JPH10510908A - 燃焼機のライナ装置 - Google Patents
燃焼機のライナ装置Info
- Publication number
- JPH10510908A JPH10510908A JP8518880A JP51888096A JPH10510908A JP H10510908 A JPH10510908 A JP H10510908A JP 8518880 A JP8518880 A JP 8518880A JP 51888096 A JP51888096 A JP 51888096A JP H10510908 A JPH10510908 A JP H10510908A
- Authority
- JP
- Japan
- Prior art keywords
- liner
- shell
- panel
- pin
- shell portion
- 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
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
- F23R3/002—Wall structures
-
- 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
- F23R3/06—Arrangement of apertures along the flame tube
- F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/20—Heat transfer, e.g. cooling
- F05B2260/221—Improvement of heat transfer
- F05B2260/224—Improvement of heat transfer by increasing the heat transfer surface
- F05B2260/2241—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
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)
Abstract
Description
Claims (1)
- 【特許請求の範囲】 1.ガス流が内部を流通しているガスタービンエンジンの燃焼機のためのライナ 装置であって、 燃焼帯を形成する弓形のシェルを有し、前記シェルは、第一シェル部と、下流 側に隣接する第二シェル部と、をそれぞれ含む軸方向に配置された連続部を有し 、前記第二シェル部は、前記ガス流の流通方向に前記第一シェル部より分岐して おり、 第一浮動ライナを有し、前記第一浮動ライナは、前記第一シェル部に支持され て、この第一シェル部との間に空間部を形成し、シェルの周囲にセグメント化さ れて配置され、 前記第一ライナと前記第一シェルとの間の第一冷却空気流空間を有し、前記第 一冷却空気流空間は、前記ガス流に対して上流端及び下流端の双方で前記ガス流 と流体的に連通しており、 第二浮動ライナを有し、前記第二浮動ライナは、前記第二シェル部に支持され て、この第二シェル部との間に空間部を形成し、シェルの周囲にセグメント化さ れて配置され、 前記第二ライナと前記第二シェルとの間の第二冷却空気流空間を有し、前記第 二冷却空気流空間は、前記ガス流に対して上流端及び下流端の双方で前記ガス流 と流体的に連通しており、 前記第一ライナの下流端は、ガス側で前記第二ライナの上流端を覆い、 前記 第二空気流空間は、ガス流に対して下流端よりも上流端の方が、前記ライナに対 して垂直方向に小さくなっていることを特徴と するライナ装置。 2.前記第二浮動ライナは、複数の一体型のピンを有し、 前記ピンは、前記第二シェルに向かって伸びており、 前記ピンは、下流端よりも上流端の近くの方で短いことを特徴とする請求項1 記載のライナ装置。 3.上流端の前記ピンは、下流端のピンの3分の2の長さであることを特徴とす る請求項2記載のライナ装置。 4.前記ピンは、前記ピンと前記パネルの上流側端部との間に空隙部を有し、前 記ピンと前記パネルの下流側端部との間には空隙部を有していないことを特徴と する請求項2記載のライナ装置。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US08/356,089 | 1994-12-15 | ||
US08/356,089 US5461866A (en) | 1994-12-15 | 1994-12-15 | Gas turbine engine combustion liner float wall cooling arrangement |
PCT/US1995/015077 WO1996018849A1 (en) | 1994-12-15 | 1995-11-17 | Combustor liner arrangement |
Publications (2)
Publication Number | Publication Date |
---|---|
JPH10510908A true JPH10510908A (ja) | 1998-10-20 |
JP3689114B2 JP3689114B2 (ja) | 2005-08-31 |
Family
ID=23400086
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP51888096A Expired - Lifetime JP3689114B2 (ja) | 1994-12-15 | 1995-11-17 | 燃焼機のライナ装置 |
Country Status (5)
Country | Link |
---|---|
US (1) | US5461866A (ja) |
EP (1) | EP0797745B1 (ja) |
JP (1) | JP3689114B2 (ja) |
DE (1) | DE69509791T2 (ja) |
WO (1) | WO1996018849A1 (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2012132461A (ja) * | 2012-01-27 | 2012-07-12 | Mitsubishi Heavy Ind Ltd | ガスタービン |
Families Citing this family (35)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5577379A (en) * | 1994-12-15 | 1996-11-26 | United Technologies Corporation | Fuel nozzle guide retainer assembly |
JP4134513B2 (ja) * | 1997-09-12 | 2008-08-20 | 株式会社日立製作所 | ガスタービン燃焼器とそのライチ構造 |
US6042315A (en) * | 1997-10-06 | 2000-03-28 | United Technologies Corporation | Fastener |
US6045310A (en) * | 1997-10-06 | 2000-04-04 | United Technologies Corporation | Composite fastener for use in high temperature environments |
