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1. 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。

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。

4. 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。

5. 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。

6. 发明申请

US20080098894A1 Acoustic degassing heat exchanger 审中-公开
标题翻译：声脱气换热器
公开(公告)号：US20080098894A1
公开(公告)日：2008-05-01
申请号：US11590945
申请日：2006-11-01
申请人： Daniel R. Sabatino , Peter G. Smith , Louis Chiappetta , Jeremiah C. Lee , Robert Hans Schlinker
发明人： Daniel R. Sabatino , Peter G. Smith , Louis Chiappetta , Jeremiah C. Lee , Robert Hans Schlinker
IPC分类号： B01D53/22
CPC分类号： B01D19/0031 , B01D19/0078 , F23K2900/05082
摘要： A fuel delivery system includes a fuel stabilization unit that receives vibratory energy for mixing fuel within fuel passages to improve the removal of dissolved oxygen from an oxygen containing fuel. A vibration generator transmits vibratory energy into the fuel stabilization unit to induce mixing of fuel. Vibratory energy is directed into the fuel to create enhanced mixing by inducing large-scale secondary flow motions that circulates fuel from a center flow area toward an oxygen permeable surface to improve overall fuel deoxygenation as more of the fuel is placed in adjacent contact with the oxygen permeable membranes.
摘要翻译：燃料输送系统包括燃料稳定单元，其接收用于在燃料通道内混合燃料的振动能量以改善从含氧燃料中除去溶解氧。振动发生器将振动能量传递到燃料稳定单元中以引起燃料的混合。振动能量被引导到燃料中以通过引起大规模的二次流动运动来引起增强的混合，其将燃料从中心流动区域向氧气渗透表面循环，以改善总体燃料脱氧，因为更多的燃料被放置在与氧气相邻的位置渗透膜。

7. 发明授权

US5172553A Convective, temperature-equalizing system for minimizing cover-to-base turbine casing temperature differentials 失效
标题翻译：对流，温度均衡系统，用于最大限度地减少覆盖到基础的涡轮机壳体温差
公开(公告)号：US5172553A
公开(公告)日：1992-12-22
申请号：US823420
申请日：1992-01-21
申请人： Serge P. Barton , Peter G. Smith
发明人： Serge P. Barton , Peter G. Smith
IPC分类号： F01D25/12 , F01D25/10 , F01K13/00
CPC分类号： F01D25/10 , F01K13/006
摘要： A method and apparatus wherein, during time periods when a turbine is off-line and in a restart-ready condition, residual steam is circulated in the turbine between the cover and base of the turbine such that the cover and base are maintained at generally equal temperatures.
摘要翻译：一种方法和装置，其中在涡轮机离线并且处于重新启动状态的时间段期间，残余蒸汽在涡轮机中在涡轮机的盖和基座之间循环，使得盖和基座保持在大致相等温度。

8. 发明授权

US4608860A Stall detector 失效
标题翻译：失速探测器
公开(公告)号：US4608860A
公开(公告)日：1986-09-02
申请号：US750125
申请日：1985-07-01
申请人： Michael G. Charrier , Peter G. Smith
发明人： Michael G. Charrier , Peter G. Smith
IPC分类号： F01D17/08 , F04D27/00 , G01M15/00
CPC分类号： F01D17/08 , F04D27/001
摘要： Compressor discharge pressure (CDP) in a gas turbine engine is sensed. A fall in CDP is interpreted as indicating compressor stall.
摘要翻译：感测到燃气涡轮发动机中的压缩机排放压力（CDP）。 CDP的下降被解释为表示压缩机失速。

9. 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.

10. 发明授权

US08083489B2 Hybrid structure fan blade 有权
标题翻译：混合风扇叶片
公开(公告)号：US08083489B2
公开(公告)日：2011-12-27
申请号：US12425133
申请日：2009-04-16
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： F01D5/18
CPC分类号： F01D5/147 , F01D5/282 , F04D29/023 , F04D29/324 , F04D29/388 , F05D2300/43 , F05D2300/437 , F05D2300/603 , F05D2300/615
摘要： A hybrid fan blade for a gas turbine engine is provided that includes an airfoil and a composite panel. The airfoil 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 airfoil includes a plurality of cavities disposed in the first side of the airfoil, 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 composite panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.
摘要翻译：提供了一种用于燃气涡轮发动机的混合风扇叶片，其包括翼型件和复合板。翼型件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。翼型件包括设置在翼型件的第一侧中的多个空腔，这些空腔朝向第二侧向内延伸。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。复合板被附接到搁架第一安装表面和肋上，并且其尺寸被设计成包围开口。第一复合板是承载结构，可操作以将载荷传递到翼型件并从翼型接收载荷。

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