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1. 发明授权

EP2867492B1 TURBINE WHEEL CATCHER 有权转让
公开(公告)号：EP2867492B1
公开(公告)日：2018-08-15
申请号：EP13810378.3
申请日：2013-06-27
申请人： United Technologies Corporation
发明人： ALEXANDER, Eric, J. , HAGSHENAS, Behzad , ELGIN, Richard, L.
IPC分类号： F02C7/00 , F02C7/20 , F02C7/32 , F02C3/00 , F01D21/04 , F01D25/00
CPC分类号： F01D25/00 , F01D9/04 , F01D21/045 , F05D2220/3215 , F05D2220/50 , F05D2240/14
摘要： A catcher for a gas turbine engine includes a central hub, a plurality of struts, and a first ring. The plurality of struts are connected to and extend outward from the central hub. The first ring is connected to a mid-section of the plurality of struts and extends therebetween.

2. 发明公开

EP3333403A1 BOUNDARY LAYER EXCITATION AFT FAN GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3333403A1
公开(公告)日：2018-06-13
申请号：EP17206030.3
申请日：2017-12-07
申请人： United Technologies Corporation
发明人： SUCIU, Gabriel L. , CHANDLER, Jesse M.
IPC分类号： F02K3/062 , B64D27/20 , F02C3/10
CPC分类号： F02C6/08 , B64C2230/04 , B64D27/20 , B64D33/02 , B64D2033/0226 , F02C3/10 , F02C3/20 , F02C7/36 , F02K3/06 , F02K3/062 , F05D2220/323 , F05D2220/50 , F05D2220/76
摘要： A boundary layer ingestion engine (120, 300, 400) includes a gas generator (130, 310) and a turbine fluidly connected to the gas generator (130, 310). A fan (330, 406) is mechanically linked to the turbine (140, 320) via a shaft (322) such that rotation of the turbine (140, 320) is translated to the fan (330, 406). A boundary layer ingestion inlet (122, 342, 404) is aligned with an expected boundary layer, such that the boundary layer ingestion inlet (122, 342, 404) is configured to ingest fluid from a boundary layer during operation of the boundary layer ingestion engine (120, 300, 400).

3. 发明授权

EP3063067B1 PROCÉDÉ ET SYSTÈME DE GÉNÉRATION DE PUISSANCE AUXILIAIRE DANS UN AÉRONEF 有权
标题翻译：在飞机中辅助发电的方法和系统
公开(公告)号：EP3063067B1
公开(公告)日：2018-05-02
申请号：EP14825386.7
申请日：2014-10-29
申请人： Safran Power Units
发明人： RIDEAU, Jean-François
IPC分类号： B64D41/00 , F02C7/26 , F02C7/268 , F02C7/275
CPC分类号： B64D41/00 , B64D2041/002 , F01D19/00 , F02C7/26 , F02C7/32 , F04B35/06 , F04C18/0215 , F04C18/16 , F04C23/02 , F05D2220/50

4. 发明授权

EP3208429B1 SYSTÈME ET PROCÉDÉ DE DÉMARRAGE DES MOTEURS D'UN AÉRONEF BIMOTEUR 有权
标题翻译：用于启动双翼飞机发动机的系统和方法
公开(公告)号：EP3208429B1
公开(公告)日：2018-04-11
申请号：EP17154682.3
申请日：2017-02-03
申请人： Airbus Operations S.A.S. , Airbus (S.A.S.)
发明人： BROUSSE, Pierre-Henri , LOZACH, Damien , MANNEVILLE, Alexis , MOLLIET, Christine , ROUX, Paul-Emile , ZACCARIA, Patrick
IPC分类号： F01D19/02 , F02C7/26 , F02C9/28
CPC分类号： B64D31/12 , F01D19/02 , F02C7/264 , F02C7/268 , F02C7/27 , F02C9/42 , F05D2220/323 , F05D2220/50 , F05D2240/20 , F05D2240/40 , F05D2260/85 , F05D2260/941

5. 发明公开

EP2520763A3 Impeller 有权
标题翻译：叶轮
公开(公告)号：EP2520763A3
公开(公告)日：2018-03-28
申请号：EP12166620.0
申请日：2012-05-03
申请人： Rafael Advanced Defense Systems Ltd.
发明人： Bronfeld, Yakov , Khosid, Savely
IPC分类号： F01D5/06 , F02C3/04 , F02K3/06 , F01D5/04 , F01D5/02
CPC分类号： F04D19/002 , F01D5/02 , F01D5/048 , F01D5/06 , F01D5/142 , F02C3/04 , F02K3/06 , F04D17/025 , F04D17/16 , F04D29/284 , F04D29/321 , F05D2220/50 , F05D2230/21 , F05D2230/53 , F05D2250/80 , Y02T50/673
摘要： A combined fan-compressor impeller comprises a single hub and a plurality of spaced main blades extending outwardly from the hub such that an air passage channel is defined between two of the main blades. Each of the main blades is a mixed flow blade which continuously extends from a fan section at an inlet end of a channel to a compressor section at an outlet end of the channel without any axial clearance between the fan section and the compressor section, providing aerodynamic matching of pressurized air flowing through the channel from the fan section to the compressor section.
摘要翻译：组合的风扇压缩机叶轮包括单个轮毂和从轮毂向外延伸的多个间隔开的主叶片，使得在两个主叶片之间限定空气通道。每个主叶片是混流叶片，其从通道的入口端处的风扇部分连续地延伸到通道的出口端处的压缩机部分，而风扇部分和压缩机部分之间没有任何轴向间隙，从而提供空气动力学从风扇部分流过通道的压缩空气与压缩机部分的匹配。

