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1. 发明申请

US20120321448A1 AIRCRAFT POWERPLANT 有权
标题翻译：飞机POWERPLANT
公开(公告)号：US20120321448A1
公开(公告)日：2012-12-20
申请号：US13523489
申请日：2012-06-14
申请人： Kenneth M. Pesyna , Bryan Henry Lerg , Michael Abraham Karam
发明人： Kenneth M. Pesyna , Bryan Henry Lerg , Michael Abraham Karam
IPC分类号： F01D25/00 , F01D1/04
CPC分类号： F02K3/077 , F02C7/18 , F02K3/115 , Y02T50/675
摘要： A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat areas for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.
摘要翻译：公开了一种燃气涡轮发动机系统，其包括可以构造为风扇旁通管道或第三流旁路管道的铁芯通道和旁路通道。核心通道和旁路通道在离开飞机之前通过喷嘴流动。喷嘴包括能够改变喷嘴的构造的可动构件。在一种形式中，可移动构件能够改变用于从芯通道和旁路通道接收工作流体的喷嘴的部分的喉部区域。旁路通道可以包括一个分支。在一种形式中，分支可以包括热交换器。旁路通道还可以向喷嘴的一个或多个部分提供冷却，例如冷却到喷嘴的甲板上。

2. 发明申请

US20110095099A1 MECHANISM FOR A VECTORING EXHAUST NOZZLE 有权
标题翻译：机构排气喷嘴
公开(公告)号：US20110095099A1
公开(公告)日：2011-04-28
申请号：US12951872
申请日：2010-11-22
申请人： Kenneth M. Pesyna , Jeffrey P. Henkle
发明人： Kenneth M. Pesyna , Jeffrey P. Henkle
IPC分类号： B05B12/00
CPC分类号： B64C15/02
摘要： A nozzle device defines a passageway including an outlet to discharge working fluid to produce thrust. This device includes a vectoring mechanism having three or more vanes pivotally mounted across the passageway and a linkage pivotally coupling the vanes together. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed to a second one of the vanes to pivot therewith about a second pivot axis, and a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. A first connecting link pivotally couples the first arm and the second arm together, and a second connecting link pivotally couples the third arm and the fourth arm together. The relative angular positioning of the arms with respect to the corresponding pivot axes and/or the arm links can be varied to define different vectoring schedules with the mechanism linkage. In one particular form, the nozzle is utilized with a lift fan of an aircraft to perform V/STOL operations.
摘要翻译：喷嘴装置限定了包括出口以排出工作流体以产生推力的通道。该装置包括具有三个或更多个叶片的矢量化机构，该叶片枢转地安装在通道上，以及将叶片枢转地联接在一起的连杆。这种联动装置包括固定到第一叶片上的第一臂，以绕第一枢转轴线枢转，第二臂和固定到第二叶片上的第三臂绕着第二枢轴转动，臂固定到第三个叶片上以围绕第三枢转轴线枢转。第一连接连杆将第一臂和第二臂枢转地连接在一起，第二连接杆将第三臂和第四臂枢转连接在一起。可以改变臂相对于相应的枢转轴线和/或臂链节的相对角度定位以通过机构联动来限定不同的矢量计划。在一种特定形式中，喷嘴与飞机的提升风扇一起使用以执行V / STOL操作。

3. 发明授权

US4884748A Fairing flap arrangement 失效
标题翻译：整流罩安排
公开(公告)号：US4884748A
公开(公告)日：1989-12-05
申请号：US239738
申请日：1988-09-02
申请人： Eric J. Ward , Kevin L. Worley , Kenneth M. Pesyna
发明人： Eric J. Ward , Kevin L. Worley , Kenneth M. Pesyna
IPC分类号： F02K1/12
CPC分类号： F02K1/1223 , F02K1/1269 , Y02T50/671
摘要： An external fairing flap (26) is provided with an hydraulic spring (42, 44) for causing the external flap (26) to follow the motion of an exhaust nozzle control flap (18). The external flap (26) is hinged (32) at the leading edge thereof, and contacts the control flap (18) via corresponding rubstrips (40, 36) at the flap trailing edges (28, 38).
摘要翻译：外部整流罩（26）设置有用于使外部挡板（26）跟随排气喷嘴控制挡板（18）的运动的液压弹簧（42,44）。外部翼片（26）在其前缘处铰接（32），并通过翼片后缘（28,38）处的对应的搓纸（40,36）与控制翼片（18）接触。

4. 发明授权

US10001084B2 Aircraft powerplant with moveable nozzle member 有权
公开(公告)号：US10001084B2
公开(公告)日：2018-06-19
申请号：US13523315
申请日：2012-06-14
申请人： Kenneth M. Pesyna , Bryan Henry Lerg , Michael Abraham Karam
发明人： Kenneth M. Pesyna , Bryan Henry Lerg , Michael Abraham Karam
IPC分类号： F02K3/077 , F02K3/115 , F02C7/18
CPC分类号： F02K3/077 , F02C7/18 , F02K3/115 , Y02T50/675
摘要： A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat area for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.

