JP2008025579A - 燃焼室の壁の換気システム - Google Patents
燃焼室の壁の換気システム Download PDFInfo
- Publication number
- JP2008025579A JP2008025579A JP2007186670A JP2007186670A JP2008025579A JP 2008025579 A JP2008025579 A JP 2008025579A JP 2007186670 A JP2007186670 A JP 2007186670A JP 2007186670 A JP2007186670 A JP 2007186670A JP 2008025579 A JP2008025579 A JP 2008025579A
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- JP
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- Prior art keywords
- diffuser
- case
- wall
- combustion chamber
- downstream
- 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.)
- Granted
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 56
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 31
- 238000009423 ventilation Methods 0.000 claims description 13
- 238000003466 welding Methods 0.000 claims description 4
- 238000000926 separation method Methods 0.000 abstract description 5
- 238000002347 injection Methods 0.000 description 11
- 239000007924 injection Substances 0.000 description 11
- 238000001816 cooling Methods 0.000 description 3
- 238000010790 dilution Methods 0.000 description 3
- 239000012895 dilution Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 1
Images
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
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
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- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
-
- 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
-
- 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
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- 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
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/182—Two-dimensional patterned crenellated, notched
-
- 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)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
【解決手段】ディフューザ(12)により燃焼室(14)に空気を供給する遠心圧縮機(10)を含む、タービンエンジン内の燃焼室の壁の換気システムであって、このシステムは、燃焼室とディフューザの上流末端部(26)との間に半径方向に配置された環状ケース(90)を含み、このケースが、ディフューザから出る空気流を案内するための半径方向外側の壁(92)と、ディフューザから出る空気が出るための通路(88)をディフューザの末端部と共に画定する半径方向内側の壁(94)とを含む。
【選択図】図1
Description
12 ディフューザ
14 環状燃焼室
26 末端部
30 上流カバー
46 燃焼室の半径方向内側の壁
52 環状リング
88 通路
90 環状ケース
92、94 回転壁
104 円筒形の上流縁
106 円筒形の下流縁
117 半シェル
118 円筒形のリング
120 圧力均衡穴
Claims (14)
- ディフューザ(12)により環状燃焼室(14)に空気を供給する遠心圧縮機(10)を含み、ディフューザが、半径方向外側の端で圧縮機の出口と連通して空気が流れる半径方向環状の通路を形成するために、遠心圧縮機のインペラに沿って下流に延びるほぼL字型断面の環状末端部(26)を含む、タービンエンジン内の燃焼室の壁の換気システムであって、環状ケース(90)が、燃焼室とディフューザの末端部との間に半径方向に配置されて、ディフューザから、燃焼室の出口の付近およびディフューザの末端部の下流端の付近まで軸方向に延びており、このケースが、ディフューザから出る空気流を燃焼室の半径方向内側の壁(46)に沿って案内するための半径方向外側の回転壁(92)と、ディフューザから出る空気が通るための環状通路(88)をディフューザの末端部と共に画定する半径方向内側の回転壁(94)とを含むことを特徴とする、システム。
- ケース(90)が、互いに横方向に組み立てられる2個の半シェルから形成されることを特徴とする、請求項1に記載のシステム。
- ケースの半径方向外側の壁(92)が、燃焼室の内壁(46)にほぼ平行に延びることを特徴とする、請求項1または2に記載のシステム。
- ケースの半径方向内側の壁(94)が、ディフューザの末端部(26)にほぼ平行に延びることを特徴とする、請求項1から3のいずれか一項に記載のシステム。
- ケースの回転壁(92、94)が、圧力均衡穴(120)を含むことを特徴とする、請求項1から4のいずれか一項に記載のシステム。
- ケースが、それぞれ、ディフューザ(12)と、燃焼室の内壁(46)の環状リング(52)とに心合わせされて支持される円筒形の上流縁(104)および円筒形の下流縁(106)を含むことを特徴とする、請求項1から5のいずれか一項に記載のシステム。
- ケースの上流縁および下流縁(104、106)が、それぞれ、ディフューザ(12)と、燃焼室の内壁(46)の環状リング(52)とに、焼きばめ固定されることを特徴とする、請求項6に記載のシステム。
