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81. 发明申请

US20120237335A1 GAS TURBINE ENGINE WITH GEARED ARCHITECTURE 有权
标题翻译：具有齿轮架构的气体涡轮发动机
公开(公告)号：US20120237335A1
公开(公告)日：2012-09-20
申请号：US13484722
申请日：2012-05-31
申请人： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
发明人： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
IPC分类号： F01D15/12
CPC分类号： F01D5/027 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2240/70 , F05D2260/34 , F05D2260/4031 , F05D2260/40311
摘要： A geared architecture with a flex mount for a fan drive gear system.
摘要翻译：具有用于风扇驱动齿轮系统的柔性安装座的齿轮架构。

82. 发明申请

US20120237334A1 GAS TURBINE ENGINE GEAR TRAIN 有权
标题翻译：气体涡轮发动机齿轮火车
公开(公告)号：US20120237334A1
公开(公告)日：2012-09-20
申请号：US13340737
申请日：2011-12-30
申请人： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
发明人： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
IPC分类号： F01D15/12 , F16H57/08
CPC分类号： F02C7/36 , F01D5/027 , F02C3/107 , F02K3/06 , F05D2220/36 , F05D2240/70 , F05D2260/34 , F05D2260/4031 , F05D2260/40311 , F16H1/28 , F16H57/0423 , F16H57/0486 , F16H2057/085
摘要： An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3
摘要翻译：行星齿轮系包括支撑与太阳齿轮啮合的星形齿轮的载体。环形齿轮围绕并与星形齿轮啮合。星形齿轮支撑在相应的轴颈轴承上。每个轴颈轴承包括周向轴颈表面，并且每个星形齿轮包括与相应的轴颈轴承的周向轴颈表面接触的径向内部轴颈表面。行星齿轮系具有大于或等于约2.3的齿轮减速比

83. 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。

84. 发明授权

US07857257B2 Aircraft thermal management system with reduced exhaust re-ingestion 有权
标题翻译：飞机热管理系统减少排气再摄入
公开(公告)号：US07857257B2
公开(公告)日：2010-12-28
申请号：US11515020
申请日：2006-09-01
申请人： Frederick M. Schwarz
发明人： Frederick M. Schwarz
IPC分类号： B64D33/02
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/0273 , F02C7/055
摘要： A thermal management system includes a cooling duct system that locates a ram air intake and an exhaust through a first aircraft surface above a second aircraft surface which locates a fan intake. During ground operations, an anti-re-ingestion door is open and a ram air door is closed such that the fan system may draw relatively cooler air from below the aircraft and exhaust the heated air above the aircraft to minimize re-ingestion of the heated exhaust. During flight operations, the anti-re-ingestion door is closed and the ram air door is open such that ram airflow communicates through the fan system prior to communication through the heat exchanger. Both the anti-re-ingestion door and the ram air door may also be operated in flight.
摘要翻译：热管理系统包括冷却管道系统，该冷却管道系统通过定位风扇进气口的第二飞行器表面上方的第一飞机表面定位冲压进气口和排气口。在地面操作期间，防反射门打开，并且压头空气门被关闭，使得风扇系统可以从飞行器下方抽取相对较冷的空气并排出飞机上方的被加热的空气，以最小化加热的排气。在飞行操作期间，防止再吸入门关闭，并且冲压气门打开，使得冲压气流在通过热交换器通信之前通过风扇系统连通。抗再摄入门和冲压空气门也可以在飞行中操作。

85. 发明授权

US07765788B2 Cooling exchanger duct 有权
标题翻译：冷却交换器管道
公开(公告)号：US07765788B2
公开(公告)日：2010-08-03
申请号：US11481550
申请日：2006-07-06
申请人： Frederick M. Schwarz
发明人： Frederick M. Schwarz
IPC分类号： F02K99/00
CPC分类号： F02C7/14 , F02K3/115 , Y02T50/675
摘要： A heat exchange system for use in operating equipment in which a working fluid is utilized in providing selected operations thereof, including for use in lubricating systems for aircraft turbofan engine equipment, the heat exchange system for providing air and working fluid heat exchanges to cool the working fluid at selectively variable rates in the operating equipment developed airstreams. A heat exchanger core is provided in a controlled air flow duct system opening at its entrance to those airstreams and having its outlet end opening downstream in those airstreams.
摘要翻译：一种用于操作设备的热交换系统，其中使用工作流体来提供其选择的操作，包括用于飞机涡轮风扇发动机设备的润滑系统，用于提供空气和工作流体热交换的热交换系统以冷却工作在操作设备中选择性变化的流体开发出气流。热交换器芯设置在受控的空气流动管道系统中，在其入口处开口，并且其出口端在这些气流中向下游开口。

