизну и расширяется по потоку с возможностью торможения первичного газового потока (F1). Вокруг переднего по потоку участка (10а) обшивки смешивания (3) есть кольцевой ковшовый заборник (11) для отбора части потока (F3) воздуха из холодного потока (F2). Поток (F3) подается тангенциально в первичный поток (F1) с помощью множества каналов (12), выполненных в стенке названной обшивки смешивания (3) между ковшовым заборником (11) и диффузором (2). Изобретение способствует охлаждению обшивки смешивания (3) потоков (F1) и (F2) на форсажных режимах работы двигателя.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0307657A FR2856744B1 (fr) | 2003-06-25 | 2003-06-25 | Canaux de ventilation sur tole de confluence d'une chambre de post-combustion |
Publications (1)
Publication Number | Publication Date |
---|---|
UA84262C2 true UA84262C2 (ru) | 2008-10-10 |
Family
ID=33396844
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
UA20040605016A UA84262C2 (ru) | 2003-06-25 | 2004-06-24 | Авиационный газотурбинный двигатель |
Country Status (9)
Country | Link |
---|---|
US (1) | US6976361B1 (ru) |
EP (1) | EP1491752B1 (ru) |
JP (1) | JP4150360B2 (ru) |
CA (1) | CA2470268A1 (ru) |
DE (1) | DE602004004319T2 (ru) |
ES (1) | ES2280914T3 (ru) |
FR (1) | FR2856744B1 (ru) |
RU (1) | RU2347930C2 (ru) |
UA (1) | UA84262C2 (ru) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2899280B1 (fr) * | 2006-03-30 | 2012-08-31 | Snecma | Dispositif de montage d'une paroi de separation de flux dans une chambre de post-combustion d'un turboreacteur |
FR2902150B1 (fr) * | 2006-06-09 | 2011-10-14 | Snecma | Dispositif injecteur de carburant, systeme de post-combustion et turboreacteur a double flux |
US8726670B2 (en) * | 2010-06-24 | 2014-05-20 | General Electric Company | Ejector purge of cavity adjacent exhaust flowpath |
JP6229590B2 (ja) * | 2014-04-30 | 2017-11-15 | 株式会社Ihi | アフタバーナ及び航空機エンジン |
CN105465831A (zh) * | 2016-01-12 | 2016-04-06 | 西北工业大学 | 带有双火焰筒及稳焰器的燃气轮机燃烧室 |
CN114738795B (zh) * | 2022-04-14 | 2023-06-09 | 西北工业大学 | 具有混气功能的支板稳定器和一体化加力燃烧室 |
CN115200042B (zh) * | 2022-07-21 | 2023-08-22 | 中国航发沈阳发动机研究所 | 一种采用气冷串列和分流支板整流的加力燃烧室 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1923150A1 (de) * | 1968-05-08 | 1970-01-15 | Man Turbo Gmbh | Zweistromturbinenstrahltriebwerk |
FR1588974A (ru) * | 1968-10-02 | 1970-03-16 | ||
US5483793A (en) * | 1970-09-02 | 1996-01-16 | General Electric Company | Infrared radiation suppression device |
US3747345A (en) * | 1972-07-24 | 1973-07-24 | United Aircraft Corp | Shortened afterburner construction for turbine engine |
US3826088A (en) * | 1973-02-01 | 1974-07-30 | Gen Electric | Gas turbine engine augmenter cooling liner stabilizers and supports |
US5694767A (en) * | 1981-11-02 | 1997-12-09 | General Electric Company | Variable slot bypass injector system |
FR2696502B1 (fr) * | 1992-10-07 | 1994-11-04 | Snecma | Dispositif de post-combustion pour turbo réacteur double flux. |
US4958489A (en) * | 1985-03-04 | 1990-09-25 | General Electric Company | Means for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas turbine engine |
FR2626044A1 (fr) * | 1988-01-14 | 1989-07-21 | Snecma | Melangeur de flux a section variable avec stabilisateur de rechauffe integre pour turboreacteur double flux |
-
2003
- 2003-06-25 FR FR0307657A patent/FR2856744B1/fr not_active Expired - Fee Related
-
2004
- 2004-06-11 CA CA002470268A patent/CA2470268A1/fr not_active Abandoned
- 2004-06-18 JP JP2004180806A patent/JP4150360B2/ja not_active Expired - Lifetime
- 2004-06-22 DE DE602004004319T patent/DE602004004319T2/de not_active Expired - Lifetime
- 2004-06-22 US US10/872,510 patent/US6976361B1/en not_active Expired - Lifetime
- 2004-06-22 EP EP04291572A patent/EP1491752B1/fr not_active Expired - Lifetime
- 2004-06-22 ES ES04291572T patent/ES2280914T3/es not_active Expired - Lifetime
- 2004-06-24 UA UA20040605016A patent/UA84262C2/ru unknown
- 2004-06-24 RU RU2004119361/06A patent/RU2347930C2/ru active
Also Published As
Publication number | Publication date |
---|---|
RU2004119361A (ru) | 2005-12-10 |
RU2347930C2 (ru) | 2009-02-27 |
US6976361B1 (en) | 2005-12-20 |
JP4150360B2 (ja) | 2008-09-17 |
JP2005016521A (ja) | 2005-01-20 |
EP1491752B1 (fr) | 2007-01-17 |
DE602004004319T2 (de) | 2007-08-30 |
DE602004004319D1 (de) | 2007-03-08 |
ES2280914T3 (es) | 2007-09-16 |
FR2856744B1 (fr) | 2007-05-25 |
US20050274114A1 (en) | 2005-12-15 |
EP1491752A1 (fr) | 2004-12-29 |
FR2856744A1 (fr) | 2004-12-31 |
CA2470268A1 (fr) | 2004-12-25 |
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