ATE367519T1 - Bauteil zur beaufschlagung mit hoher thermischer belastung beim betrieb und verfahren zur herstellung eines solchen bauteils - Google Patents
Bauteil zur beaufschlagung mit hoher thermischer belastung beim betrieb und verfahren zur herstellung eines solchen bauteilsInfo
- Publication number
- ATE367519T1 ATE367519T1 AT02783945T AT02783945T ATE367519T1 AT E367519 T1 ATE367519 T1 AT E367519T1 AT 02783945 T AT02783945 T AT 02783945T AT 02783945 T AT02783945 T AT 02783945T AT E367519 T1 ATE367519 T1 AT E367519T1
- Authority
- AT
- Austria
- Prior art keywords
- component
- during operation
- high thermal
- thermal load
- load during
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/343—Joints, connections, seals therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/972—Fluid cooling arrangements for nozzles
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)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Processing And Handling Of Plastics And Other Materials For Molding In General (AREA)
- Physical Or Chemical Processes And Apparatus (AREA)
- Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US34049001P | 2001-12-18 | 2001-12-18 | |
SE0104273A SE520669C2 (sv) | 2001-12-18 | 2001-12-18 | En komponent avsedd att utsättas för hög termisk last vid drift, och ett förfarande för tillverkning av en sådan komponent |
Publications (1)
Publication Number | Publication Date |
---|---|
ATE367519T1 true ATE367519T1 (de) | 2007-08-15 |
Family
ID=26655628
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
AT02783945T ATE367519T1 (de) | 2001-12-18 | 2002-11-15 | Bauteil zur beaufschlagung mit hoher thermischer belastung beim betrieb und verfahren zur herstellung eines solchen bauteils |
Country Status (9)
Country | Link |
---|---|
US (1) | US7299622B2 (de) |
EP (1) | EP1458968B1 (de) |
JP (1) | JP4452919B2 (de) |
AT (1) | ATE367519T1 (de) |
AU (1) | AU2002347745A1 (de) |
DE (1) | DE60221284T2 (de) |
ES (1) | ES2290344T3 (de) |
RU (1) | RU2289035C2 (de) |
WO (1) | WO2003052255A1 (de) |
Families Citing this family (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7188417B2 (en) * | 2002-06-28 | 2007-03-13 | United Technologies Corporation | Advanced L-channel welded nozzle design |
EP1398569A1 (de) * | 2002-09-13 | 2004-03-17 | Siemens Aktiengesellschaft | Gasturbine |
DE10343049B3 (de) * | 2003-09-16 | 2005-04-14 | Eads Space Transportation Gmbh | Brennkammer mit Kühleinrichtung und Verfahren zur Herstellung der Brennkammer |
US7596940B2 (en) * | 2005-03-22 | 2009-10-06 | Pratt & Whitney Rocketdyne, Inc. | Rocket engine nozzle and method of fabricating a rocket engine nozzle using pressure brazing |
ES2350847T3 (es) * | 2005-09-06 | 2011-01-27 | Volvo Aero Corporation | Procedimiento para la fabricación de una estructura de pared de un motor. |
EP1926904A4 (de) * | 2005-09-06 | 2013-04-10 | Volvo Aero Corp | Motorwandstruktur und verfahren zur herstellung einer motorwandstruktur |
SE531857C2 (sv) * | 2007-12-21 | 2009-08-25 | Volvo Aero Corp | En komponent avsedd att utsättas för hög termisk last vid drift |
DE102008011502A1 (de) * | 2008-02-25 | 2009-09-03 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Düsenerweiterung und Verfahren zur Herstellung einer Düsenerweiterung |
FR2962493B1 (fr) * | 2010-07-09 | 2014-05-16 | Snecma | Chambre de propulsion de moteur-fusee et procede de fabrication d'une telle chambre |