86. 发明申请

US20100013242A1 Aircraft combination engines plural airflow conveyances system 失效
标题翻译：飞机组合引擎多重气流运输系统
公开(公告)号：US20100013242A1
公开(公告)日：2010-01-21
申请号：US11804429
申请日：2007-05-18
申请人： Frederick M. Schwarz , Brian M. Fentress
发明人： Frederick M. Schwarz , Brian M. Fentress
IPC分类号： F01B21/04 , H02K23/52 , F01D15/10
CPC分类号： F01D13/02 , F02C5/06 , F02C6/08 , F05D2220/76
摘要： An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being a plurality of air transfer ducts each extending from a different location in the gas turbine engine so as to be capable to provide air in each of those air transfer ducts at one end thereof at pressures differing from one another and connected at the other end of each to the air intake to transfer air thereto.
摘要翻译：用于产生具有燃气涡轮发动机产生力的力的发动机组合和设置在该组合中的内燃机作为具有进气口的间歇式内燃机产生力，存在多个空气传送管道，每个空气传送管道从不同位置延伸燃气涡轮发动机，以便能够在其一端处在彼此不同的压力下在这些空气输送管道的每一个中提供空气，并且在每个空气传输管道的另一端连接到进气口以将空气输送到其上。

87. 发明授权

US07485981B2 Aircraft combination engines complemental connection and operation 有权
标题翻译：飞机组合引擎互补连接和运行
公开(公告)号：US07485981B2
公开(公告)日：2009-02-03
申请号：US11801266
申请日：2007-05-09
申请人： Frederick M. Schwarz , Andrew P. Berryann , Brian M. Fentress
发明人： Frederick M. Schwarz , Andrew P. Berryann , Brian M. Fentress
IPC分类号： F01D41/00
CPC分类号： F02C7/275 , F02C5/06 , F02C7/268 , F02C7/32 , F05D2220/50
摘要： A power generation system for propelling, and generating electrical power in, an aircraft, using a gas turbine engine coupled to a turbine starter/generator unit having therein an electrical machine capable of being selected to be alternatively a motor and an electrical power generator and having a coupling shaft extending therefrom to be engaged with the air compressor in the gas turbine engine and further having an interconnection conductor for electrical energization. An internal combustion engine provided as an intermittent combustion engine in the aircraft has an air intake coupled through an air transfer duct connected to the air compressor to allow the transfer of compressed air thereto, and has in connection therewith a supply starter/generator unit with a coupling shaft extending therefrom to be engaged with the intermittent combustion engine power shaft. An interconnection conductor therein for electrical energization is electrically interconnected with the turbine starter/generator unit interconnection conductor.
摘要翻译：一种用于在飞行器中推进和产生电力的发电系统，其使用联接到涡轮启动器/发电机单元的燃气涡轮发动机，其中具有能够被选择为电动机和发电机的电机，并具有连接轴，其从其延伸以与燃气涡轮发动机中的空气压缩机接合，并且还具有用于电通电的互连导体。在飞行器中作为间歇式内燃机设置的内燃机具有通过连接到空气压缩机的空气输送管道联接的进气口，以允许将压缩空气传送到其上，并且与其连接，具有一个供应起动器/发电机单元连接轴从其延伸以与间歇式内燃机动力轴接合。其中用于电通电的互连导体与涡轮起动器/发电机单元互连导体电互连。