6. 发明公开

EP3094846A4 SYSTEM AND METHOD TO DETECT SHUTOFF VALVE FAILURES 审中-公开
公开(公告)号：EP3094846A4
公开(公告)日：2017-11-01
申请号：EP15735155
申请日：2015-01-09
申请人： UNITED TECHNOLOGIES CORP
发明人： RIPLEY DAVID LLOYD , MEHRER MICHAEL E
IPC分类号： F02C9/00 , B64D27/10 , B64D37/32 , B64D41/00 , F01D21/00 , F02C7/232 , F02C9/26 , F02C9/28 , F02D41/22
CPC分类号： B64D37/32 , B64D27/10 , B64D41/00 , F01D21/003 , F02C7/232 , F02C9/28 , F02D41/221 , F02D2200/0602 , F02D2200/101 , F05D2220/50 , F05D2260/80 , F05D2260/83 , F05D2270/021 , F05D2270/3013 , Y02T10/40
摘要： The present disclosure relates generally to system and method for detecting fuel shutoff valve failures in a system including multiple fuel shutoff valves connected in series. By commanding different fuel shutoff valves to close and detecting changes in the system operating conditions, the system and method may determine if any of the fuel shutoff valves are not working properly.

7. 发明公开

EP3205839A1 METHOD AND SYSTEM FOR APU OIL LEVEL INDICATION 无效
标题翻译： APU油位指示的方法和系统
公开(公告)号：EP3205839A1
公开(公告)日：2017-08-16
申请号：EP17152075.2
申请日：2017-01-18
申请人： Honeywell International Inc.
发明人： MALLETTE, Robert , RILEY, Harold
IPC分类号： F01D21/00 , F01D25/18 , F02C7/06 , F01M11/12 , G05D9/12 , F01D25/20 , F01M11/06
CPC分类号： F16N29/02 , B64D41/00 , F01D25/20 , F02C7/06 , F05D2220/50 , F05D2260/80 , F05D2260/98 , F16N7/38 , F16N7/40 , F16N2210/04 , F16N2250/18
摘要： An auxiliary power unit (APU) oil quantity indication system and method provides a stable and accurate oil quantity indication during startup, mission duration and shutdown. The system determines a gulp value at various stages of operation, which is combined with a raw oil quantity indication to provide an indicated oil quantity.
摘要翻译：辅助动力单元（APU）油量指示系统和方法在启动，任务持续时间和停机期间提供稳定和准确的油量指示。该系统在各个操作阶段确定一个吞噬值，将其与原油量指示相结合以提供指示的油量。

8. 发明公开

EP3181866A1 GAS TURBINE ENGINE FOR AN AIRCRAFT 有权
标题翻译： GASTURBINENMOTORFÜREIN FLUGZEUG
公开(公告)号：EP3181866A1
公开(公告)日：2017-06-21
申请号：EP15382630
申请日：2015-12-16
申请人： AIRBUS OPERATIONS SL
发明人： GARDE LA CASA ALEXANDRE
IPC分类号： F02C7/10 , F01D1/12 , F02C3/14
CPC分类号： F02C7/08 , B64D27/10 , B64D41/00 , B64D2041/002 , F01D1/12 , F01D5/02 , F01D9/041 , F01D15/10 , F01D15/12 , F01D17/105 , F02C3/04 , F02C3/145 , F02C7/10 , F02C9/18 , F05D2220/323 , F05D2220/50 , F05D2240/35 , F05D2240/60 , Y02T50/671
摘要： A gas turbine engine (1) for an aircraft comprising a compressor (3), a combustion chamber (7), and a turbine (5) having at least one stator (8, 10), and at least one rotor (9, 11). Each stator and rotor formed by a plurality of blades, a fluid channel formed between two consecutive blades, and each blade having two opposing surfaces. The compressor (3) is in fluid communication with a first group of stator channels (28), and the combustion chamber (7) is in fluid communication with a second group of stator channels (29), such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls (2, 4) defining a duct for the passage of the heated fluid through the rotor blades, and the outer wall (4) being also arranged for directing the compressed air towards the combustion chamber (7).
摘要翻译： 1。一种用于飞机的燃气涡轮发动机（1），包括具有至少一个定子（8,10）的压缩机（3），燃烧室（7）和涡轮机（5），以及至少一个转子）。每个定子和转子由多个叶片形成，流体通道形成在两个连续的叶片之间，并且每个叶片具有两个相对的表面。压缩机（3）与第一组定子通道（28）流体连通，并且燃烧室（7）与第二组定子通道（29）流体连通，使得热交换可以通过至少一个定子叶片的两个相对表面。外壁和内壁（2,4）限定了用于使加热流体通过转子叶片的通道，并且外壁（4）也布置成用于将压缩空气引向燃烧室（7）。