5. 发明授权

US08245495B2 Mechanism for a vectoring exhaust nozzle 有权
标题翻译：导向排气喷嘴的机构
公开(公告)号：US08245495B2
公开(公告)日：2012-08-21
申请号：US12951872
申请日：2010-11-22
申请人： Kenneth M. Pesyna , Jeffrey P. Henkle
发明人： Kenneth M. Pesyna , Jeffrey P. Henkle
IPC分类号： B63H11/00
CPC分类号： B64C15/02
摘要： A nozzle device defines a passageway including an outlet to discharge working fluid to produce thrust. This device includes a vectoring mechanism having three or more vanes pivotally mounted across the passageway and a linkage pivotally coupling the vanes together. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed to a second one of the vanes to pivot therewith about a second pivot axis, and a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. A first connecting link pivotally couples the first arm and the second arm together, and a second connecting link pivotally couples the third arm and the fourth arm together. The relative angular positioning of the arms with respect to the corresponding pivot axes and/or the arm links can be varied to define different vectoring schedules with the mechanism linkage. In one particular form, the nozzle is utilized with a lift fan of an aircraft to perform V/STOL operations.
摘要翻译：喷嘴装置限定了包括出口以排出工作流体以产生推力的通道。该装置包括具有三个或更多个叶片的矢量化机构，该叶片枢转地安装在通道上，以及将叶片枢转地联接在一起的连杆。这种联动装置包括固定到第一叶片上的第一臂，以绕第一枢转轴线枢转，第二臂和固定到第二叶片上的第三臂绕着第二枢轴转动，臂固定到第三个叶片上以围绕第三枢转轴线枢转。第一连接连杆将第一臂和第二臂枢转地连接在一起，第二连接杆将第三臂和第四臂枢转连接在一起。可以改变臂相对于相应的枢转轴线和/或臂链节的相对角度定位以通过机构联动来限定不同的矢量计划。在一种特定形式中，喷嘴与飞机的提升风扇一起使用以执行V / STOL操作。

6. 发明授权

US08745990B2 Gas turbine engine with integrated electric starter/generator 有权
标题翻译：带集成电动起动器/发电机的燃气轮机
公开(公告)号：US08745990B2
公开(公告)日：2014-06-10
申请号：US12694786
申请日：2010-01-27
申请人： Philip Burkholder , Rigoberto J. Rodriguez , Steven Gagne , Kenneth M. Pesyna
发明人： Philip Burkholder , Rigoberto J. Rodriguez , Steven Gagne , Kenneth M. Pesyna
IPC分类号： F02N11/04
CPC分类号： F01D9/065 , F01D15/10 , F02C7/275 , F02C7/32 , F04D25/04 , F04D25/0606 , F16L9/003 , Y02T50/671
摘要： An electrical machine is embedded into the compressor assembly of a gas turbine engine. An electrical system interface module distributes electrical current to and from the embedded electrical machine for starting the gas turbine engine and for operating accessory components. Accordingly, the gas turbine engine and accessory components can be started and operated without a power-takeoff shaftline and without an external accessory gearbox.
摘要翻译：电机被嵌入到燃气轮机的压缩机组件中。电气系统接口模块将电流分配给嵌入式电机，以启动燃气涡轮发动机和操作附件部件。因此，燃气涡轮发动机和辅助部件可以在没有动力输出轴线和没有外部附件齿轮箱的情况下启动和操作。

7. 发明申请

US20120317957A1 AIRCRAFT POWERPLANT 有权
标题翻译：飞机POWERPLANT
公开(公告)号：US20120317957A1
公开(公告)日：2012-12-20
申请号：US13523315
申请日：2012-06-14
申请人： Kenneth M. Pesyna , Bryan Henry Lerg , Michael Abraham Karam
发明人： Kenneth M. Pesyna , Bryan Henry Lerg , Michael Abraham Karam
IPC分类号： F02K3/02 , F02K99/00 , F02K1/46
CPC分类号： F02K3/077 , F02C7/18 , F02K3/115 , Y02T50/675
摘要： A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat area for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.
摘要翻译：公开了一种燃气涡轮发动机系统，其包括可以构造为风扇旁通管道或第三流旁路管道的铁芯通道和旁路通道。核心通道和旁路通道在离开飞机之前通过喷嘴流动。喷嘴包括能够改变喷嘴的构造的可动构件。在一种形式中，可移动构件能够改变从芯通道和旁路通道接收工作流体的喷嘴的部分的喉部区域。旁路通道可以包括一个分支。在一种形式中，分支可以包括热交换器。旁路通道还可以向喷嘴的一个或多个部分提供冷却，例如冷却到喷嘴的甲板上。