RU2511942C1 (ru) * | 2013-03-18 | 2014-04-10 | Николай Борисович Болотин | Система охлаждения камеры жидкостного ракетного двигателя |
JP6481978B2 (ja) | 2015-03-10 | 2019-03-13 | 三菱重工業株式会社 | 燃焼室の冷却機構、冷却機構を備えるロケットエンジン、及び、冷却機構の製造方法 |
FR3042542B1 (fr) * | 2015-10-20 | 2017-12-01 | Snecma | Chambre propulsive et procede de fabrication |
RU168808U1 (ru) * | 2016-04-20 | 2017-02-21 | Акционерное общество "НПО Энергомаш имени академика В.П. Глушко" | Корпус газовода жидкостного ракетного двигателя с дожиганием генераторного газа |
CN108060990A (zh) * | 2016-11-07 | 2018-05-22 | 贾海亮 | 一种串联单机固体发动机 |
US10739001B2 (en) * | 2017-02-14 | 2020-08-11 | Raytheon Technologies Corporation | Combustor liner panel shell interface for a gas turbine engine combustor |
US10830434B2 (en) | 2017-02-23 | 2020-11-10 | Raytheon Technologies Corporation | Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor |
US10823411B2 (en) | 2017-02-23 | 2020-11-03 | Raytheon Technologies Corporation | Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor |
US10718521B2 (en) | 2017-02-23 | 2020-07-21 | Raytheon Technologies Corporation | Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor |
US10677462B2 (en) | 2017-02-23 | 2020-06-09 | Raytheon Technologies Corporation | Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor |
US10941937B2 (en) | 2017-03-20 | 2021-03-09 | Raytheon Technologies Corporation | Combustor liner with gasket for gas turbine engine |
CN107023419B (zh) * | 2017-05-03 | 2019-05-03 | 湖北航天技术研究院总体设计所 | 一种固体火箭发动机燃烧室壳体轻质接头 |
US20190329355A1 (en) * | 2018-04-27 | 2019-10-31 | United States Of America As Represented By The Administrator Of Nasa | Method for Fabricating Seal-Free Multi-Metallic Thrust Chamber Liner |
US11448163B1 (en) * | 2018-09-05 | 2022-09-20 | Abl Space Systems | Multi-part fluid chamber and method of manufacturing |
CN110578619A (zh) * | 2019-09-29 | 2019-12-17 | 上海空间推进研究所 | 液体火箭发动机再生冷却身部及其槽道结构 |
FR3110483B1 (fr) * | 2020-05-20 | 2022-06-03 | Arianegroup Sas | Structure d’assemblage d’une pièce comprenant une première partie métallique et une deuxième partie en matériau composite à matrice organique |
KR102468746B1 (ko) * | 2020-11-18 | 2022-11-18 | 한국항공우주연구원 | 열교환 구조를 포함하는 연소기 및 이를 포함하는 로켓 |
CN112462714B (zh) * | 2020-12-01 | 2021-08-24 | 陕西蓝箭航天技术有限公司 | 航天器推力室双层结构的加工方法 |
JP2023065163A (ja) | 2021-10-27 | 2023-05-12 | インターステラテクノロジズ株式会社 | ロケットエンジンの燃焼器及びその製造方法 |
CN114991998B (zh) * | 2022-04-28 | 2024-08-13 | 北京航天动力研究所 | 分段式液体火箭发动机推力室扩散焊身部结构及焊接方法 |
Family Cites Families (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3126702A (en) * | 1964-03-31 | newcomb | ||
US3066702A (en) * | 1959-05-28 | 1962-12-04 | United Aircraft Corp | Cooled nozzle structure |
US3224678A (en) * | 1962-10-04 | 1965-12-21 | Marquardt Corp | Modular thrust chamber |
US3695515A (en) * | 1967-07-19 | 1972-10-03 | Karl Stockel | Fluid cooled thrust nozzle for a rocket |
US3605412A (en) * | 1968-07-09 | 1971-09-20 | Bolkow Gmbh | Fluid cooled thrust nozzle for a rocket |
US3630449A (en) * | 1970-05-11 | 1971-12-28 | Us Air Force | Nozzle for rocket engine |
US4555901A (en) * | 1972-12-19 | 1985-12-03 | General Electric Company | Combustion chamber construction |
DE2356572C3 (de) * | 1973-11-13 | 1979-03-29 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Flüssigkeitsgekühlte Raketenbrennkammer mit Schubdüse |