EP1312865A1 (de) * | 2001-11-15 | 2003-05-21 | Siemens Aktiengesellschaft | Ringbrennkammer für eine Gasturbine |
US6719524B2 (en) | 2002-02-25 | 2004-04-13 | Honeywell International Inc. | Method of forming a thermally isolated gas turbine engine housing |
US6638013B2 (en) | 2002-02-25 | 2003-10-28 | Honeywell International Inc. | Thermally isolated housing in gas turbine engine |
US7010921B2 (en) * | 2004-06-01 | 2006-03-14 | General Electric Company | Method and apparatus for cooling combustor liner and transition piece of a gas turbine |
GB2420614B (en) * | 2004-11-30 | 2009-06-03 | Alstom Technology Ltd | Tile and exo-skeleton tile structure |
US8051663B2 (en) * | 2007-11-09 | 2011-11-08 | United Technologies Corp. | Gas turbine engine systems involving cooling of combustion section liners |
US8109099B2 (en) * | 2008-07-09 | 2012-02-07 | United Technologies Corporation | Flow sleeve with tabbed direct combustion liner cooling air |
US8245514B2 (en) * | 2008-07-10 | 2012-08-21 | United Technologies Corporation | Combustion liner for a gas turbine engine including heat transfer columns to increase cooling of a hula seal at the transition duct region |
US8910378B2 (en) * | 2012-05-01 | 2014-12-16 | United Technologies Corporation | Method for working of combustor float wall panels |
US9239165B2 (en) | 2012-06-07 | 2016-01-19 | United Technologies Corporation | Combustor liner with convergent cooling channel |
US9335049B2 (en) | 2012-06-07 | 2016-05-10 | United Technologies Corporation | Combustor liner with reduced cooling dilution openings |
US9243801B2 (en) | 2012-06-07 | 2016-01-26 | United Technologies Corporation | Combustor liner with improved film cooling |
US9217568B2 (en) | 2012-06-07 | 2015-12-22 | United Technologies Corporation | Combustor liner with decreased liner cooling |
US9334756B2 (en) | 2012-09-28 | 2016-05-10 | United Technologies Corporation | Liner and method of assembly |
WO2015050879A1 (en) | 2013-10-04 | 2015-04-09 | United Technologies Corporation | Heat shield panels with overlap joints for a turbine engine combustor |
EP3058201B1 (en) * | 2013-10-18 | 2018-07-18 | United Technologies Corporation | Combustor wall having cooling element(s) within a cooling cavity |
EP3071885B1 (en) | 2013-11-21 | 2020-03-11 | United Technologies Corporation | Turbine engine multi-walled structure with internal cooling elements |
US10317078B2 (en) | 2013-11-21 | 2019-06-11 | United Technologies Corporation | Cooling a multi-walled structure of a turbine engine |
WO2015077592A1 (en) | 2013-11-22 | 2015-05-28 | United Technologies Corporation | Turbine engine multi-walled structure with cooling element(s) |
EP3967854B1 (en) | 2013-11-25 | 2023-07-05 | Raytheon Technologies Corporation | Assembly for a turbine engine |
EP3077724B1 (en) | 2013-12-05 | 2021-04-28 | Raytheon Technologies Corporation | Cooling a quench aperture body of a combustor wall |
WO2015084963A1 (en) | 2013-12-06 | 2015-06-11 | United Technologies Corporation | Cooling a quench aperture body of a combustor wall |
WO2015085069A1 (en) | 2013-12-06 | 2015-06-11 | United Technologies Corporation | Combustor quench aperture cooling |
US10968829B2 (en) | 2013-12-06 | 2021-04-06 | Raytheon Technologies Corporation | Cooling an igniter body of a combustor wall |
