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1. 发明公开

EP2933469A1 VERFAHREN UND VORRICHTUNG ZUR HERSTELLUNG EINER HOCHEMISSIVEN OBERFLÄCHENSTRUKTUR EINER STRAHLUNGSGEKÜHLTEN BRENNKAMMER 有权转让
标题翻译：设计用于产生辐射HOCHEMISSIVEN的表面构造的方法和装置冷却燃烧室
公开(公告)号：EP2933469A1
公开(公告)日：2015-10-21
申请号：EP15001125.2
申请日：2015-04-17
申请人： Airbus DS GmbH
发明人： Kraus, Stephan , Hartmann, Gerhard , Riehle, Martin , Caesar, Christoph
IPC分类号： F02K9/40 , F02K9/64
摘要： Die Erfindung betrifft ein Verfahren zur Herstellung einer Oberflächenstruktur einer strahlungsgekühlten Brennkammer (10) eines Raketentriebwerks, bei dem eine Strukturierung der radial nach außen gewandten Brennkammeroberfläche (17) mit einem gepulsten, optisch gepumpten Festkörperlaser (30) erfolgt, wobei als Strukturierung ein Muster aus einer Vielzahl von einzelnen Vertiefungen erzeugt wird.
摘要翻译：本发明涉及的制造方法，其中，朝向径向向外的燃烧室表面（17）的结构化用脉冲，光泵浦固态激光器（30）进行了火箭发动机的辐射冷却的燃烧室（10）的表面结构，作为一个结构化的图案多种由单独的孔中产生的。

2. 发明公开

EP2693033A4 AIRCRAFT/SPACECRAFT FLUID COOLING SYSTEM AND AIRCRAFT/SPACECRAFT FLUID COOLING DEVICE 审中-公开
标题翻译：液体冷却系统，用于飞机/飞行器飞机/太空飞行器和油冷却器
公开(公告)号：EP2693033A4
公开(公告)日：2015-01-14
申请号：EP12762853
申请日：2012-03-21
申请人： MITSUBISHI HEAVY IND LTD
发明人： KITAYAMA OSAMU , ISHIKAWA KEITARO , MIHARA YORICHIKA , AOYAMA TAICHI , NISHIMURA SHINJI
IPC分类号： F02K9/40 , B64G1/00 , B64G1/40 , F02K9/32 , F02K9/60 , F02K9/64 , F28D7/10
CPC分类号： F28F1/00 , B64G1/402 , F02C1/08 , F02C7/16 , F02C7/18 , F02C7/185 , F02C7/224 , F02K9/34 , F02K9/40 , F02K9/46 , F02K9/48 , F02K9/60 , F02K9/64 , F02K9/972 , F05D2260/20 , F28D7/106 , F28F2265/26
摘要： Provided are an aircraft/spacecraft fluid cooling system and an aircraft/spacecraft fluid cooling method in which a fluid in a pipe installed in aircraft or spacecraft can be cooled efficiently so that the amount of fluid required for cooling the fluid can be reduced. A fluid cooling system (1) includes a feed line (6) that feeds a fluid from a storage tank (4) to a pump (8), and a cooling section (26) that expands a propellant having traveled through the pump (8), feeds the propellant to the outer periphery of the feed line (6) so as to cool the propellant in the feed line (6), and discharges the expanded propellant outside.

3. 发明公开

EP4211343A1 SCHUBKAMMERVORRICHTUNG UND VERFAHREN ZUM BETREIBEN EINER SCHUBKAMMERVORRICHTUNG 审中-实审
公开(公告)号：EP4211343A1
公开(公告)日：2023-07-19
申请号：EP21773752.7
申请日：2021-09-08
申请人： Deutsches Zentrum für Luft- und Raumfahrt e.V.
发明人： ORTELT, Markus
IPC分类号： F02K9/40 , F02K9/48 , F02K9/52 , F02K9/97

