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31. 发明申请

WO2016003517A3 VARIABLE PROFILE CASCADE 审中-公开
公开(公告)号：WO2016003517A3
公开(公告)日：2016-01-07
申请号：PCT/US2015/025418
申请日：2015-04-10
申请人： CRAWFORD, Sara C.
发明人： CRAWFORD, Sara C.
IPC分类号： F02K1/56
摘要： A thrust reverser system may comprise a cascade radially positioned about a centerline of an engine or a nacelle centerline. Various cascade features may be positioned at a constant radius from the centerline while other features vary according to station and/or circumferential position.

32. 发明专利

JP6596593B2 逆推力装置の作動有权
公开(公告)号：JP6596593B2
公开(公告)日：2019-10-23
申请号：JP2018541632
申请日：2017-02-08
申请人：ウッドワード,インコーポレーテッド , Woodward,Inc.
发明人：コペチェク,ジョセフトーマス , スウィート,ジュリアン
IPC分类号： F02K1/15 , F02K1/56 , F02K1/64 , F02K1/76

33. 发明专利

JP2019508621A 逆推力装置の作動审中-公开
公开(公告)号：JP2019508621A
公开(公告)日：2019-03-28
申请号：JP2018541632
申请日：2017-02-08
申请人：ウッドワード,インコーポレーテッド , Woodward,Inc.
发明人：コペチェク,ジョセフトーマス , スウィート,ジュリアン
IPC分类号： F02K1/15 , F02K1/56 , F02K1/64 , F02K1/76
摘要：逆推力装置は、格納位置と展開位置との間で移動可能な逆推力要素と、この逆推力要素を格納位置と展開位置との間で動かせるように、作動可能に結合された少なくとも1つの油圧アクチュエータと、第1の作動圧力に応じて、逆推力要素の移動が防止される係合状態と、逆推力要素の移動が防止されない解放状態との間を移行するように構成された少なくとも1つの油圧プライマリロックと、油圧アクチュエータ及び油圧プライマリロックに流体結合された方向制御ユニットであって、第1の作動圧力よりも大きい第2の作動圧力に応じて第1の段階から第2の段階へ移行するように構成され、第1の段階から第2の段階への移行によって、油圧アクチュエータに、逆推力要素を展開位置へ移動させる方向制御ユニットとを含む。

35. 发明专利

JP4870750B2 Flight-body air compression type engine 有权
公开(公告)号：JP4870750B2
公开(公告)日：2012-02-08
申请号：JP2008508053
申请日：2006-04-19
申请人： ▲鴻▼元 ▲張▼
发明人： ▲鴻▼元 ▲張▼ , 明▲シェン▼ ▲張▼
IPC分类号： F42B10/66 , F02C6/00 , F02C7/00 , F02C7/32 , F02C7/36 , F02K1/54 , F02K1/56 , F02K3/04 , F02K9/80
CPC分类号： F02K1/002 , F02C3/04 , F02C3/107 , F05D2220/90 , Y02T50/671
摘要： The present invention relates to an air compression type engine for aviation. The conventional aircraft engine is complicated in structure, consumes expensive aero fuel, and produces extremely loud noise during operation. Therefore, the present invention employs a turbo-charged air compressor to generate high temperature and high pressure gas in the pressure chamber, and uses the reaction thrust force generated by ejecting the compressed air through the nozzle to make the aircraft vertically take off/land, suspend in the air and fly forwardly. Benefited from the simple structure, the manufacture cost of the aircraft engine can be dramatically decreased. Vertically raising and landing the aircraft can be achieved by changing the ejection directed of the compressed air in the pressure chamber. The commonly used gasoline or diesel, which is cost saving and capable of combusting with a high combustion value, can be used instead of the expensive aviation kerosene. Further, the generated noise is quite small. By means of above arrangement, it is possible to manufacture a jet type manned craft like a car, which can be operated by common people to vertically take off/land and shuttle conveniently in the downtown area through simple operation procedure.

36. 发明专利

JPH1122552A TURBOFAN ENGINE WITH COWLING CONNECTED TO THRUST REVERSER AND FITTED IN FLOW TUBE 失效
公开(公告)号：JPH1122552A
公开(公告)日：1999-01-26
申请号：JP16564498
申请日：1998-06-12
申请人： HISPANO SUIZA SA
发明人： GONIDEC PATRICK , VAUCHEL GUY BERNARD , ROUYER PASCAL GERARD
IPC分类号： B64D33/00 , F02K1/52 , F02K1/56 , F02K1/70 , F02K3/06
摘要： PROBLEM TO BE SOLVED: To provide a turbofan engine meeting improvement requirement for an aerodynamic flow. SOLUTION: An inner structure 11 forming the primary cowling of a turbojet engine and an outer structure 12 supporting a thrust reverser 10 are connected to the thrust reverser 10 having no connection to the downstream side of the structures 11, 12 and having the circular passage 15 of a flow tube between both structures 11, 12 in this turbofan engine. A cowling 25 is fitted on the downstream side of an arm 3 forming the support structure of the outer wall of the rear pipe of the fan of the turbojet engine in the passage 15.

