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1. 发明申请

US20120068003A1 WIRELESS SENSOR FOR AN AIRCRAFT PROPULSION SYSTEM 有权
标题翻译：无线传感器用于飞机推进系统
公开(公告)号：US20120068003A1
公开(公告)日：2012-03-22
申请号：US12884803
申请日：2010-09-17
申请人： Sanjay Bajekal , Peter G. Smith , Vijaya Ramaraju Lakamraju , Nicholas Charles Soldner
发明人： Sanjay Bajekal , Peter G. Smith , Vijaya Ramaraju Lakamraju , Nicholas Charles Soldner
IPC分类号： B64C27/00 , G06F19/00 , F01D25/00
CPC分类号： B64C27/008 , B64D2045/0085 , F01D21/003 , F05D2260/80
摘要： A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters.
摘要翻译：提供了一种用于无线监测具有多个转子叶片的飞机推进系统的方法，其中至少一些转子叶片具有内部隔室。该方法包括：提供具有初级线圈和一个或多个次级换能器的主换能器，每个次级换能器具有连接到传感器的次级线圈，其中所述次级换能器分别设置在所述内部隔间内; 使用由主换能器产生的磁场无线地为次级换能器供电; 使用相应的传感器监测来自每个内部隔室内的至少一个操作参数; 以及通过所述磁场将来自所述次级换能器的输出信号发送到所述主换能器，其中所述输出信号指示所监视的参数。

2. 发明授权

US08482434B2 Wireless sensor for an aircraft propulsion system 有权
标题翻译：用于飞机推进系统的无线传感器
公开(公告)号：US08482434B2
公开(公告)日：2013-07-09
申请号：US12884803
申请日：2010-09-17
申请人： Sanjay Bajekal , Peter G. Smith , Vijaya Ramaraju Lakamraju , Nicholas C. Soldner
发明人： Sanjay Bajekal , Peter G. Smith , Vijaya Ramaraju Lakamraju , Nicholas C. Soldner
IPC分类号： G08B21/00
CPC分类号： B64C27/008 , B64D2045/0085 , F01D21/003 , F05D2260/80
摘要： A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters.
摘要翻译：提供了一种用于无线监测具有多个转子叶片的飞机推进系统的方法，其中至少一些转子叶片具有内部隔室。该方法包括：提供具有初级线圈和一个或多个次级换能器的主换能器，每个次级换能器具有连接到传感器的次级线圈，其中所述次级换能器分别设置在所述内部隔间内; 使用由主换能器产生的磁场无线地为次级换能器供电; 使用相应的传感器监测来自每个内部隔室内的至少一个操作参数; 以及通过所述磁场将来自所述次级换能器的输出信号发送到所述主换能器，其中所述输出信号指示所监视的参数。

3. 发明授权

US09335051B2 Ceramic matrix composite combustor vane ring assembly 有权
标题翻译：陶瓷基复合燃烧器叶片环组件
公开(公告)号：US09335051B2
公开(公告)日：2016-05-10
申请号：US13181898
申请日：2011-07-13
申请人： David C. Jarmon , Peter G. Smith
发明人： David C. Jarmon , Peter G. Smith
IPC分类号： F23R3/60 , F23R3/16 , F01D9/04 , F01D5/28 , F01D9/02 , F23R3/00 , F23R3/06
CPC分类号： F23R3/16 , F01D5/284 , F01D9/023 , F01D9/042 , F23M2900/05002 , F23R3/002 , F23R3/005 , F23R3/06 , F23R3/60 , F23R2900/00012 , F23R2900/03042
摘要： A vane assembly has an outer support ring, an inner support ring, an outer liner ring, an inner liner ring, and a circumferential array of vanes. Each vane has a shell extending from an inboard end to an outboard end and at least partially through an associated aperture in the inner liner ring and an associated aperture in the outer liner ring. There is at least one of: an outer compliant member compliantly radially positioning the vane; and an inner compliant member compliantly radially positioning the vane.
摘要翻译：叶片组件具有外支撑环，内支撑环，外衬垫环，内衬环和周向阵列的叶片。每个叶片具有壳体，其从内侧端部延伸到外侧端部，并且至少部分地穿过内部衬套环中的相关联的孔和外部衬套环中的相关联的孔。至少一个：外部柔顺部件顺从地径向定位叶片; 以及顺应性地顺向地定位叶片的内部顺应构件。

