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1. 发明公开

EP3406526A2 PROPULSION SYSTEM FOR AN AIRCRAFT 有权
公开(公告)号：EP3406526A2
公开(公告)日：2018-11-28
申请号：EP18173393.2
申请日：2018-05-21
申请人： General Electric Company
发明人： BARONE, Dominic , GEMIN, Paul Robert
IPC分类号： B64D27/24 , B64D35/02 , B64D27/02
CPC分类号： B64D27/24 , B64D27/10 , B64D27/16 , B64D35/02 , B64D2027/026 , B64D2221/00 , F01D15/10 , F02C3/04 , F05D2220/323 , Y02T50/64
摘要： A propulsion system 50, 350 for an aircraft 10 includes an electric generator 56, 356 mechanically driven by a combustion engine, with the electric generator 56, 356 configured to generate alternating current electrical power. The propulsion system 50, 350 additionally includes a power bus 58, 356 electrically connected to the electric generator 56, 356 and configured to receive and transmit the alternating current electrical power generated by the electric generator 56, 356. Additionally, the propulsion system 50, 350 includes, an electric propulsor assembly comprising an electric motor 360 and a propulsor drivingly connected to the electric motor 360, the electric motor 360 electrically coupled to the power bus 58, 356 for the receiving alternating current electrical power from the power bus 58, 356.

2. 发明公开

EP3406438A1 COMPOSITE CORE, COMPOSITE STRUCTURE ASSEMBLY, AND METHOD FOR FORMING THE SAME 有权转让
公开(公告)号：EP3406438A1
公开(公告)日：2018-11-28
申请号：EP18167287.4
申请日：2018-04-13
申请人： The Boeing Company
发明人： WALDROP, John C., III , RENWICK, Zachary Benjamin , THOMPSON, Matthew Scott , HAYES, Michael William
IPC分类号： B32B7/08 , B32B7/12 , B32B27/08 , B32B27/12 , B32B27/28 , B32B27/34 , B32B3/12
CPC分类号： B64D33/02 , B32B3/12 , B32B7/08 , B32B7/12 , B32B27/08 , B32B27/12 , B32B27/285 , B32B27/286 , B32B27/288 , B32B27/34 , B32B37/0076 , B32B2260/021 , B32B2260/046 , B32B2262/0269 , B32B2262/101 , B32B2262/106 , B32B2305/024 , B32B2307/102 , B32B2307/724 , B32B2307/726 , B32B2605/18 , B64D27/16 , B64D2033/0206
摘要： A composite core (102), composite structure assembly (100), and method (200) of forming the composite structure assembly are provided. The composite core includes a first cell layer (110) having a plurality of first cells (108) and a second cell layer (111) having a plurality of second cells (108). The first cell layer is adjacent to the second cell layer. The plurality of first cells are fluidly interconnected with the plurality of second cells.

3. 发明公开

EP3404217A1 METHOD OF REMOVING A FIBER-REINFORCED WRAP FROM A FAN CASING AND CORRESPONDING SYSTEM FOR REMOVING A FIBER-REINFORCED WRAP FROM A FAN CASING 有权
公开(公告)号：EP3404217A1
公开(公告)日：2018-11-21
申请号：EP18171907.1
申请日：2018-05-11
申请人： General Electric Company
发明人： CYREK, Michal Jerzy , STASZAK, Mariusz Pawel , MOCZULSKI, Leszek Jozef
IPC分类号： F01D21/04 , B29C70/22 , B32B43/00 , F01D25/00 , F01D25/24 , F01D25/28 , B32B38/00 , B32B38/10 , F02C7/04
CPC分类号： B32B43/006 , B29C63/0013 , B29L2031/7504 , B32B38/0036 , B32B38/10 , B32B2305/08 , B32B2305/188 , B32B2311/24 , B32B2311/30 , B32B2377/00 , B32B2605/18 , B64D27/16 , B64D29/00 , F01D21/045 , F01D25/005 , F01D25/24 , F01D25/285 , F02C7/04 , F05D2230/80 , F05D2300/603 , F05D2300/701
摘要： a method of removing a fiber-reinforced wrap (102) from a fan casing (18) compries heating the fiber-reinforced wrap (102) while on a metal support (104) of the fan casing (18), unwinding a layer (101) of the fiber-reinforced wrap (102) from the fan casing (18), and winding the layer (101) of the fiber-reinforced wrap (102) onto a collection drum (114). A system for removing a fiber-reinforced wrap (102) from a fan casing (18) comprises a mounting roll for a metal support (104) of the fan casing (18), a heat source (106) directed at the mount and configured to heat a surface of the fan casing (18) when loaded onto the mounting roll, and a collection drum (114).