- ケースの円筒形の上流縁(104)が、刻みをつけられていて、ディフューザから出る空気を、ディフューザの末端部(26)に沿った空気通路(88)に供給する穴を形成することを特徴とする、請求項6または7に記載のシステム。
- ケースが、ケースの円筒形の下流縁(106)に軸方向に係合されてたとえば溶接により固定される、円筒形のリング(118)により固定されることを特徴とする、請求項6から8のいずれか一項に記載のシステム。
- 請求項1から9のいずれか一項に記載の換気システムを含むことを特徴とする、タービンエンジン。
- 互いの内部に延びる同軸の2個の回転壁(92、94)を含み、これらの壁の上流端が、上流に向かって配向された円筒形の軸方向の縁(104)により互いに結合され、これらの壁の下流端が、下流に向かって配向された円筒形の軸方向の縁(106)によって互いに結合されることを特徴とする、請求項1から10のいずれか一項に記載の換気システムのための環状ケース。
- 半径方向外側の壁(92)が、ほぼ円錐台形であり、半径方向内側の壁(94)が、ほぼU字型の断面を有することを特徴とする、請求項11に記載のケース。
- 回転壁(92、94)が、穴(120)を含むことを特徴とする、請求項11または12に記載のケース。
- 横に並置された2個の半シェル(117)から形成されることを特徴とする、請求項11から13のいずれか一項に記載のケース。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0606542 | 2006-07-19 | ||
FR0606542A FR2904047B1 (fr) | 2006-07-19 | 2006-07-19 | Systeme de ventilation de paroi de chambre de combustion |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2008025579A true JP2008025579A (ja) | 2008-02-07 |
JP2008025579A5 JP2008025579A5 (ja) | 2010-08-12 |
JP4904592B2 JP4904592B2 (ja) | 2012-03-28 |
Family
ID=37833542
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007186670A Active JP4904592B2 (ja) | 2006-07-19 | 2007-07-18 | 燃焼室の壁の換気システム |
Country Status (6)
Country | Link |
---|---|
US (1) | US7937944B2 (ja) |
EP (1) | EP1881180B1 (ja) |
JP (1) | JP4904592B2 (ja) |
CA (1) | CA2594146C (ja) |
FR (1) | FR2904047B1 (ja) |
RU (1) | RU2446297C2 (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008025580A (ja) * | 2006-07-19 | 2008-02-07 | Snecma | 遠心圧縮機のインペラの下流側空洞の冷却システム |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2920032B1 (fr) * | 2007-08-13 | 2014-08-22 | Snecma | Diffuseur d'une turbomachine |
FR2927951B1 (fr) * | 2008-02-27 | 2011-08-19 | Snecma | Ensemble diffuseur-redresseur pour une turbomachine |
FR2946687B1 (fr) * | 2009-06-10 | 2011-07-01 | Snecma | Turbomachine comprenant des moyens ameliores de reglage du debit d'un flux d'air de refroidissement preleve en sortie de compresseur haute pression |
FR2950656B1 (fr) | 2009-09-25 | 2011-09-23 | Snecma | Ventilation d'une roue de turbine dans une turbomachine |
US20110088379A1 (en) * | 2009-10-15 | 2011-04-21 | General Electric Company | Exhaust gas diffuser |
WO2014133616A1 (en) * | 2013-03-01 | 2014-09-04 | Rolls-Royce North American Technologies,Inc. | Gas turbine engine impeller system for an intermediate pressure (ip) compressor |
FR3006369B1 (fr) * | 2013-06-04 | 2015-05-29 | Snecma | Turbomachine a etage de compression centrifuge |
US20160290174A1 (en) * | 2015-04-02 | 2016-10-06 | General Electric Company | Heat pipe aftercooling system for a turbomachine |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
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US4657482A (en) * | 1980-10-10 | 1987-04-14 | Rolls-Royce Plc | Air cooling systems for gas turbine engines |
US5555721A (en) * | 1994-09-28 | 1996-09-17 | General Electric Company | Gas turbine engine cooling supply circuit |
JPH108996A (ja) * | 1996-06-24 | 1998-01-13 | Nissan Motor Co Ltd | ガスタービンエンジン |
JP2001506342A (ja) * | 1996-12-23 | 2001-05-15 | プラット アンド ホイットニー カナダ インコーポレイテッド | スラストベアリング荷重制御装置を有するタービンエンジン |
