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31. 发明公开

EP1413738A3 Rakete 审中-公开
标题翻译：火箭
公开(公告)号：EP1413738A3
公开(公告)日：2006-12-27
申请号：EP03023629.3
申请日：2003-10-16
申请人： Blaschko, Siegfried
发明人： Blaschko, Siegfried
IPC分类号： F02K9/48 , F02K9/64 , F02K9/68 , F02C3/16 , F01D1/22 , F01D1/32 , F01D1/16
CPC分类号： F02C3/165 , F01D1/16 , F01D1/22 , F01D1/32 , F02K9/48 , F02K9/64 , F02K9/68
摘要： Ein Düsenantriebssystem umfasst eine Gasbeschleunigungsvorrichtung (2) zur Erzeugung von Druckgas und eine Antriebsdüse (40), die mit der Gasbeschleunigungsvorrichtung (2) verbunden ist und von ihr mit Druckluft versorgt wird, wobei die Gasbeschleunigungsvorrichtung (2) eine Gasbeschleunigungsturbine (4), einen Gasführungskanal (6) zur Führung eines Gasstromes, ein Druckgassammelrohr (8) und eine Gasrückführungsvorrichtung (10) zum Antrieb der Gasbeschleunigungsturbine (4) aufweist, und die Antriebsdüse eine Wirbelkammer (42) zur Erzeugung einer spiralförmigen Druckgasstromes, eine Dissoziationskammer (44) zur Dissoziation von Wasser, eine Verbrennungsvorrichtung (46) zur Verbrennung eines Treibstoffes, einen Kühlkreislauf (48) und eine Druckgasausstoßkammer (50) zur Erzeugung von Schub aufweist.

32. 发明授权

EP1352168B1 ROCKET ENGINE MEMBER AND METHOD FOR MANUFACTURING A ROCKET ENGINE MEMBER 有权
标题翻译：火箭发动机的四肢和生产火箭发动机元件方法
公开(公告)号：EP1352168B1
公开(公告)日：2006-06-21
申请号：EP02729605.2
申请日：2002-01-09
申请人： Volvo Aero Corporation
发明人： HÄGGANDER, Jan , BOMAN, Arne
IPC分类号： F02K9/64 , F02K9/97
CPC分类号： F02K9/64 , Y10T29/49346
摘要： The invention relates to a liquid fuel rocket engine member (10). The member has a load bearing wall structure (14) comprising a plurality of cooling channels (11). For improving the heat transfer, a material with a higher thermal conductivity than the load bearing wall structure (14) has been applied to the wall structure.

33. 发明授权

EP1352170B1 ROCKET ENGINE MEMBER AND A METHOD FOR MANUFACTURING A ROCKET ENGINE MEMBER 有权
标题翻译：火箭发动机的四肢和一种用于生产火箭发动机元件
公开(公告)号：EP1352170B1
公开(公告)日：2006-06-07
申请号：EP02729607.8
申请日：2002-01-09
申请人： Volvo Aero Corporation
发明人： HÄGGANDER, Jan
IPC分类号： F02K9/64 , F02K9/97
CPC分类号： B23P15/008 , F02K9/64 , F02K9/972 , F05D2230/12 , F05D2230/26 , F05D2260/22141 , F28F1/40 , F28F13/12 , Y10T29/49346
摘要： The invention relates to a liquid fuel rocket engine member. The member has a load bearing wall structure (11, 14) comprising a plurality of cooling channels (11) for handling a coolant flow. Each cooling channel (11) is provided with a flow guiding surface (15) extending at an angle to the cooling channel axis, for providing the axial coolant flow with an added radial directional flow component.

34. 发明授权

EP0927299B1 BRENNKAMMER UND VERFAHREN ZUR HERSTELLUNG EINER BRENNKAMMER 失效
标题翻译：燃烧室和一种用于生产燃烧室
公开(公告)号：EP0927299B1
公开(公告)日：2005-11-23
申请号：EP98937565.4
申请日：1998-07-10
申请人： Deutsches Zentrum für Luft- und Raumfahrt e.V.
发明人： HAIDN, Oskar , HALD, Hermann , LEZUO, Michael , WINKELMANN, Peter
IPC分类号： F02K9/64 , C04B35/80
CPC分类号： F02K9/64 , F02K9/972
摘要： So as to create a combustion chamber, especially for a rocket propulsion unit, comprising a combustion chamber, an inner casing surrounding said combustion chamber, an outer casing surrounding the inner casing and coolant channels embodied between the inner and outer casing, the casing of which has improved thermal resistance and a greater mechanical load-bearing capacity, the invention provides for the outer casing to be made of a fibro-ceramic material and for the inner casing to made of a fibro-ceramic material or graphite.

35. 发明授权

EP1187978B1 SCHUBKAMMER-ANORDNUNG 有权
标题翻译：推力室装置
公开(公告)号：EP1187978B1
公开(公告)日：2004-10-13
申请号：EP00947782.9
申请日：2000-06-06
申请人： EADS SPACE Transportation GmbH
发明人： SOWA, Armin
IPC分类号： F02K9/62 , F02K9/64
CPC分类号： F02K9/64 , B64G1/26 , B64G1/401 , F05D2230/90 , F05D2300/142 , F05D2300/143 , F05D2300/21 , F05D2300/502 , F05D2300/611
摘要： The invention relates to a thrust chamber assembly (1) comprising an expansion nozzle (5) and a combustion chamber wall (3) on which an injection head (7) is mounted. The portion of the combustion chamber wall (3) located close to the injection head (7) forms a preparation chamber wall (17), in which the fuel to be supplied for combustion firstly forms a cooling film. In addition, a heat conducting layer (40) is provided at least in the area located on the exterior of the preparation chamber wall (17). The inventive thrust chamber assembly also comprises a platinum or gold coating that prevents oxidation.

