JP2005513322A5 - - Google Patents
Download PDFInfo
- Publication number
- JP2005513322A5 JP2005513322A5 JP2003553114A JP2003553114A JP2005513322A5 JP 2005513322 A5 JP2005513322 A5 JP 2005513322A5 JP 2003553114 A JP2003553114 A JP 2003553114A JP 2003553114 A JP2003553114 A JP 2003553114A JP 2005513322 A5 JP2005513322 A5 JP 2005513322A5
- Authority
- JP
- Japan
- 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
Applications Claiming Priority (3)
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 |
PCT/SE2002/002085 WO2003052255A1 (en) | 2001-12-18 | 2002-11-15 | A component for being subjected to high thermal load during operation and a method for manufacturing such a component |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2005513322A JP2005513322A (ja) | 2005-05-12 |
JP2005513322A5 true JP2005513322A5 (ja) | 2005-12-22 |
JP4452919B2 JP4452919B2 (ja) | 2010-04-21 |
Family
ID=26655628
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2003553114A Expired - Fee Related JP4452919B2 (ja) | 2001-12-18 | 2002-11-15 | 動作中に高い熱負荷を受ける構成部品及びそのような構成部品を製造する方法 |
Country Status (9)
Country | Link |
---|---|
US (1) | US7299622B2 (ja) |
EP (1) | EP1458968B1 (ja) |
JP (1) | JP4452919B2 (ja) |
AT (1) | ATE367519T1 (ja) |
AU (1) | AU2002347745A1 (ja) |
DE (1) | DE60221284T2 (ja) |
ES (1) | ES2290344T3 (ja) |
RU (1) | RU2289035C2 (ja) |
WO (1) | WO2003052255A1 (ja) |
Families Citing this family (27)
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 |
WO2007030038A1 (en) * | 2005-09-06 | 2007-03-15 | Volvo Aero Corporation | An engine wall structure and a method of producing an engine wall structure |
DE602005023223D1 (de) * | 2005-09-06 | 2010-10-07 | Volvo Aero Corp | 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 |
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 |
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 |
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 |
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 |
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 |
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 |
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 |
US5363643A (en) * | 1993-02-08 | 1994-11-15 | General Electric Company | Segmented combustor |
US5333443A (en) * | 1993-02-08 | 1994-08-02 | General Electric Company | Seal assembly |
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 |
ATE393875T1 (de) * | 2001-01-11 | 2008-05-15 | Volvo Aero Corp | Raketentriebwerksglied und ein verfahren zur herstellung eines raketentriebwerksglieds |
US6701714B2 (en) * | 2001-12-05 | 2004-03-09 | United Technologies Corporation | Gas turbine combustor |
-
2002
- 2002-11-15 EP EP02783945A patent/EP1458968B1/en not_active Expired - Lifetime
- 2002-11-15 AT AT02783945T patent/ATE367519T1/de not_active IP Right Cessation
- 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 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 JP JP2003553114A patent/JP4452919B2/ja not_active Expired - Fee Related
- 2002-11-15 AU AU2002347745A patent/AU2002347745A1/en not_active Abandoned
-
2004
- 2004-06-18 US US10/710,108 patent/US7299622B2/en not_active Expired - Lifetime