4. 发明公开

EP3387244A1 FLUGGASTURBINE MIT VARIABLER AUSTRITTSDÜSE EINES NEBENSTROMKANALS 审中-公开
公开(公告)号：EP3387244A1
公开(公告)日：2018-10-17
申请号：EP16805124.1
申请日：2016-12-01
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： KÖPF, Frank Uwe
IPC分类号： F02K1/08
CPC分类号： F02K1/08 , B64D27/16 , B64D31/06 , F05D2220/323
摘要： The invention relates to an aircraft gas turbine, comprising a core engine (10) and a bypass flow channel (25), which bypasses the core engine and which forms an outlet nozzle (31) together with a casing (29) of the core engine (10) and together with a radially outer housing wall (30), characterized in that a ring element (32), which can be displaced in the axial direction, is arranged in the region of the outlet nozzle (31), wherein a ring channel (33) that can be varied by the displacement of the ring element (32) is formed between the casing (29) of the core engine (10) and the ring element (32).

5. 发明授权

EP3263454B1 VTOL AIRCRAFT WITH A THRUST-TO-WEIGHT RATIO SMALLER THAN 0.1 有权
公开(公告)号：EP3263454B1
公开(公告)日：2018-09-26
申请号：EP17020335.0
申请日：2014-04-17
申请人： Chen, Li Jing
发明人： Chen, Li Jing
IPC分类号： B64C29/00 , B64C21/04
CPC分类号： B64C29/00 , B64C9/00 , B64C15/02 , B64C21/04 , B64C23/005 , B64C29/005 , B64C29/0066 , B64C2009/005 , B64D27/16 , Y02T50/166
摘要： An aircraft includes: ailerons (1,2); a turbofan engine (3) comprising a high-temp duct (4) with an openable/ closable propelling nozzle (5), and a low-temp duct (6) with an openable/closable propelling nozzle (7); a high-temp bypass duct (9) comprising an openable/closable inlet (8) connected to the high-temp duct(4), an outer wall(10) and a rectangle outlet(12) with a height-to-width ratio smaller than 0.1; a low-temp bypass duct (15) comprising an openable/closable inlet (14) connected to the low-temp duct (7), an outer wall (16), an inner wall (17) and a rectangle outlet (19) with a height-to-width ratio smaller than 0.1. During vertical take-off/lading, closing the propelling nozzles (5, 7) of turbofan engine (3), and opening the inlets (8,14) of high-temp and low-temp bypass ducts(9,15), low-temp planar air jet (20) is cause to flow over upper surface of the aircraft, thereby generating lift and no air flow over lower one.

6. 发明公开

EP3293387A1 HIDDEN THRUST REVERSER BLOCKER DOOR LINK ARM FITTING 有权转让
标题翻译：隐藏推倒换挡器门链接臂配件
公开(公告)号：EP3293387A1
公开(公告)日：2018-03-14
申请号：EP17188437.2
申请日：2017-08-29
申请人： United Technologies Corporation
发明人： SAWYERS-ABBOTT, Nigel David , EXNER, Matthew
IPC分类号： F02K1/72 , F16C11/04
CPC分类号： B64D29/06 , B64D27/16 , F01D25/24 , F02K1/56 , F02K1/72 , F02K1/763 , F05D2220/323 , F05D2230/60 , F05D2260/50 , F16C11/045 , F16C2360/23 , Y02T50/672
摘要： A linkage system (232; 432; 532; 632) for a nacelle (112) may comprise a pivot (330; 430; 530) configured to extend through a second aperture disposed in a link arm (256), a base member (310; 410; 510; 610), and a retaining member (320; 420; 520; 620) at least partially defining a first aperture and a cavity (342; 442; 542). The pivot (330; 430; 530) is configured to extend at least partially into the first aperture. The cavity (342; 442; 542) is configured to accommodate a portion of the link arm (256).
摘要翻译：用于机舱（112）的连杆系统（232; 432; 532; 632）可以包括被配置为延伸穿过设置在连杆臂（256）中的第二孔的枢轴（330; 430; 530），基座构件 ; 410; 510; 610）以及至少部分地限定第一孔和空腔（342; 442; 542）的保持构件（320; 420; 520; 620）。枢轴（330; 430; 530）构造成至少部分地延伸到第一孔中。空腔（342; 442; 542）构造成容纳连杆臂（256）的一部分。