US20030167775A1 (en) * | 2000-12-13 | 2003-09-11 | Soechting Friedrich O. | Vane platform trailing edge cooling |
Family Cites Families (10)
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US3088279A (en) * | 1960-08-26 | 1963-05-07 | Gen Electric | Radial flow gas turbine power plant |
SU556221A1 (ru) * | 1975-11-20 | 1977-04-30 | Уфимский авиационный институт им. Орджоникидзе | Устройство дл охлаждени диска турбомашины |
US4277222A (en) * | 1979-01-11 | 1981-07-07 | Teledyne Industries, Inc. | Turbine engine compressor |
US4416111A (en) * | 1981-02-25 | 1983-11-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Air modulation apparatus |
US4462204A (en) * | 1982-07-23 | 1984-07-31 | General Electric Company | Gas turbine engine cooling airflow modulator |
DE3514352A1 (de) * | 1985-04-20 | 1986-10-23 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Gasturbinentriebwerk mit einrichtungen zur abzweigung von verdichterluft zur kuehlung von heissteilen |
US5628193A (en) * | 1994-09-16 | 1997-05-13 | Alliedsignal Inc. | Combustor-to-turbine transition assembly |
RU2130124C1 (ru) * | 1996-05-28 | 1999-05-10 | Акционерное общество "Авиадвигатель" | Ротор многоступенчатой турбины |
DE19845375A1 (de) * | 1998-10-02 | 2000-04-06 | Asea Brown Boveri | Verfahren und Vorrichtung zur indirekten Kühlung der Strömung in zwischen Rotoren und Statoren von Turbomaschinen ausgebildeten Radialspalten |
FR2839745B1 (fr) * | 2002-05-16 | 2005-05-20 | Snecma Moteurs | Turboreacteur avec un carenage stator dans la cavite sous chambre |
-
2006
- 2006-07-19 FR FR0606542A patent/FR2904047B1/fr active Active
-
2007
- 2007-06-22 EP EP07290779.3A patent/EP1881180B1/fr active Active
- 2007-07-16 CA CA2594146A patent/CA2594146C/fr active Active
- 2007-07-18 RU RU2007127556/06A patent/RU2446297C2/ru active
- 2007-07-18 JP JP2007186670A patent/JP4904592B2/ja active Active
- 2007-07-19 US US11/780,287 patent/US7937944B2/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4657482A (en) * | 1980-10-10 | 1987-04-14 | Rolls-Royce Plc | Air cooling systems for gas turbine engines |
US5555721A (en) * | 1994-09-28 | 1996-09-17 | General Electric Company | Gas turbine engine cooling supply circuit |
JPH108996A (ja) * | 1996-06-24 | 1998-01-13 | Nissan Motor Co Ltd | ガスタービンエンジン |
JP2001506342A (ja) * | 1996-12-23 | 2001-05-15 | プラット アンド ホイットニー カナダ インコーポレイテッド | スラストベアリング荷重制御装置を有するタービンエンジン |
US20030167775A1 (en) * | 2000-12-13 | 2003-09-11 | Soechting Friedrich O. | Vane platform trailing edge cooling |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008025580A (ja) * | 2006-07-19 | 2008-02-07 | Snecma | 遠心圧縮機のインペラの下流側空洞の冷却システム |
Also Published As
Publication number | Publication date |
---|---|
US7937944B2 (en) | 2011-05-10 |
FR2904047A1 (fr) | 2008-01-25 |
EP1881180A3 (fr) | 2008-09-17 |
CA2594146C (fr) | 2014-11-25 |
CA2594146A1 (fr) | 2008-01-19 |
FR2904047B1 (fr) | 2013-03-01 |
RU2446297C2 (ru) | 2012-03-27 |
EP1881180B1 (fr) | 2018-01-03 |
RU2007127556A (ru) | 2009-01-27 |
JP4904592B2 (ja) | 2012-03-28 |
US20080141680A1 (en) | 2008-06-19 |
EP1881180A2 (fr) | 2008-01-23 |
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