8. 发明授权

US07836681B2 Mechanism for a vectoring exhaust nozzle 有权
标题翻译：导向排气喷嘴的机构
公开(公告)号：US07836681B2
公开(公告)日：2010-11-23
申请号：US11451835
申请日：2006-06-13
申请人： Kenneth M. Pesyna , Jeffrey P. Henkle
发明人： Kenneth M. Pesyna , Jeffrey P. Henkle
IPC分类号： F02K1/00
CPC分类号： B64C15/02
摘要： A nozzle device defines a passageway including an outlet to discharge working fluid to produce thrust. This device includes a vectoring mechanism having three or more vanes pivotally mounted across the passageway and a linkage pivotally coupling the vanes together. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed to a second one of the vanes to pivot therewith about a second pivot axis, and a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. A first connecting link pivotally couples the first arm and the second arm together, and a second connecting link pivotally couples the third arm and the fourth arm together. The relative angular positioning of the arms with respect to the corresponding pivot axes and/or the arm links can be varied to define different vectoring schedules with the mechanism linkage. In one particular form, the nozzle is utilized with a lift fan of an aircraft to perform V/STOL operations.
摘要翻译：喷嘴装置限定了包括出口以排出工作流体以产生推力的通道。该装置包括具有三个或更多个叶片的矢量化机构，该叶片枢转地安装在通道上，以及将叶片枢转地联接在一起的连杆。这种联动装置包括固定到第一叶片上的第一臂，以绕第一枢转轴线枢转，第二臂和固定到第二叶片上的第三臂绕着第二枢轴转动，臂固定到第三个叶片上以围绕第三枢转轴线枢转。第一连接连杆将第一臂和第二臂枢转地连接在一起，第二连接杆将第三臂和第四臂枢转连接在一起。可以改变臂相对于相应的枢转轴线和/或臂链节的相对角度定位以通过机构联动来限定不同的矢量计划。在一种特定形式中，喷嘴与飞机的提升风扇一起使用以执行V / STOL操作。

9. 发明授权

US09091229B2 Aircraft powerplant 有权
标题翻译：飞机发动机
公开(公告)号：US09091229B2
公开(公告)日：2015-07-28
申请号：US13523489
申请日：2012-06-14
申请人： Kenneth M. Pesyna , Bryan Henry Lerg , Michael Abraham Karam
发明人： Kenneth M. Pesyna , Bryan Henry Lerg , Michael Abraham Karam
IPC分类号： F01D25/00 , F02K3/077 , F02K3/115 , F02C7/18
CPC分类号： F02K3/077 , F02C7/18 , F02K3/115 , Y02T50/675
摘要： A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat areas for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.
摘要翻译：公开了一种燃气涡轮发动机系统，其包括可以构造为风扇旁通管道或第三流旁路管道的铁芯通道和旁路通道。核心通道和旁路通道在离开飞机之前通过喷嘴流动。喷嘴包括能够改变喷嘴的构造的可动构件。在一种形式中，可移动构件能够改变用于从芯通道和旁路通道接收工作流体的喷嘴的部分的喉部区域。旁路通道可以包括一个分支。在一种形式中，分支可以包括热交换器。旁路通道还可以向喷嘴的一个或多个部分提供冷却，例如冷却到喷嘴的甲板上。

10. 发明申请

US20110018273A1 STARTER/GENERATOR INTEGRATED INTO COMPRESSOR OF TURBINE ENGINE 审中-公开
标题翻译：集成到涡轮发动机压缩机的起动机/发电机
公开(公告)号：US20110018273A1
公开(公告)日：2011-01-27
申请号：US12509887
申请日：2009-07-27
申请人： Philip Burkholder , Rigoberto J. Rodriguez , Steven Gagne , Kenneth M. Pesyna
发明人： Philip Burkholder , Rigoberto J. Rodriguez , Steven Gagne , Kenneth M. Pesyna
IPC分类号： H02K7/18 , F02C6/04
CPC分类号： F02C7/275 , F01D9/065 , F01D15/10 , F02C7/32 , F04D19/02 , F04D25/0606
摘要： A turbine engine compressor has a rotor including rotating compressor discs. Magnets are positioned on the rotating compressor discs. Electrical coils are positioned in a stationary guide vane internal ring so as to create an electric machine providing starting torque to a rotor, and/or generating electrical energy once the rotor is rotating.
摘要翻译：涡轮发动机压缩机具有包括旋转压缩机盘的转子。磁铁位于旋转的压缩机盘上。电线圈定位在固定的导向叶片内环中，以便在转子旋转时产生向转子提供启动扭矩的电机和/或产生电能。

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