专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

EP3415728B1 GAS TURBINE ENGINE WITH ROTATING REVERSING COMPOUND GEARBOX 有权
公开(公告)号：EP3415728B1
公开(公告)日：2020-10-21
申请号：EP18177012.4
申请日：2018-06-11
申请人： General Electric Company
发明人： STUART, Alan Roy , ZATORSKI, Darek Tomasz
IPC分类号： F01D25/00 , F02C7/36

2. 发明授权

EP3023623B1 Gas turbine engine with thrust reversal and method of assembling the same 有权
公开(公告)号：EP3023623B1
公开(公告)日：2018-10-24
申请号：EP15194920.3
申请日：2015-11-17
申请人： General Electric Company
发明人： ZATORSKI, Darek T. , LONNEMAN, Patrick John , STUART, Alan Roy
IPC分类号： F02K1/12 , F02K1/30 , F02K1/32 , F02K1/66 , F01D25/06 , F02K1/70 , F01D7/00
CPC分类号： F01D7/00 , F01D25/06 , F02K1/12 , F02K1/30 , F02K1/32 , F02K1/66 , F02K1/70 , Y02T50/673
摘要： A gas turbine engine 100 having a forward thrust mode and a reverse thrust mode is provided. The gas turbine engine includes a variable pitch fan 102 configured for generating forward thrust in the forward thrust mode of the engine and reverse thrust in the reverse thrust mode of the engine. The engine also includes a fan cowl 110 surrounding the variable pitch fan, wherein the fan cowl forms a bypass duct 112 for airflow generated by the fan. The fan cowl includes an aft edge 128 that defines a physical flow area of the bypass duct, and a deflection device 114 configured for deflecting airflow near the aft edge, wherein the deflection device is configured for operation in the reverse thrust mode of the engine. The physical flow area of the bypass duct at the aft edge remains the same in the forward thrust mode of the engine and in the reverse thrust mode of the engine.

3. 发明公开

EP3023623A1 GAS TURBINE ENGINE WITH THRUST REVERSAL AND METHOD OF ASSEMBLING THE SAME 审中-公开
标题翻译： GASTURBINENMOTOR MIT SCHUBUMKEHR UND MONTAGEVERFAHRENDAFÜR
公开(公告)号：EP3023623A1
公开(公告)日：2016-05-25
申请号：EP15194920.3
申请日：2015-11-17
申请人： General Electric Company
发明人： ZATORSKI, Darek T. , LONNEMAN, Patrick John , STUART, Alan Roy
IPC分类号： F02K1/12 , F02K1/30 , F02K1/32 , F02K1/66 , F01D25/06 , F02K1/70 , F01D7/00
CPC分类号： F01D7/00 , F01D25/06 , F02K1/12 , F02K1/30 , F02K1/32 , F02K1/66 , F02K1/70 , Y02T50/673
摘要： A gas turbine engine 100 having a forward thrust mode and a reverse thrust mode is provided. The gas turbine engine includes a variable pitch fan 102 configured for generating forward thrust in the forward thrust mode of the engine and reverse thrust in the reverse thrust mode of the engine. The engine also includes a fan cowl 110 surrounding the variable pitch fan, wherein the fan cowl forms a bypass duct 112 for airflow generated by the fan. The fan cowl includes an aft edge 128 that defines a physical flow area of the bypass duct, and a deflection device 114 configured for deflecting airflow near the aft edge, wherein the deflection device is configured for operation in the reverse thrust mode of the engine. The physical flow area of the bypass duct at the aft edge remains the same in the forward thrust mode of the engine and in the reverse thrust mode of the engine.
摘要翻译：提供具有向前推力模式和逆推力模式的燃气涡轮发动机100。燃气涡轮发动机包括可变桨距风扇102，该变桨距风扇102构造成在发动机的向前推力模式中产生正向推力并且以发动机的反推力模式产生反推力。发动机还包括围绕可变桨距风扇的风扇罩110，其中风扇罩形成用于由风扇产生的气流的旁路管道112。风扇罩包括限定旁路管道的物理流动区域的后边缘128和被配置为偏转靠近后边缘的气流的偏转装置114，其中偏转装置构造成在发动机的反向推力模式下操作。在后缘的旁通管道的物理流动面积在发动机的向前推力模式和发动机的反向推力模式下保持相同。

