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1. 发明授权

US07530787B2 Rotor hub fairing system for a counter-rotating, coaxial rotor system 有权
标题翻译：转子轮毂整流罩系统，用于反转，同轴转子系统
公开(公告)号：US07530787B2
公开(公告)日：2009-05-12
申请号：US11436362
申请日：2006-05-18
申请人： Fabio P. Bertolotti , Mark W. Scott , Brian E. Wake , T. Alan Egolf , Duane C. McCormick , Ebru Usta , Stuart S. Ochs
发明人： Fabio P. Bertolotti , Mark W. Scott , Brian E. Wake , T. Alan Egolf , Duane C. McCormick , Ebru Usta , Stuart S. Ochs
IPC分类号： B64C27/50
CPC分类号： B64C27/12 , B64C1/00 , B64C7/00 , B64C27/04 , B64C27/10 , B64C27/14 , B64C27/20
摘要： A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system reduces the total drag on a dual, counter-rotating, coaxial rotor system. Other aerodynamic structures may be mounted to the shaft fairing, hub fairings and airframe to facilitate flow around the upper and lower hub fairings to reduce flow separation and drag.
摘要翻译：转子轮毂整流罩系统包括上部轮毂整流罩，下部轮毂整流罩和在其间的整流装置。转子轮毂整流罩系统减少了双重反向旋转同轴转子系统的总阻力。其他空气动力学结构可以安装到轴整流罩，轮毂整流罩和机身，以便于围绕上部和下部轮毂整流罩流动以减少流动分离和阻力。

2. 发明授权

US08347633B2 Gas turbine engine with variable geometry fan exit guide vane system 有权
标题翻译：具有可变几何风扇出口导叶系统的燃气轮机
公开(公告)号：US08347633B2
公开(公告)日：2013-01-08
申请号：US11829213
申请日：2007-07-27
申请人： Peter G. Smith , Stuart S. Ochs
发明人： Peter G. Smith , Stuart S. Ochs
IPC分类号： F02C7/045
CPC分类号： F01D17/162 , F04D29/563 , F05D2220/36
摘要： A turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.
摘要翻译：涡轮风扇发动机包括具有多个周向间隔开的径向延伸的风扇出口导向叶片的可变几何风扇出口导叶（FEGV）系统。风扇出口导向叶片在标称位置和旋转位置之间的旋转选择性地改变风扇旁路流动路径以允许在各种飞行条件下的有效操作。

3. 发明申请

US20120124964A1 GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY 审中-公开
标题翻译：具有改进燃油效率的燃气涡轮发动机
公开(公告)号：US20120124964A1
公开(公告)日：2012-05-24
申请号：US13361987
申请日：2012-01-31
申请人： Karl L. Hasel , Peter G. Smith , Stuart S. Ochs
发明人： Karl L. Hasel , Peter G. Smith , Stuart S. Ochs
IPC分类号： F02K3/02
CPC分类号： F01D17/162 , F04D29/563 , F05D2220/36
摘要： A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has an expansion ratio greater than or equal to about 5. The fan has a bypass ratio greater than or equal to about 8. In other features, a turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.
摘要翻译：涡轮风扇发动机包括由低压涡轮机通过齿轮减速器驱动的风扇。齿轮减速器具有大于或等于约2.4的齿轮比。低压涡轮机具有大于或等于约5的膨胀比。风扇具有大于或等于约8的旁通比。在其它特征中，涡轮风扇发动机包括可变几何风扇出口导叶（FEGV）系统，其具有周向间隔开的径向延伸的风扇出口导叶的多个。风扇出口导向叶片在标称位置和旋转位置之间的旋转选择性地改变风扇旁路流动路径以允许在各种飞行条件下的有效操作。

4. 发明申请

US20090097967A1 GAS TURBINE ENGINE WITH VARIABLE GEOMETRY FAN EXIT GUIDE VANE SYSTEM 有权
标题翻译：气体涡轮发动机与可变几何风扇离开导向风扇系统
公开(公告)号：US20090097967A1
公开(公告)日：2009-04-16
申请号：US11829213
申请日：2007-07-27
申请人： Peter G. Smith , Stuart S. Ochs
发明人： Peter G. Smith , Stuart S. Ochs
IPC分类号： F02C9/18 , F01D17/16
CPC分类号： F01D17/162 , F04D29/563 , F05D2220/36
摘要： A turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.
摘要翻译：涡轮风扇发动机包括具有多个周向间隔开的径向延伸的风扇出口导向叶片的可变几何风扇出口导叶（FEGV）系统。风扇出口导向叶片在标称位置和旋转位置之间的旋转选择性地改变风扇旁路流动路径以允许在各种飞行条件下的有效操作。

5. 发明授权

US09157368B2 Active flow control for nacelle inlet 有权
标题翻译：机舱入口的主动流量控制
公开(公告)号：US09157368B2
公开(公告)日：2015-10-13
申请号：US11850300
申请日：2007-09-05
申请人： Wayne Hurwitz , Stuart S. Ochs
发明人： Wayne Hurwitz , Stuart S. Ochs
IPC分类号： F02C7/057 , B64D33/02 , F01D17/02
CPC分类号： F02C7/057 , B64D33/02 , B64D2033/0226 , B64D2033/0286 , F01D17/02 , F05D2270/301 , F05D2270/44 , F05D2270/62
摘要： The disclosed turbine engine includes a fan nacelle surrounding a fan and including an inlet arranged upstream from the fan. The inlet includes an inlet surface having a boundary layer flow. A flow control actuator is in fluid communication with the inlet surface. A boundary layer sensing device is associated with the inlet surface for detecting a boundary layer condition at the inlet surface. A controller is in communication with the flow control actuator and the boundary layer sensing device. The controller is programmed to command the flow control actuator in response to the boundary layer sensing device detecting an undesired boundary layer condition. In this manner, the flow control actuator generates a desired boundary layer condition.
摘要翻译：所公开的涡轮发动机包括围绕风扇并包括布置在风扇上游的入口的风扇机舱。入口包括具有边界层流的入口表面。流量控制致动器与入口表面流体连通。边界层感测装置与入口表面相关联，用于检测入口表面处的边界层状态。控制器与流量控制致动器和边界层感测装置通信。控制器被编程为响应于边界层感测装置检测不期望的边界层条件来命令流量控制致动器。以这种方式，流量控制致动器产生期望的边界层条件。