4. 发明申请

US20180318312A1 SPLICE VARIANTS ASSOCIATED WITH NEOMORPHIC SF3B1 MUTANTS 审中-公开
公开(公告)号：US20180318312A1
公开(公告)日：2018-11-08
申请号：US15755225
申请日：2016-08-30
申请人： Lihua YU , Kian Huat LIM , Jacob D. FEALA , Silvia BUONAMICI , Yoshiharu MIZUI , Peter G. SMITH , Ping ZHU , Eunice Sun PARK , Michael W. SEILER , Marco Peter FEKKES , Eisai R&D Management Co., Ltd.
发明人： Lihua Yu , Kian Huat Lim , Jacob D. Feala , Silvia Buonamici , Yoshiharu Mizui , Peter G. Smith , Ping Zhu , Eunice Sun Park , Michael W. Seiler , Marco Peter Fekkes
IPC分类号： A61K31/55 , A61P35/00 , A61K31/4545 , A61K31/495 , C12Q1/6886 , C12Q1/02
CPC分类号： A61K31/55 , A61K31/4545 , A61K31/495 , A61P35/00 , C12Q1/025 , C12Q1/6806 , C12Q1/6841 , C12Q1/6886 , C12Q2600/106 , C12Q2600/158
摘要： Splice variants associated with neomorphic SF3B1 mutations are described herein. This application also relates to methods of detecting the described splice variants, and uses for diagnosing cancer, evaluating modulators of SF3B1, and methods of treating cancer associated with mutations in SF3B1.

5. 发明授权

US08585368B2 Hybrid structure airfoil 有权
标题翻译：混合翼型
公开(公告)号：US08585368B2
公开(公告)日：2013-11-19
申请号：US13331957
申请日：2011-12-20
申请人： Daniel V. Viens , Vincent C. Nardone , Peter G. Smith , James R. Strife , Foster P. Lamm
发明人： Daniel V. Viens , Vincent C. Nardone , Peter G. Smith , James R. Strife , Foster P. Lamm
IPC分类号： B23K5/18
CPC分类号： F01D5/147 , F01D5/16 , F01D5/282 , F04D29/023 , F04D29/324 , F04D29/388 , F05D2260/96 , F05D2300/603 , F05D2300/612 , F05D2300/615 , Y02T50/672 , Y02T50/673
摘要： A hybrid airfoil for a gas turbine engine is provided that includes a body and a panel. The body has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The body includes a plurality of cavities disposed in the first side of the body, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The panel is a load bearing structure operable to transfer loads to the body and receive loads from the body.
摘要翻译：提供了一种用于燃气涡轮发动机的混合翼型件，其包括主体和面板。主体具有与第一侧相对定向的第一侧和第二侧。第一和第二面在尖端，底座，前缘和后缘之间延伸。主体包括设置在主体的第一侧中的多个空腔，空腔向内朝向第二侧延伸。空腔共同形成开口。至少一个肋设置在空腔之间。一个搁板设置在开口周围。面板连接到搁架第一安装表面和肋上，并且其尺寸被设计成封闭开口。面板是承载结构，可操作以将负载传递到主体并从身体接收负载。

6. 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。

7. 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。

8. 发明申请

US20090325468A1 ABRASIVE WATERJET MACHINING AND METHOD TO MANUFACTURE A CURVED ROTOR BLADE RETENTION SLOT 有权
标题翻译：磨光水刀加工及制造弯曲转子叶片保持槽的方法
公开(公告)号：US20090325468A1
公开(公告)日：2009-12-31
申请号：US12164311
申请日：2008-06-30
申请人： Tahany Ibrahim El-Wardany , Peter G. Smith , Warren Reynolds , Eugene Ng , Kay V. Adams
发明人： Tahany Ibrahim El-Wardany , Peter G. Smith , Warren Reynolds , Eugene Ng , Kay V. Adams
IPC分类号： B24C1/00 , B24C5/00
CPC分类号： B23P15/006 , B24C1/045 , F01D5/3007 , F05D2230/10 , F05D2250/71
摘要： A method of machining a blade retention slot with an abrasive water jet machining. A straight blade retention slot along an X-axis then a at least one side of the straight blade retention slot is abrasive water jet machined to generate a curved side of the blade retention slot defined within an X-Y plane.
摘要翻译：用磨料水喷射机加工刀片固定槽的方法。沿X轴然后直刀片保持槽的至少一侧的直刀片保持狭槽是被研磨的磨料水喷射，以产生限定在X-Y平面内的刀片保持槽的弯曲侧。

9. 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。

10. 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。

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