4. 发明公开

EP3216699A1 METHOD AND SYSTEM FOR MOUNTING AN AIRCRAFT ENGINE 审中-公开
标题翻译：用于安装飞机发动机的方法和系统
公开(公告)号：EP3216699A1
公开(公告)日：2017-09-13
申请号：EP17159591.1
申请日：2017-03-07
申请人： General Electric Company
发明人： STUART, Alan Roy
IPC分类号： B64D27/18 , B64D27/26 , F01D25/28 , F02C7/20
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/268 , F02C7/20 , F05D2220/323 , F05D2230/60 , F05D2240/90 , Y02T50/44 , Y02T50/671
摘要： A system 100 for mounting an engine 10 to an aircraft 1 includes a rigid structure 102 coupled to a wing 3 and including a forward mount interface 104 and an aft mount interface 106. The system includes a frame 115 including a first support connection 108 and a second support connection 110 spaced apart from the first support connection. A linkage structure 114 couples the frame to the rigid structure and includes a first linkage pair 116 extending between the forward mount interface and the first support connection at a first angle α with respect to a rotational axis 40, and a second linkage pair 118 extending between the aft mount interface and the second support connection at a second angle β with respect to the rotational axis. A projection of the load vector 120,122 of the first linkage pair and the second linkage pair intersect proximate the rotational axis of the engine between a forward end of a fan assembly 16 and a high pressure compressor 22.
摘要翻译：用于将发动机10安装到飞机1的系统100包括刚性结构102，该刚性结构102联接到机翼3并且包括前部安装接口104和后部安装接口106.该系统包括框架115，框架115包括第一支撑连接件108和第二支撑连接件110与第一支撑连接件间隔开。连杆结构114将框架连接到刚性结构并且包括第一连杆对116和第二连杆对118，第一连杆对116在前部安装接口和第一支撑连接部之间相对于旋转轴线40以第一角度α延伸，后安装界面和第二支撑连接件相对于旋转轴线成第二角度β。第一连杆对和第二连杆对的载荷矢量120,122的投影在风扇组件16的前端和高压压缩机22之间的发动机的旋转轴线附近相交。

5. 发明公开

EP3023624A1 GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME 有权
标题翻译： GASTURBINENMOTOR UNDDIESBEZÜGLICHESMONTAGEVERFAHREN
公开(公告)号：EP3023624A1
公开(公告)日：2016-05-25
申请号：EP15195700.8
申请日：2015-11-20
申请人： General Electric Company
发明人： STUART, Alan Roy , LONNEMAN, Patrick John
IPC分类号： F02K1/66 , F02K1/72 , F02K1/76
CPC分类号： F02K1/72 , F02K1/66 , F02K1/763 , F04D19/002 , F04D27/002 , F05D2250/241 , F05D2250/314 , F05D2250/34 , F05D2250/51
摘要： A gas turbine engine 100 having a centerline axis 106 is provided. The gas turbine engine includes a fan 102 and a fan cowl assembly 110 surrounding the fan to define a bypass duct 116 configured to channel airflow for the fan. The fan cowl assembly includes a stationary cowl 112 and a transcowl 114. The gas turbine engine further includes a plurality of actuators 132 configured for displacing the transcowl relative to the stationary cowl. Each of the actuators is skewed relative to the centerline axis of the engine.
摘要翻译：提供具有中心线轴线106的燃气涡轮发动机100。燃气涡轮发动机包括风扇102和围绕风扇的风扇罩组件110，以限定被配置为引导风扇的气流的旁路管道116。风扇罩组件包括固定罩112和转筒114。燃气涡轮发动机还包括多个致动器132，其构造成用于相对于静止整流罩移动转子。每个致动器相对于发动机的中心线倾斜。

6. 发明公开

EP2925990A1 THRUST REVERSER SYSTEM WITH TRANSLATING ROTATING BLOCKER DOORS AND METHOD OF OPERATION 审中-公开
标题翻译：用于操作ROTATING滑动锁门方法反推系统
公开(公告)号：EP2925990A1
公开(公告)日：2015-10-07
申请号：EP13785779.3
申请日：2013-10-22
申请人： General Electric Company
发明人： STUART, Alan Roy , COSGROVE, James Michael
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , F05D2260/50 , Y02T50/672
摘要： A thrust reverser system and operation suitable for turbofan engines. Blocker doors of the thrust reverser system have stowed positions in which each door is disposed between a fixed structure and a translating cowl of the engine. The translating cowl is translated in an aft direction of the engine to define at least one opening with the fixed structure, after which the translating cowl is further translated aft to deploy linkage mechanisms that are received in slots recessed into the blocker doors and pivotably connect the doors to the fixed structure. Deployment of the linkage mechanisms from the slots causes the blocker doors to rotate to a deployed position in which each door extends across a bypass duct of the engine and diverts bypass air within the duct through the opening.

7. 发明公开

EP3460182A1 COUNTER ROTATING TURBINE WITH REVERSING SPEED REDUCTION ASSEMBLY 审中-公开
公开(公告)号：EP3460182A1
公开(公告)日：2019-03-27
申请号：EP18193679.0
申请日：2018-09-11
申请人： General Electric Company
发明人： CLEMENTS, Jeffrey Donald , ZATORSKI, Darek Tomasz , STUART, Alan Roy
IPC分类号： F01D1/26 , F02K3/068 , F02K3/072 , F02C3/067 , F02C3/107 , F02C7/36
摘要： The present disclosure is directed to a gas turbine engine 10 including a turbine section 90 including a first rotating component 110 interdigitated along a longitudinal direction with a second rotating component 120. The first rotating component 110 and the second rotating component 120 are each coupled to a speed reduction assembly 45 in counter-rotating arrangement. The first rotating component 110 comprising an outer shroud 114 and a plurality of outer shroud airfoils 118 extended inward along a radial direction from the outer shroud (114). A connecting member 116 couples the outer shroud 114 to a radially extended first rotor 113. The second rotating component 120 comprising an inner shroud (112) and a plurality of inner shroud airfoils 119 extended outward along the radial direction from the inner shroud 112, the plurality of inner shroud airfoils 119 in alternating arrangement along the longitudinal direction with the plurality of outer shroud airfoils 118. The gas turbine engine 10 defines a radius per unit thrust defined by a maximum radius (RR) at the turbine section 90 over a maximum thrust output between approximately .0004 to approximately .0010 inches per pound thrust.