9. 发明公开

EP3017165A4 ENHANCED APU OPERABILITY 有权转让
标题翻译： VERBESSERTE APU-FUNKTIONSFÄHIGKEIT
公开(公告)号：EP3017165A4
公开(公告)日：2017-06-21
申请号：EP14851306
申请日：2014-06-24
申请人： UNITED TECHNOLOGIES CORP
发明人： RIBAROV LUBOMIR A , LISCINSKY DAVID S , COLKET MEREDITH B III
IPC分类号： F02C7/224 , B64D37/34 , B64D41/00 , F02C3/22 , F02C7/26 , F02C9/40
CPC分类号： F02C7/224 , B64D37/34 , B64D41/00 , F02C3/22 , F02C7/26 , F02C9/40 , F05D2220/50
摘要： A fuel system for a gas turbine engine comprises an injector disposed to inject fuel and air into a combustor of the gas turbine engine. In a first embodiment, the fuel system further comprises an air separation module configured to supply oxygen-enriched air into the combustor via the injector for combustion. In a second embodiment, the fuel system further comprises a barbotage system and a heating element. The barbotage system is configured to feed hydrogen to the injector, and the heating element is configured to pre-heat the fuel.
摘要翻译：用于燃气涡轮发动机的燃料系统包括设置成将燃料和空气喷射到燃气涡轮发动机的燃烧器中的喷射器。在第一实施例中，燃料系统还包括空气分离模块，该空气分离模块构造成经由喷射器将富氧空气供应到燃烧器中用于燃烧。在第二实施例中，燃料系统进一步包括阻塞系统和加热元件。所述阻塞系统构造成将氢气供给到所述喷射器，并且所述加热元件构造成预热所述燃料。

10. 发明公开

EP3179077A1 FUEL CONTROL SYSTEM FOR A GAS TURBINE ENGINE OF AN AIRCRAFT 审中-公开
标题翻译：飞机燃气轮机发动机燃料控制系统
公开(公告)号：EP3179077A1
公开(公告)日：2017-06-14
申请号：EP15382618.5
申请日：2015-12-11
申请人： Airbus Operations, S.L.
发明人： DEMELAS, Salvatore
IPC分类号： F02C7/22 , F02C7/232 , F02C9/28 , F02C9/30
CPC分类号： F02C9/28 , F02C7/22 , F02C7/232 , F02C7/36 , F02C9/30 , F05D2220/323 , F05D2220/50 , F05D2260/40311 , F05D2270/301 , F05D2270/3013 , F05D2270/303 , F05D2270/306 , Y02T50/671
摘要： A fuel control system (1) for a gas turbine engine of an aircraft comprising an engine gearbox (2), a fuel tank (3), and an engine combustion chamber (6), wherein the system (1) further comprises a high pressure fuel pump (9), at least one electrically controlled fuel injector (7), a fuel pressure (11) and temperature sensors (12), and a fuel controller (5) coupled with said sensors (11, 12) to calculate the fuel density, said controller (5) being also coupled with the fuel injector (7) to determine the fuel flow injection rate, said controller (5) being further coupled with the fuel pump (9) to establish a pump output pressure value, according to the fuel density and the flow injection rate of the pumped fuel, such that a constant fuel pressure value is supplied to the fuel injector (7), to finally inject a constant high fuel injection pressure in the combustion chamber (6).
摘要翻译： 1。一种用于飞机的燃气涡轮发动机的燃料控制系统（1），其包括发动机变速箱（2），燃料箱（3）和发动机燃烧室（6），其中系统（1）还包括高压燃料泵（9），至少一个电控燃料喷射器（7），燃料压力（11）和温度传感器（12）以及与所述传感器（11,12）耦合的燃料控制器（5）所述控制器（5）还与所述燃料喷射器（7）耦合以确定燃料流动喷射速率，所述控制器（5）进一步与所述燃料泵（9）耦合以建立泵输出压力值，根据燃料密度和泵送燃料的流动喷射速率，从而向燃料喷射器（7）供应恒定的燃料压力值，以最终在燃烧室（6）中喷射恒定的高燃料喷射压力。

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