37. 发明授权

EP0916835B1 Closed loop cooled rocket engine 有权
标题翻译：火箭带有封闭冷却回路
公开(公告)号：EP0916835B1
公开(公告)日：2002-04-17
申请号：EP98120675.8
申请日：1998-11-05
申请人： TRW Inc.
发明人： Dressler, Gordon
IPC分类号： F02K9/64
CPC分类号： F02K9/64 , F05D2260/205

38. 发明公开

EP1025947A3 Method for producing a welded-brazed construction 有权
标题翻译：的制造焊接部件钎焊的方法
公开(公告)号：EP1025947A3
公开(公告)日：2002-01-16
申请号：EP99307037.4
申请日：1999-09-03
申请人： Otkrytoe Aktsionernoe Obschestvo Nauchno-Proizvodstvennoe Obiedinenie "Energomash", Imeni Akademika V.P. Glushko of Russian Fe
发明人： Semenov,Viktor Nikonorovich , Grigoriev,Anatoly Ivanovich, , Derkach,Gennady Grigorievitch, , Katorgin, Boris Ivanovich , Chvanov, Vladimir Konstantinovich, , Movchan, Jury Vasilievich, , Shashelova, Galina Vasilievna , Sagalovich, Vladimir Veniaminovich, , Baranov, Evgeny Ivanovich, , Tumanov, Leonid Alexeevich , Dudkin,Nikolai Kondratievich, , Anosova, Ljudmila Alexandrovna , Chernikova,Raisa Vasilievna , Vycherov, Alexandr Nikolaevich , Studenikin, Oleg Ivanovich, , Molev, Nikolai Fedorovich , Pestov, Jury Alexandrovich, , Bedov, Jury Alexandrovich , Vasin, Alexandr Alexandrovich , Bogushev, Vladimir Jurievich , Fedorov, Vladimir Vladimirovich , Grigorkin, Nikolai Mikhailovich , Babaeva,Galina Andreevna , Kamensky,Stanislav Dmitrievich
IPC分类号： B23K28/02 , B23K31/02 , F02K9/64
CPC分类号： F02K9/68 , B23K1/0018 , B23K1/0056 , B23K9/0026 , B23K15/0006 , Y10T29/49346
摘要： A combustion chamber for a liquid-propellant rocket engine comprises an injector head jointed to a combustion chamber casing having an exhaust head on a nozzle output. The casing is made of a steel jacket and a bronze-steel internal fire wall, which are joined with each other and contain shells connected in series. The exhaust head with shells of the casing, jointed to the exhaust head, are brazed using a solder on the basis of nickel, chromium and manganese. Parts of the injector head and other members of the combustion chamber casing are brazed using a copper-silver solder. Shells of the fire wall are connected by an electron-beam welding, directing an electron beam into axial gaps left while brazing between shells of the jacket. The shells of the jacket are then sequentially connected by an automatic gas-shielded arc welding through corresponding ring spacers.

39. 发明公开

EP1005949A1 Method of forming a rocket thrust chamber 有权
标题翻译：赫尔斯特朗·赫斯特伦
公开(公告)号：EP1005949A1
公开(公告)日：2000-06-07
申请号：EP99309528.0
申请日：1999-11-29
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Wright, Robert J.
IPC分类号： B23P15/00 , F02K9/64
CPC分类号： B23P15/008 , F02K9/972 , F02K9/974 , Y10T29/49346 , Y10T29/4935 , Y10T29/49982
摘要： Molten metal is sprayed onto the outer shell 32 of a cooling tube bundle 10, and the ends of tubes 18, 20 are covered with predetermined thicknesses of the metal 52, 54. Circumferentially extending manifold channels 60, 64 that intersect each of the tube ends 18, 20 are then machined into the predetermined thicknesses of metal, and mating assemblies 74, 76 are attached to enclose the manifold channels 60, 64.
摘要翻译：将熔融金属喷涂到冷却管束10的外壳32上，并且管18,20的端部被预定厚度的金属52,54覆盖。圆周延伸的歧管通道60,64与每个管端相交 18,20然后被加工成预定厚度的金属，并且配合组件74,76被附接以包围歧管通道60,64。

40. 发明公开

EP0916835A1 Closed loop cooled rocket engine 有权
标题翻译： Rakete mit geschlossenemKühlkreislauf
公开(公告)号：EP0916835A1
公开(公告)日：1999-05-19
申请号：EP98120675.8
申请日：1998-11-05
申请人： TRW Inc.
发明人： Dressler, Gordon
IPC分类号： F02K9/64
CPC分类号： F02K9/64 , F05D2260/205
摘要： A space craft's rocket engines are cooled by a recirculating cooling system containing a non-propellant coolant fluid, such as water and/or ethylene glycol. With that recirculating cooling system to maintain the rocket engine combustion chamber at a lower temperature, spacecraft rocket engines may be constructed less expensively and can operate with greater safety by employing the more common metals in their construction. The cooling system also provides an easy means to warm and/or vaporize a propellant.
摘要翻译：太空飞船的火箭发动机由包含非推进剂冷却剂流体（例如水和/或乙二醇）的循环冷却系统冷却。利用这种循环冷却系统将火箭发动机燃烧室维持在较低的温度下，可以使用较低成本的太空船火箭发动机，并且通过在其结构中采用更常见的金属可以更高的安全性运行。冷却系统还提供了一种用于温热和/或蒸发推进剂的简单方法。

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