9. 发明公开

EP3106649A1 AIRCRAFT GAS TURBINE PROPULSION ENGINE CONTROL WITHOUT AIRCRAFT TOTAL AIR TEMPERATURE SENSORS 有权
标题翻译： FLUGZEUGGASTURBINENANTRIEBSTRIEBWERKSTEUERUNG OHNE FLUGZEUGGESAMTLUFTTEMPERATURSENSOREN
公开(公告)号：EP3106649A1
公开(公告)日：2016-12-21
申请号：EP16173128.6
申请日：2016-06-06
申请人： Honeywell International Inc.
发明人： XIONG, Yufei , FAYMON, Dave , COFFEY, Scot
IPC分类号： F02C9/28 , F01D17/08 , F01D21/00
CPC分类号： B64D31/06 , B64D27/16 , F02C9/28 , F05D2270/313 , G07C5/0816
摘要： A control system for an aircraft gas turbine propulsion engine includes an engine control that is adapted to receive at least engine inlet temperature data and aircraft altitude data. The engine control is configured to determine the availability of the engine inlet temperature data and implements a measured temperature engine thrust setting schedule when the engine inlet temperature data is available, and a default temperature engine thrust setting schedule when the engine inlet temperature data is unavailable. The default temperature engine thrust setting schedule ensures that the gas turbine propulsion engine will generate at least 90% of rated engine thrust at all actual engine inlet temperatures at the sensed aircraft altitude.
摘要翻译：用于飞机燃气轮机推进发动机的控制系统包括适于接收至少发动机入口温度数据和飞行器高度数据的发动机控制。发动机控制被配置为确定发动机入口温度数据的可用性，并且当发动机入口温度数据可用时实施测量的温度发动机推力设定时间表，以及当发动机入口温度数据不可用时的默认温度发动机推力设定调度。默认的温度发动机推力设定计划确保燃气轮机推进发动机将在感测到的飞机高度处的所有实际发动机入口温度下产生至少90％的额定发动机推力。

10. 发明公开

EP3085419A1 BANC D'ESSAIS DE TURBOREACTEUR D'AERONEF AVEC OBTURATEURS 有权转让
标题翻译： PRÜFBANKFÜRTURBOREAKTOR EINES LUFTFAHRZEUGS MIT ABSPERRVENTILEN
公开(公告)号：EP3085419A1
公开(公告)日：2016-10-26
申请号：EP16158934.6
申请日：2016-03-07
申请人： Techspace Aero S.A.
发明人： TACCOGNA, Gaetano
IPC分类号： A62C2/10 , A62C2/14 , F01D21/00 , G01M15/14 , A62C3/00
CPC分类号： F01D21/003 , A62C2/10 , A62C2/14 , A62C3/08 , B64D27/16 , B64F5/60 , F01D25/285 , F05D2260/83 , G01M15/14
摘要： L'invention a trait à un banc d'essais (2) pour turboréacteur (4) d'avion. Le banc d'essais (2) comprend une configuration en « U », avec un passage (6) en forme de couloir (12) allongé, une cheminée d'entrée (20), une cheminée sortie (22). Le couloir (12) comporte une zone de fixation (16) avec un bras de fixation (18) pour maintenir le turboréacteur (4) pendant son essai. Le passage (6) montre en outre un obturateur amont (38) avec des guides d'air verticaux pivotants, et un obturateur aval (40) avec un ballon gonflable dans le tube collecteur. En cas d'incendie (42), les obturateurs (38 ; 40) se ferment et confinent le turboréacteur (4) pour étouffer rapidement le feu. L'invention propose également un procédé de gestion d'incendie (42) dans un banc d'essais (2) avec un passage (6). Des obturateurs (38 ; 40) sont placés dans le passage, ils s'y déploient instantanément en cas d'incendie (42).
摘要翻译：提供飞机涡轮喷气发动机的试验台。测试台包括具有细长走廊形式的通道的U形构造，入口管道和出口管道。该走廊包括固定区，其具有用于在测试期间保持涡轮喷气发动机的固定臂。该通道还具有具有垂直枢转空气引导件的上游闸门和在收集管中具有可膨胀气囊的下游挡板。在发生火灾的情况下，百叶窗接近限制涡轮喷气发动机，以迅速窒息火灾。还提供了一种用于在具有通道的测试台中管理火的方法。百叶窗放在通道中，在那里部署。

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