37. 发明专利

JPH04272459A GAS TURBINE ENGINE WITH THRUST REVERSER CONTROL DEVICE 失效
公开(公告)号：JPH04272459A
公开(公告)日：1992-09-29
申请号：JP16998591
申请日：1991-07-10
申请人： ROLLS ROYCE PLC
发明人： ANDORIYUU JIYOOJI WAADO
IPC分类号： B64C15/02 , B64D33/04 , F02K1/56 , F02K1/64 , F02K1/76
摘要： PURPOSE: To provide a thrust reverser control device to reduce the possibility of inadvertent operation of the device in checking the operation of the device in a maintenance of an aircraft with reference to a trust reverser provided on a gas turbine engine for aircraft. CONSTITUTION: A safety switch 19 is provided on a cowling 13 close to an air intake port 14 of an engine. The safety switch forms a part of a controlled for the operation of a thrust reverser 16, and is of the type capable of operating only during the manual operation. If the operation of the thrust reverser is tested when an engine 10 is not in operation, a main thrust reverser switch in a cockpit to give the first command signal is operated, and then, the safety switch 19 is manually operated. The thrust reverser is operated thereby.

38. 发明专利

JPS572449A GAS TURBINE ENGINE 失效
公开(公告)号：JPS572449A
公开(公告)日：1982-01-07
申请号：JP6609681
申请日：1981-04-30
申请人： ROLLS ROYCE
发明人： MARUKOMU CHIYAARUZU HITSUCHIKO
IPC分类号： F02K1/56 , F02K1/60

39. 发明专利

JPS5484117A REVERSING APPARATUS 失效
公开(公告)号：JPS5484117A
公开(公告)日：1979-07-04
申请号：JP10983378
申请日：1978-09-08
申请人： GEN ELECTRIC
发明人： DATSUDORII OOEN NASHIYU
IPC分类号： F02K1/62 , B64D33/00 , F02K1/00 , F02K1/56
摘要： A thrust reverser is provided for use with an asymmetric aircraft gas turbine engine exhaust nozzle. The thrust reverser includes a movable aerodynamic flap downstream of the asymmetric nozzle casing which is rotatable about one pivot in order to effect in-flight thrust vectoring through deflection of the exhaust stream, and which is also independently rotatable about another pivot to effect thrust reversing. In the reverse thrust mode, the leading edge of the flap is immersed into the exhaust stream, thereby splitting the stream into two portions, one of which is deflected upward and forward by a turning vane incorporated into the leading edge of the flap, and the other portion of which is deflected downward and forward by a hinged lip connected to the flap trailing edge. The thrust reverser thus permits the exhaust stream to be ejected in the vertical plane to produce reverse thrust without an accompanying pitch moment even though the exhaust nozzle is not symmetrical in the vertical plane.

40. 发明申请

WO2014109785A1 BELOW WING REVERSE CORE GAS TURBINE ENGINE WITH THRUST REVERSER 审中-公开
标题翻译：下面的逆向核心燃气涡轮发动机与扭矩反转器
公开(公告)号：WO2014109785A1
公开(公告)日：2014-07-17
申请号：PCT/US2013/040487
申请日：2013-05-10
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SUCIU, Gabriel L. , CHANDLER, Jesse M.
IPC分类号： F02K1/56 , F02K1/54 , F02K3/02
CPC分类号： F02C3/107 , F02K1/60 , F02K1/70 , F02K3/00
摘要： A core engine includes a compressor section, a combustor and a turbine section, with the turbine section being closest to a fan, the combustor section and then the compressor section being positioned further away from the fan relative to the turbine section. A downstream end of a nozzle has at least one pivoting shell and an actuator pivots the shell between a stowed position and a deployed position. A mount bracket is mounted at one circumferential location of the engine. The shell moves in a direction having at least a component perpendicular to a vertical direction defined perpendicular to a top surface of the mount bracket.
摘要翻译：核心发动机包括压缩机部分，燃烧器和涡轮机部分，其中涡轮部分最靠近风扇，燃烧器部分然后压缩机部分相对于涡轮部分定位成更远离风扇。喷嘴的下游端具有至少一个枢转壳体，并且致动器在收起位置和展开位置之间枢转壳体。安装支架安装在发动机的一个圆周位置。壳体沿着至少垂直于垂直于安装支架的顶表面限定的垂直方向的分量的方向移动。

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