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1. 发明公开

EP4403471A1 FLOW CONTROL DUCTED FANS 审中-公开
公开(公告)号：EP4403471A1
公开(公告)日：2024-07-24
申请号：EP23210796.1
申请日：2023-11-20
申请人： The Boeing Company
发明人： NADEL, Adam , BALTADJIEV, Nikola , PRETE, Anthony , WHIPPLE, Brian
IPC分类号： B64D33/02 , B64C29/00 , B64C21/06 , F02C7/042 , B64C11/00 , B64C21/08
CPC分类号： B64D2033/022620130101 , B64D33/02 , B64C11/001 , B64C21/06 , B64C21/08 , B64C29/0033 , F02K3/00 , F02K3/04
摘要： Flow control ducted fans are disclosed. A disclosed example flow control apparatus for use with an aircraft includes a duct defining an inner cavity (208) with a primary flow path, a fan (110, Figure 1) disposed in the inner cavity (208), an aperture (210) on an exterior surface of the duct and upstream from the fan, the aperture fluidly coupled to the inner cavity to define a secondary flow path, and a door (310) to control a degree to which the aperture is opened.

2. 发明公开

EP3333401A1 HYBRID PROPULSION SYSTEM AND CONTROL METHOD THEREOF 有权
公开(公告)号：EP3333401A1
公开(公告)日：2018-06-13
申请号：EP17205746.5
申请日：2017-12-06
申请人： Rolls-Royce North American Technologies, Inc.
发明人： ARMSTRONG, Michael James
IPC分类号： F02K3/00 , F02K5/00 , F02C9/58
CPC分类号： B64D27/24 , B64D27/10 , B64D2027/026 , F02C9/58 , F02K3/00 , F02K5/00 , F04D29/362 , F05D2220/7642 , F05D2270/061 , H02K7/1823
摘要： A system is described that includes a turbine engine including an engine fan including one or more variable-pitch blades driven by a shaft, which rotates at a rotational speed which depends on a pitch of the one or more variable-pitch blades of the engine fan. The system further includes a generator configured to produce alternating-current (AC) electricity at a particular frequency relative to the rotational speed of the shaft. The system also includes a propulsor, which includes a propulsor motor and a propulsor fan. The propulsor motor is configured to drive, based on the AC electricity produced by the generator, the propulsor fan. The system includes a controller configured to control the particular frequency of the AC electricity by at least controlling the pitch of the one or more variable-pitch blades of the engine fan and thereby the rotational speed of the generator.

4. 发明公开

EP3108110A1 GAS TURBINE ENGINE AIRFOIL 有权转让
标题翻译：燃气涡轮发动机WING
公开(公告)号：EP3108110A1
公开(公告)日：2016-12-28
申请号：EP15752013.1
申请日：2015-02-19
申请人： United Technologies Corporation
发明人： GALLAGHER, Edward, J. , MONZON, Byron, R. , LIU, Ling , LI, Linda, S. , WHITLOW, Darryl , FORD, Barry, M.
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/02 , F02C3/107 , F02K3/00 , F05D2200/222 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/30 , F05D2240/301 , F05D2250/713 , F05D2260/40311 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starting at the 0% span position is either zero or positive. The first critical point is in the range of 5-15% span.

5. 发明授权

EP2871130B1 Autonomous propulsion apparatus and method 有权
标题翻译：自主行走装置和方法
公开(公告)号：EP2871130B1
公开(公告)日：2016-07-20
申请号：EP14192537.0
申请日：2014-11-10
申请人： The Boeing Company
发明人： Newman, Daniel
IPC分类号： B64D31/00 , F02C9/00
CPC分类号： B64D31/06 , B64C11/001 , B64D31/00 , F02K3/00

6. 发明公开

EP3014089A2 OVER SPEED MONITORING USING A FAN DRIVE GEAR SYSTEM 有权转让
标题翻译：超速监测风扇驱动系统来
公开(公告)号：EP3014089A2
公开(公告)日：2016-05-04
申请号：EP14847847.2
申请日：2014-06-12
申请人： United Technologies Corporation
发明人： OTTO, John R.
IPC分类号： F02C9/00 , F02C9/16 , F02C7/32 , G01P3/00
CPC分类号： F01D21/003 , F01D17/06 , F01D21/06 , F02K3/00 , F02K3/06 , F05D2240/60 , F05D2260/40311 , F05D2260/80 , F05D2270/021 , F05D2270/304
摘要： A control system for turbofan engine includes a first sensor measuring rotation of a first shaft at a first location and a fan shaft sensor measuring a speed of a fan shaft. A controller utilizes measurements of a first speed of the first shaft from the first sensor and a second speed of the fan shaft driven by a geared architecture and rotating at a speed different than the first shaft. The controller determines that one of the first shaft and the fan shaft are outside predetermined deformation limits responsive to a difference between an actual difference between the first and second speeds and a calculated expected difference between speeds of the first shaft and the fan shaft.