6. 发明申请

US20120222398A1 GAS TURBINE ENGINE WITH GEARED ARCHITECTURE 审中-公开
标题翻译：具有齿轮架构的气体涡轮发动机
公开(公告)号：US20120222398A1
公开(公告)日：2012-09-06
申请号：US13346100
申请日：2012-01-09
申请人： Peter G. Smith , Stuart S. Ochs , Frederick M. Schwarz
发明人： Peter G. Smith , Stuart S. Ochs , Frederick M. Schwarz
IPC分类号： F02K3/04
CPC分类号： F01D17/162 , F04D29/563 , F05D2220/36
摘要： A turbofan engine includes a geared architecture and a fan variable area nozzle axially movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
摘要翻译：涡轮风扇发动机包括齿轮架构和相对于风扇机舱可轴向移动的风扇可变区喷嘴，以改变风扇喷嘴出口区域，并在发动机运行期间调节风扇旁路气流的压力比。

7. 发明申请

US20120222397A1 GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO 有权
公开(公告)号：US20120222397A1
公开(公告)日：2012-09-06
申请号：US13340761
申请日：2011-12-30
申请人： Peter G. Smith , Stuart S. Ochs , Frederick M. Schwarz
发明人： Peter G. Smith , Stuart S. Ochs , Frederick M. Schwarz
IPC分类号： F02K3/075
CPC分类号： F01D17/162 , F04D29/563 , F05D2220/36
摘要： A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

8. 发明申请

US20090060704A1 ACTIVE FLOW CONTROL FOR NACELLE INLET 有权
标题翻译：主动流量控制为NACELLE进口
公开(公告)号：US20090060704A1
公开(公告)日：2009-03-05
申请号：US11850300
申请日：2007-09-05
申请人： Wayne Hurwitz , Stuart S. Ochs
发明人： Wayne Hurwitz , Stuart S. Ochs
IPC分类号： F02B27/02
CPC分类号： F02C7/057 , B64D33/02 , B64D2033/0226 , B64D2033/0286 , F01D17/02 , F05D2270/301 , F05D2270/44 , F05D2270/62
摘要： The disclosed turbine engine includes a fan nacelle surrounding a fan and including an inlet arranged upstream from the fan. The inlet includes an inlet surface having a boundary layer flow. A flow control actuator is in fluid communication with the inlet surface. A boundary layer sensing device is associated with the inlet surface for detecting a boundary layer condition at the inlet surface. A controller is in communication with the flow control actuator and the boundary layer sensing device. The controller is programmed to command the flow control actuator in response to the boundary layer sensing device detecting an undesired boundary layer condition. In this manner, the flow control actuator generates a desired boundary layer condition.
摘要翻译：所公开的涡轮发动机包括围绕风扇并包括布置在风扇上游的入口的风扇机舱。入口包括具有边界层流的入口表面。流量控制致动器与入口表面流体连通。边界层感测装置与入口表面相关联，用于检测入口表面处的边界层状态。控制器与流量控制致动器和边界层感测装置通信。控制器被编程为响应于边界层感测装置检测不期望的边界层条件来命令流量控制致动器。以这种方式，流量控制致动器产生期望的边界层条件。

9. 发明授权

US08459035B2 Gas turbine engine with low fan pressure ratio 有权
标题翻译：具有低风扇压力比的燃气轮机
公开(公告)号：US08459035B2
公开(公告)日：2013-06-11
申请号：US13340761
申请日：2011-12-30
申请人： Peter G. Smith , Stuart S. Ochs , Frederick M. Schwarz
发明人： Peter G. Smith , Stuart S. Ochs , Frederick M. Schwarz
IPC分类号： F02K1/00
CPC分类号： F01D17/162 , F04D29/563 , F05D2220/36
摘要： A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
摘要翻译：涡轮风扇发动机包括相对于风扇机舱可轴向移动的风扇可变区域喷嘴，以改变风扇喷嘴出口区域，并且在发动机运行期间调节风扇旁路气流的压力比。

10. 发明申请

US20120233981A1 GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO 审中-公开
标题翻译：具有低风扇压力比的燃气涡轮发动机
公开(公告)号：US20120233981A1
公开(公告)日：2012-09-20
申请号：US13484308
申请日：2012-05-31
申请人： Peter G. Smith , Stuart S. Ochs , Frederick M. Schwarz
发明人： Peter G. Smith , Stuart S. Ochs , Frederick M. Schwarz
IPC分类号： F02K3/075
CPC分类号： F01D17/162 , F04D29/563 , F05D2220/36
摘要： A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
摘要翻译：涡轮风扇发动机包括相对于风扇机舱可轴向移动的风扇可变区域喷嘴，以改变风扇喷嘴出口区域，并且在发动机运行期间调节风扇旁路气流的压力比。

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