88. 发明申请

US20080277944A1 Aircraft combination engines complemental connection and operation 有权
标题翻译：飞机组合引擎互补连接和运行
公开(公告)号：US20080277944A1
公开(公告)日：2008-11-13
申请号：US11801266
申请日：2007-05-09
申请人： Frederick M. Schwarz , Andrew P. Berryann , Brian M. Fentress
发明人： Frederick M. Schwarz , Andrew P. Berryann , Brian M. Fentress
IPC分类号： F02D25/00
CPC分类号： F02C7/275 , F02C5/06 , F02C7/268 , F02C7/32 , F05D2220/50
摘要： A power generation system for propelling, and generating electrical power in, an aircraft, using a gas turbine engine coupled to a turbine starter/generator unit having therein an electrical machine capable of being selected to be alternatively a motor and an electrical power generator and having a coupling shaft extending therefrom to be engaged with the air compressor in the gas turbine engine and further having an interconnection conductor for electrical energization. An internal combustion engine provided as an intermittent combustion engine in the aircraft has an air intake coupled through an air transfer duct connected to the air compressor to allow the transfer of compressed air thereto, and has in connection therewith a supply starter/generator unit with a coupling shaft extending therefrom to be engaged with the intermittent combustion engine power shaft. An interconnection conductor therein for electrical energization is electrically interconnected with the turbine starter/generator unit interconnection conductor.
摘要翻译：一种用于在飞行器中推进和产生电力的发电系统，其使用联接到涡轮启动器/发电机单元的燃气涡轮发动机，其中具有能够被选择为电动机和发电机的电机，并具有连接轴，其从其延伸以与燃气涡轮发动机中的空气压缩机接合，并且还具有用于电通电的互连导体。在飞行器中作为间歇式内燃机设置的内燃机具有通过连接到空气压缩机的空气输送管道联接的进气口，以允许将压缩空气传送到其上，并且与其连接，具有一个供应起动器/发电机单元连接轴从其延伸以与间歇式内燃机动力轴接合。其中用于电通电的互连导体与涡轮起动器/发电机单元互连导体电互连。

89. 发明申请

US20080053101A1 Aircraft thermal management system with reduced exhaust re-ingestion 有权
标题翻译：飞机热管理系统减少排气再摄入
公开(公告)号：US20080053101A1
公开(公告)日：2008-03-06
申请号：US11515020
申请日：2006-09-01
申请人： Frederick M. Schwarz
发明人： Frederick M. Schwarz
IPC分类号： F02C1/00
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/0273 , F02C7/055
摘要： A thermal management system includes a cooling duct system that locates a ram air intake and an exhaust through a first aircraft surface above a second aircraft surface which locates a fan intake. During ground operations, an anti-re-ingestion door is open and a ram air door is closed such that the fan system may draw relatively cooler air from below the aircraft and exhaust the heated air above the aircraft to minimize re-ingestion of the heated exhaust. During flight operations, the anti-re-ingestion door is closed and the ram air door is open such that ram airflow communicates through the fan system prior to communication through the heat exchanger. Both the anti-re-ingestion door and the ram air door may also be operated in flight.
摘要翻译：热管理系统包括冷却管道系统，该冷却管道系统通过定位风扇进气口的第二飞行器表面上方的第一飞机表面定位冲压进气口和排气口。在地面操作期间，防反射门打开，并且压头空气门被关闭，使得风扇系统可以从飞行器下方抽取相对较冷的空气并排出飞机上方的被加热的空气，以最小化加热的排气。在飞行操作期间，防止再吸入门关闭，并且冲压气门打开，使得冲压气流在通过热交换器通信之前通过风扇系统连通。抗再摄入门和冲压空气门也可以在飞行中操作。

90. 发明授权

US5157914A Modulated gas turbine cooling air 失效
标题翻译：调制气体涡轮冷却空气
公开(公告)号：US5157914A
公开(公告)日：1992-10-27
申请号：US634905
申请日：1990-12-27
申请人： Frederick M. Schwarz , David J. Candelori , Richard D. Brooke
发明人： Frederick M. Schwarz , David J. Candelori , Richard D. Brooke
IPC分类号： F01D9/02 , F01D5/08 , F01D11/00 , F01D11/02 , F01D11/06 , F01D17/08 , F02C7/18 , F02C7/28
CPC分类号： F01D17/085 , F01D11/001 , F01D5/081 , Y02T50/676
摘要： Cooling air to the 1-2 turbine stage seal is supplied in parallel with air to the second vane surface from a plenum. A modulatable valve in the supply line to the plenum regulates air flow in response to a sensed temperature in the 1-2 seal area. A thermocouple is located in a bypass around a portion of the seal, being radially installed through a hollow vane and an opening in the seal shroud.

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