DE2949522C2 (de) * | 1979-12-08 | 1982-01-28 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Gekühlte Schubdüse für ein Raketentriebwerk |
US4655044A (en) * | 1983-12-21 | 1987-04-07 | United Technologies Corporation | Coated high temperature combustor liner |
US4622821A (en) * | 1985-01-07 | 1986-11-18 | United Technologies Corporation | Combustion liner for a gas turbine engine |
US5435139A (en) * | 1991-03-22 | 1995-07-25 | Rolls-Royce Plc | Removable combustor liner for gas turbine engine combustor |
GB2257781B (en) * | 1991-04-30 | 1995-04-12 | Rolls Royce Plc | Combustion chamber assembly in a gas turbine engine |
US5467528A (en) * | 1991-12-23 | 1995-11-21 | United Technologies Corporation | Method of making a tubular thermal structure |
US5333443A (en) * | 1993-02-08 | 1994-08-02 | General Electric Company | Seal assembly |
US5363643A (en) * | 1993-02-08 | 1994-11-15 | General Electric Company | Segmented combustor |
DE19505357C1 (de) * | 1995-02-17 | 1996-05-23 | Daimler Benz Aerospace Ag | Verfahren zur Kühlung von Triebwerkswänden und Wandstruktur zur Durchführung desselben |
GB2298267B (en) * | 1995-02-23 | 1999-01-13 | Rolls Royce Plc | An arrangement of heat resistant tiles for a gas turbine engine combustor |
US5704208A (en) * | 1995-12-05 | 1998-01-06 | Brewer; Keith S. | Serviceable liner for gas turbine engine |
US5832719A (en) * | 1995-12-18 | 1998-11-10 | United Technologies Corporation | Rocket thrust chamber |
SE512942C2 (sv) * | 1998-10-02 | 2000-06-12 | Volvo Aero Corp | Förfarande för tillverkning av utloppsmunstycken för raketmotorer |
RU2158666C2 (ru) * | 1999-02-04 | 2000-11-10 | Открытое акционерное общество НПО Энергомаш им. акад. В.П. Глушко | Способ изготовления сварно-паяной конструкции |
RU2274763C2 (ru) * | 2001-01-11 | 2006-04-20 | Вольво Аэро Корпорейшн | Элемент ракетного двигателя и способ изготовления такого элемента ракетного двигателя |
US6701714B2 (en) * | 2001-12-05 | 2004-03-09 | United Technologies Corporation | Gas turbine combustor |
-
2002
- 2002-11-15 DE DE60221284T patent/DE60221284T2/de not_active Expired - Lifetime
- 2002-11-15 WO PCT/SE2002/002085 patent/WO2003052255A1/en active IP Right Grant
- 2002-11-15 AT AT02783945T patent/ATE367519T1/de not_active IP Right Cessation
- 2002-11-15 AU AU2002347745A patent/AU2002347745A1/en not_active Abandoned
- 2002-11-15 RU RU2004122402/06A patent/RU2289035C2/ru not_active IP Right Cessation
- 2002-11-15 ES ES02783945T patent/ES2290344T3/es not_active Expired - Lifetime
- 2002-11-15 EP EP02783945A patent/EP1458968B1/de not_active Expired - Lifetime
- 2002-11-15 JP JP2003553114A patent/JP4452919B2/ja not_active Expired - Fee Related
-
2004
- 2004-06-18 US US10/710,108 patent/US7299622B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
US7299622B2 (en) | 2007-11-27 |
RU2289035C2 (ru) | 2006-12-10 |
EP1458968A1 (de) | 2004-09-22 |
RU2004122402A (ru) | 2005-07-10 |
US20050188678A1 (en) | 2005-09-01 |
AU2002347745A1 (en) | 2003-06-30 |
DE60221284T2 (de) | 2008-04-10 |
DE60221284D1 (de) | 2007-08-30 |
ES2290344T3 (es) | 2008-02-16 |
WO2003052255A1 (en) | 2003-06-26 |
JP4452919B2 (ja) | 2010-04-21 |
EP1458968B1 (de) | 2007-07-18 |
JP2005513322A (ja) | 2005-05-12 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
RER | Ceased as to paragraph 5 lit. 3 law introducing patent treaties |