4. 发明公开

EP3255271A1 COOLING MECHANISM FOR COMBUSTION CHAMBER, ROCKET ENGINE PROVIDED WITH COOLING MECHANISM, AND COOLING MECHANISM PRODUCTION METHOD 有权转让
标题翻译：燃烧室，火箭发动机提供冷却机构的冷却机构及冷却机构生产方法
公开(公告)号：EP3255271A1
公开(公告)日：2017-12-13
申请号：EP16761794.3
申请日：2016-03-09
申请人： Mitsubishi Heavy Industries, Ltd. , Japan Aerospace Exploration Agency
发明人： WATANABE Daiki , ADACHI Masaki , KOBAYASHI Hiroyuki , KUROSU Akihide , KAWASHIMA Hideto , NEGORO Nobuki
IPC分类号： F02K9/64 , F02K9/40
CPC分类号： F02K9/64 , F02K9/40 , F05D2260/2212 , F05D2260/2214 , F23M5/08 , F23R3/005 , F23R2900/03043
摘要： The present invention is provided with a floor wall (22) that is in contact with a combustion chamber, an upper wall (30), and a cooling flow path (40) that is disposed between the floor wall (22) and the upper wall (30). The cooling flow path (40) is provided with a first flow path (50) that extends in a first direction, a second flow path (60) that extends in the first direction, and a connection part (70) that is connected to the first flow path (50) and the second flow path (60). The second flow path (60) goes along the floor wall (22) relative to the first flow path (50) and is disposed offset in a second direction perpendicular to the first direction.
摘要翻译：本发明设有与燃烧室接触的底壁（22），上壁（30）以及设置在底壁（22）与上壁之间的冷却流路（40）（30）。冷却流路（40）具备：沿第一方向延伸的第一流路（50）;沿第一方向延伸的第二流路（60）;以及连接部（70），连接部第一流动路径（50）和第二流动路径（60）。第二流动路径（60）相对于第一流动路径（50）沿着底壁（22）行进并且在垂直于第一方向的第二方向上偏移地设置。

5. 发明公开

EP2103799A3 Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine 有权
标题翻译： Raketenschubdüseund Steuerungsverfahren derAbgasströmung在einem Raketentriebwerk
公开(公告)号：EP2103799A3
公开(公告)日：2013-06-26
申请号：EP08162393.6
申请日：2008-08-14
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Kimura, Tatsuya , Kawamata, Yoshihiro , Niu, Kenichi
IPC分类号： F02K9/97 , F02K9/40 , F02K9/48 , F02K9/82 , F02K1/38
CPC分类号： F02K1/38 , F02K9/48 , F02K9/58 , F02K9/82 , F02K9/972 , F05D2250/713
摘要： A rocket nozzle (8) includes a dual-bell nozzle (10) and a gas introducing section (40A, 40B, 40C, 40D) configured to introduce gas into space (80) surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle (20) bell-shaped and surrounding an upstream portion (81) of the space, and a second stage nozzle (30) bell-shaped and surrounding a downstream portion (82) of the space. The dual-bell nozzle has an inflection point (12) between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet (45, 63) provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.
摘要翻译：火箭喷嘴（8）包括双钟形喷嘴（10）和被配置为将气体引入由双钟形喷嘴包围的空间（80）中的气体引入部分（40A，40B，40C，40D）。燃烧气体在空间流动。双钟形喷嘴包括钟形的第一级喷嘴（20）并且围绕该空间的上游部分（81），并且第二级喷嘴（30）是钟形的并围绕该空间的下游部分（82）。双钟形喷嘴在第一级喷嘴和第二级喷嘴之间具有拐点（12）。气体导入部包括设置在第一级喷嘴的内壁面的气体入口（45,63）。气体从气体入口引入空间。

6. 发明授权

EP1080302B1 MODULARE FESTSTOFFRAKETENTREIBSÄTZE MIT UMMANTELUNG, FILL-DRAIN SYSTEM, KÜHLUNG UND AUFHÄNGUNG 有权
标题翻译：与环绕模块化固体火箭DRIVE套件，填漏系统，冷却和暂停
公开(公告)号：EP1080302B1
公开(公告)日：2002-07-03
申请号：EP99936294.0
申请日：1999-05-18
申请人： Lo, Roger E.
发明人： Lo, Roger E.
IPC分类号： F02K9/10 , F02K9/34 , F02K9/40 , F02K9/36 , C06B45/00
CPC分类号： F02K9/40 , F02K9/00 , F02K9/10 , F02K9/32 , F02K9/36
摘要： The invention relates to modular solid-fuel rocket propelling charges comprising different propellant components and other components, for example, fuels, oxidators, energy increasing admixtures, binders, additives, coatings, inhibitors, etc. which can be completely or partially fragmented, i.e. they are not provided in the form of the conventional quasi homogeneous mixture, rather they are available in the form of one or more macroscopic combustible elements having any appropriate configuration. All or individual components can also be comprised of substances which must first be sufficiently brought to a solid state by cooling. The aim of the invention is to provide modular solid-fuel rocket propelling charges of the aforementioned type such that the development of dangerous situations resulting from a cooling failure during simultaneous power increases of the carrier rockets is drastically minimized. To this end, the modules are provided as an assembly or the individual combustible elements thereof are provided with a special casing (1). Said special casing permits the storage of such propelling charges and/or the operation thereof according to prescription in such a way that problems do not occur due to the dependence on temperature of the mechanical characteristics or of the state of the aggregate.