EP3077726B1 (en) | 2013-12-06 | 2021-03-03 | United Technologies Corporation | Cooling a combustor heat shield proximate a quench aperture |
EP3102883B1 (en) | 2014-02-03 | 2020-04-01 | United Technologies Corporation | Film cooling a combustor wall of a turbine engine |
WO2015117139A1 (en) | 2014-02-03 | 2015-08-06 | United Technologies Corporation | Stepped heat shield for a turbine engine combustor |
DE102014204482A1 (de) * | 2014-03-11 | 2015-09-17 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammer einer Gasturbine |
CN105333456B (zh) * | 2014-07-31 | 2017-11-10 | 中国航发商用航空发动机有限责任公司 | 用于火焰筒的浮动壁瓦块及其浮动壁 |
US10480787B2 (en) | 2015-03-26 | 2019-11-19 | United Technologies Corporation | Combustor wall cooling channel formed by additive manufacturing |
GB201603166D0 (en) * | 2016-02-24 | 2016-04-06 | Rolls Royce Plc | A combustion chamber |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4614082A (en) * | 1972-12-19 | 1986-09-30 | General Electric Company | Combustion chamber construction |
US4109459A (en) * | 1974-07-19 | 1978-08-29 | General Electric Company | Double walled impingement cooled combustor |
FR2340453A1 (fr) * | 1976-02-06 | 1977-09-02 | Snecma | Corps de chambre de combustion, notamment pour turboreacteurs |
US4302941A (en) * | 1980-04-02 | 1981-12-01 | United Technologies Corporation | Combuster liner construction for gas turbine engine |
GB2087065B (en) * | 1980-11-08 | 1984-11-07 | Rolls Royce | Wall structure for a combustion chamber |
US4567730A (en) * | 1983-10-03 | 1986-02-04 | General Electric Company | Shielded combustor |
US4790140A (en) * | 1985-01-18 | 1988-12-13 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Liner cooling construction for gas turbine combustor or the like |
JPH0752014B2 (ja) * | 1986-03-20 | 1995-06-05 | 株式会社日立製作所 | ガスタ−ビン燃焼器 |
FR2624953B1 (fr) * | 1987-12-16 | 1990-04-20 | Snecma | Chambre de combustion, pour turbomachines, possedant un convergent a doubles parois |
US5083422A (en) * | 1988-03-25 | 1992-01-28 | General Electric Company | Method of breach cooling |
US4916906A (en) * | 1988-03-25 | 1990-04-17 | General Electric Company | Breach-cooled structure |
US5123248A (en) * | 1990-03-28 | 1992-06-23 | General Electric Company | Low emissions combustor |
DE4239856A1 (de) * | 1992-11-27 | 1994-06-01 | Asea Brown Boveri | Gasturbinenbrennkammer |
-
1994
- 1994-12-15 US US08/356,089 patent/US5461866A/en not_active Expired - Lifetime
-
1995
- 1995-11-17 EP EP95944301A patent/EP0797745B1/en not_active Expired - Lifetime
- 1995-11-17 WO PCT/US1995/015077 patent/WO1996018849A1/en active IP Right Grant
- 1995-11-17 JP JP51888096A patent/JP3689114B2/ja not_active Expired - Lifetime
- 1995-11-17 DE DE69509791T patent/DE69509791T2/de not_active Expired - Lifetime
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2012132461A (ja) * | 2012-01-27 | 2012-07-12 | Mitsubishi Heavy Ind Ltd | ガスタービン |
Also Published As
Publication number | Publication date |
---|---|
US5461866A (en) | 1995-10-31 |
DE69509791T2 (de) | 1999-12-23 |
WO1996018849A1 (en) | 1996-06-20 |
JP3689114B2 (ja) | 2005-08-31 |
EP0797745A1 (en) | 1997-10-01 |
EP0797745B1 (en) | 1999-05-19 |
DE69509791D1 (de) | 1999-06-24 |
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