7. 发明公开

EP2738355A1 A gas turbine engine system and an associated method thereof 有权转让
标题翻译： Gasturbinentriebwerk undzugehörigesVerfahren
公开(公告)号：EP2738355A1
公开(公告)日：2014-06-04
申请号：EP13194988.5
申请日：2013-11-29
申请人： General Electric Company
发明人： Haynes, Joel Meier , Joshi, Narendra Digamber , Chen, Huijuan
IPC分类号： F01D9/02 , F23R3/34
CPC分类号： F23R3/346 , F01D9/023 , F02K3/00 , F23R3/286 , F23R3/34 , F23R3/46
摘要： A gas turbine engine system (10) includes a compressor (14), a combustor (16), and a turbine (22). The combustor is coupled to the compressor and disposed downstream of the compressor. The combustor includes a secondary combustor section (20) coupled to a primary combustor section (18) and disposed downstream of the primary combustor section (18). The combustor also includes a transition nozzle (28) coupled to the secondary combustor section and disposed downstream of the secondary combustor section. The combustor further includes an injector (58) coupled to the secondary combustor section, for injecting an air-fuel mixture to the secondary combustor section. The turbine (22) is coupled to the combustor (16) and disposed downstream of the transition nozzle (28); wherein the transition nozzle is oriented substantially tangential to the turbine (22).
摘要翻译：燃气涡轮发动机系统（10）包括压缩机（14），燃烧器（16）和涡轮机（22）。燃烧器联接到压缩机并设置在压缩机的下游。燃烧器包括联接到主燃烧器部分（18）并且设置在主燃烧器部分（18）的下游的二级燃烧器部分（20）。燃烧器还包括连接到次级燃烧器部分并设置在次级燃烧器部分下游的过渡喷嘴（28）。燃烧器还包括联接到次级燃烧器部分的喷射器（58），用于将空气 - 燃料混合物喷射到次级燃烧器部分。涡轮（22）联接到燃烧器（16）并且设置在过渡喷嘴（28）的下游; 其中所述过渡喷嘴基本上与所述涡轮机（22）相切地定向。

8. 发明公开

EP2643579A1 PROPULSEUR COMBINE TURBOREACTEUR ET STATOREACTEUR 有权转让
标题翻译：组合TURBO空气喷气发动机和冲压发动机
公开(公告)号：EP2643579A1
公开(公告)日：2013-10-02
申请号：EP11794549.3
申请日：2011-11-14
申请人： Snecma
发明人： CONRARDY, Jean-Marie , SOULIER, Nicolas
IPC分类号： F02K7/16
CPC分类号： F02K7/16 , F02C7/224 , F02K3/00 , F02K3/072 , Y02T50/672
摘要： The combined engine comprises a turbopump (129) comprising a pump (129A) for injecting hydrogen into a reheater (150) placed in an external casing (104) downstream of a central spool (105) and a subsonic turbine (129B) for driving the pump (129A), which receives the hydrogen collected at the outlet of the reheater (150), which is partially expanded, in order to apply the hydrogen to a supersonic turbine (122), for operating the engine as a turbojet engine, the hydrogen emanating from the supersonic turbine (122) then being collected in piping (124, 125) inside the central spool (105) to be sent to a combustion chamber (110) defined downstream of the central spool (105), whereas the hydrogen that has been partially expanded in a subsonic turbine (129B) is passed on directly to the combustion chamber (110) by injectors (111) for operating the engine as a ramjet.

9. 发明授权

EP2075420B1 Method of preparing an engine for transportation 有权
标题翻译： Verfahren zur Herstellung eines Strahltriebwerks zum Transport
公开(公告)号：EP2075420B1
公开(公告)日：2012-08-15
申请号：EP08172258.9
申请日：2008-12-19
申请人： General Electric Company
发明人： Daniels, James Lloyd
IPC分类号： F02C7/20 , F01D25/28 , B64F1/00 , B64F5/00 , F02C7/00 , F02K3/00
CPC分类号： F01D25/285 , B64F1/005 , B64F5/50 , F02C7/00 , F02C7/20 , F02K3/00 , F05D2240/55 , Y02T50/672 , Y10T29/49318

10. 发明公开

EP2344739A1 HYBRID PROPULSIVE ENGINE INCLUDING AT LEAST ONE INDEPENDENTLY ROTATABLE COMPRESSOR ROTOR 失效转让
标题翻译：与至少一个可独立旋转的压气机转子混合动力驱动电机
公开(公告)号：EP2344739A1
公开(公告)日：2011-07-20
申请号：EP09819581.1
申请日：2009-10-08
申请人： Searete LLC
发明人： FOSTER, Glenn, B. , HYDE, Roderick, A. , ISHIKAWA, Muriel, Y. , JUNG, Edward, K.Y. , KARE, Jordin, T. , MYHRVOLD, Nathan, P. , TEGREENE, Clarence, T. , WEAVER, Thomas, Allan , WOOD, Lowell, L., Jr. , WOOD, Victoria, Y.H.
IPC分类号： F02D29/06
CPC分类号： F02C6/206 , B64D27/16 , B64D27/24 , B64D31/04 , B64D31/06 , B64D33/00 , B64D2027/026 , F01D5/03 , F01D15/10 , F01K23/10 , F02C6/00 , F02C6/08 , F02C6/14 , F02C6/18 , F02C7/36 , F02K3/00 , F02K3/025 , F02K3/077 , F05D2220/324 , F05D2220/325 , F05D2220/326 , F05D2220/327 , F05D2220/76 , F05D2260/408 , F05D2260/85 , Y02T50/44 , Y02T50/64 , Y02T50/672 , Y02T50/673
摘要： A hybrid propulsive technique includes providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further comprises rotating an at least one independently rotatable propeller/fan of at least one rotatable propeller/fan assembly at least partially responsive to the converting the at least a portion of the electrical power to torque, wherein the rotating of the at least one independently rotatable propeller/fan of the at least one rotatable propeller/fan assembly is arranged to produce at least some second thrust.

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