8. 发明公开

EP3176415A1 THRUST REVERSER SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机推力换向系统
公开(公告)号：EP3176415A1
公开(公告)日：2017-06-07
申请号：EP16199963.6
申请日：2016-11-22
申请人： General Electric Company
发明人： STUART, Alan Roy
IPC分类号： F02K1/72 , F02K3/06 , F02K1/70
摘要： A thrust reverser system (100) for incorporation into a nacelle assembly (50) of a gas turbine engine includes a frame member (110) and a forward ring (108) movable along an axial centerline (12) relative to the frame member (110). The forward ring (108) is movable between a first position and the second position. The thrust reverser system (100) additionally includes a cascade segment (116) slidably attached to the frame member (110) and rotatably attached to the forward ring (108). When the forward ring (108) is in the first position the cascade segment (116) is in a radially outer position outside the bypass passage, and when the forward ring (108) is in the second position, the cascade segment (116) is in a radially inner position at least partially within the bypass passage for changing a direction of a flow of air to generate reverse thrust.
摘要翻译：一种用于结合到燃气涡轮发动机的外罩组件（50）中的推力反向器系统（100）包括框架构件（110）和相对于框架构件（110）沿着轴向中心线（12）可移动的前环（108））。前环（108）可在第一位置和第二位置之间移动。推力反向器系统（100）另外包括可滑动地附接到框架构件（110）并且可旋转地附接到前环（108）的级联段（116）。当前环108处于第一位置时，叶栅段116处于旁路通道外的径向外部位置，并且当前环108处于第二位置时，叶栅段116为在至少部分位于旁路通道内的径向内部位置，用于改变空气流动的方向以产生反推力。

9. 发明公开

EP3171002A1 FAN CASE FOR USE IN A TURBOFAN ENGINE 审中-公开
标题翻译：用于涡扇发动机的风扇壳
公开(公告)号：EP3171002A1
公开(公告)日：2017-05-24
申请号：EP16196840.9
申请日：2016-11-02
申请人： General Electric Company
发明人： STUART, Alan Roy
IPC分类号： F02C7/045 , F02K3/068
CPC分类号： F02C7/042 , B64D29/00 , B64D33/02 , B64D2033/0206 , F02C7/045 , F02K3/06 , F02K3/068 , F05D2230/70 , F05D2250/314 , F05D2260/96 , Y02T50/672
摘要： A fan case 100 for use in a turbofan engine 10 is provided. The fan case 100 includes an aft portion 102 having a substantially cylindrical cross-sectional shape, and a forward portion 104 extending from the aft portion 102. A cross-sectional shape of the forward portion 104 progressively decreases in radial size as the forward portion 104 extends from the aft portion 102.
摘要翻译：提供了用于涡轮风扇发动机10的风扇壳体100。风扇壳体100包括具有大致圆柱形横截面形状的后部102和从后部102延伸的前部104.前部104的横截面形状在径向尺寸上逐渐减小，如前部104 从后部102延伸。

10. 发明公开

EP3027876A1 THRUST REVERSER SYSTEM WITH TRANSLATING-ROTATING HINGE ASSEMBLY 审中-公开
标题翻译：通过翻译一转动铰安排的反向推力系统
公开(公告)号：EP3027876A1
公开(公告)日：2016-06-08
申请号：EP14750671.1
申请日：2014-07-30
申请人： General Electric Company
发明人： STUART, Alan Roy
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , F05D2250/42 , F05D2250/70 , Y02T50/672
摘要： A thrust reverser system (12C) suitable for a high-bypass turbofan engine (10) of a type having a nacelle (12). The thrust reverser system (12C) includes a transcowl (34A) having a stowed, deployed and open positions. A hinge assembly (50) translationally and rotationally couples the transcowl (34A) to a fixed structure (13) that does not translate when the transcowl (34A) is translated in the aft direction. The hinge assembly (50) includes a first member (52) connected to the transcowl (34A) for translation therewith, and a fixed second member (58) that defines a channel (60) in which a portion of the first member (52) is slidably received. The first (52) and second (58) members are configured to enable the portion of the first member (52) to translate within the slider channel (60) in an aft direction corresponding to a translational movement of the transcowl (34A), and to enable the portion of the first member (52) to rotate within the channel (60) corresponding to a pivotal movement of the transcowl (34A).

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式