7. 发明授权

EP4058667B1 TRIEBWERKANORDNUNG UND VERFAHREN ZUM BETREIBEN EINER TRIEBWERKANORDNUNG MIT DURCHFLUSSBATTERIEANORDNUNG 有权
公开(公告)号：EP4058667B1
公开(公告)日：2024-06-26
申请号：EP20800093.5
申请日：2020-10-29
IPC分类号： F02K9/40 , F02K9/46 , H01M8/18
CPC分类号： F02K9/40 , F02K9/46 , H01M8/188 , H01M2250/2020130101 , H01M2250/4020130101 , Y02T90/40 , Y02E60/50

8. 发明公开

EP3684691A1 EMERGENCY LANDING OF AIRCRAFT 审中-公开
公开(公告)号：EP3684691A1
公开(公告)日：2020-07-29
申请号：EP18795772.5
申请日：2018-10-19
申请人： Active Vtol Crash Prevention Limited
发明人： SLOMAN, Roger Mark
IPC分类号： B64D25/00 , F02K9/40 , B64D17/72 , B64D1/16 , B64C15/14 , B64D17/80

9. 发明公开

EP3255271A4 COOLING MECHANISM FOR COMBUSTION CHAMBER, ROCKET ENGINE PROVIDED WITH COOLING MECHANISM, AND COOLING MECHANISM PRODUCTION METHOD 有权转让
公开(公告)号：EP3255271A4
公开(公告)日：2018-03-21
申请号：EP16761794
申请日：2016-03-09
申请人： MITSUBISHI HEAVY IND LTD , JAPAN AEROSPACE EXPLORATION
发明人： WATANABE DAIKI , ADACHI MASAKI , KOBAYASHI HIROYUKI , KUROSU AKIHIDE , KAWASHIMA HIDETO , NEGORO NOBUKI
IPC分类号： F02K9/64 , F02K9/40 , F23M5/08 , F23R3/00
CPC分类号： F02K9/64 , F02K9/40 , F05D2260/2212 , F05D2260/2214 , F23M5/08 , F23R3/005
摘要： The present invention is provided with a floor wall (22) that is in contact with a combustion chamber, an upper wall (30), and a cooling flow path (40) that is disposed between the floor wall (22) and the upper wall (30). The cooling flow path (40) is provided with a first flow path (50) that extends in a first direction, a second flow path (60) that extends in the first direction, and a connection part (70) that is connected to the first flow path (50) and the second flow path (60). The second flow path (60) goes along the floor wall (22) relative to the first flow path (50) and is disposed offset in a second direction perpendicular to the first direction.

10. 发明公开

EP2391802A1 REACTEUR NOTAMMENT UN REACTEUR POUR AERONEF 审中-公开
标题翻译：与等容烧伤飞机的喷气发动机
公开(公告)号：EP2391802A1
公开(公告)日：2011-12-07
申请号：EP10700712.2
申请日：2010-01-15
申请人： Aguilar, Michel
发明人： Aguilar, Michel
IPC分类号： F01D17/14 , F02C5/12 , F02K9/40 , F02K7/02
CPC分类号： F01D17/14 , F02C5/12 , F02K7/067 , F02K9/40
摘要： The invention relates to a jet engine (1), in particular an aircraft jet engine, including at least one combustion chamber (3). The combustion chamber (3) is connected to at least one compressed gas intake (4) and to at least one burnt gas outlet (5). Said burnt gas outlet(s) (5) include an exhaust valve. The exhaust valve includes two rotary parts (7), referred to as rotary exhaust parts, the rotary exhaust parts (7) including curved walls (8) and intermediate walls (9) connecting the curved walls (8), and rotating in a coordinated, continuous fashion such that said valve is in a closed position in order to block the gas during at least one combustion step, and in an open position in order to define a space (10) through which the gas flows out from the combustion chamber (3) during at least one expansion step.

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