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1. 发明授权

US09097133B2 Compressor tip clearance management for a gas turbine engine 有权
标题翻译：燃气轮机的压缩机顶端间隙管理
公开(公告)号：US09097133B2
公开(公告)日：2015-08-04
申请号：US13487632
申请日：2012-06-04
申请人： Yuan Dong , Lisa I. Brilliant , Daniel Carminati , Steven J. Sirica
发明人： Yuan Dong , Lisa I. Brilliant , Daniel Carminati , Steven J. Sirica
IPC分类号： F01D11/20 , F01D11/08 , F04D27/00 , F04D29/16 , F04D29/56 , F02C9/20 , F04D27/02
CPC分类号： F01D11/08 , F02C9/20 , F04D27/004 , F04D27/0246 , F04D29/164 , F04D29/563
摘要： A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream from the high pressure compressor. The variable stator vane is connected to an actuator, and a controller is in communication with the actuator. The controller is configured to provide a command to the actuator to move the variable stator vane in response to a high pressure compressor clearance condition. A high pressure compressor rotor speed is altered, and the high pressure compressor clearance condition is changed to a desired clearance.
摘要翻译：压缩机顶端间隙管理系统包括压缩机部分，其具有布置在低压压缩机下游的低压压缩机和高压压缩机。可变定子叶片布置在高压压缩机的上游。可变定子叶片连接到致动器，并且控制器与致动器连通。控制器构造成响应于高压压缩机间隙状况向致动器提供命令以移动可变定子叶片。改变高压压缩机转子速度，将高压压缩机间隙条件改变为期望的间隙。

2. 发明授权

US08511058B2 Convertible gas turbine propulsion system 有权
公开(公告)号：US08511058B2
公开(公告)日：2013-08-20
申请号：US11998291
申请日：2007-11-29
申请人： Rajendra K. Agrawal , Steven J. Sirica , William F. Schneider
发明人： Rajendra K. Agrawal , Steven J. Sirica , William F. Schneider
IPC分类号： F02C6/00 , F02G1/00 , F02G3/00
CPC分类号： F02C6/206 , F02C7/36
摘要： A convertible gas turbine propulsion system operates in multiple output modes. The convertible gas turbine propulsion system comprises a gas generator, a first power turbine, a secondary propulsion system and an exhaust duct. The gas generator is configured to produce exhaust gas. The first power turbine is aligned with the gas generator to receive the exhaust gas. The secondary propulsion system is in series with the gas generator and the first power turbine. The exhaust duct coaxially extends from the first power turbine to the secondary propulsion system. The exhaust duct includes an exhaust port for opening the exhaust duct to ambient air pressure and permitting exhaust gas to bypass the secondary propulsion system. In various embodiments of the invention, the first power turbine is connected to a first rotary propulsion system, and the secondary propulsion system comprises a second power turbine or a nozzle.

3. 发明授权

US08615980B2 Gas turbine engine with noise attenuating variable area fan nozzle 有权
标题翻译：燃气涡轮发动机带有噪音衰减可变面积的风扇喷嘴
公开(公告)号：US08615980B2
公开(公告)日：2013-12-31
申请号：US13271181
申请日：2011-10-11
申请人： Rajendra K. Agrawal , Steven J. Sirica , William F. Schneider
发明人： Rajendra K. Agrawal , Steven J. Sirica , William F. Schneider
IPC分类号： F02C6/00 , F02G1/00 , F02G3/00
CPC分类号： F02C6/206 , F02C7/36
摘要： A rotary-wing aircraft includes a retractable port movable between a closed position and an open position to selectively control flow of combustion gases into a bypass passage to change a power distribution between a rotor system and a secondary propulsion system.
摘要翻译：旋转翼飞行器包括可在关闭位置和打开位置之间移动的可缩回端口，以选择性地控制燃烧气体进入旁路通道以改变转子系统和次推进系统之间的动力分配。

4. 发明授权

US08276362B2 Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method 有权
标题翻译：可变风机入口导叶组件，具有这种组件的涡轮发动机及相应的控制方法
公开(公告)号：US08276362B2
公开(公告)日：2012-10-02
申请号：US13022456
申请日：2011-02-07
申请人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
发明人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
IPC分类号： F02K3/02
CPC分类号： F01D17/162 , F02C3/073 , F02K3/068
摘要： A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.
摘要翻译：涡轮发动机包括多个可变风扇入口导向叶片。在涡轮发动机是顶端涡轮发动机的情况下，即使风扇 - 涡轮转子组件以固定的速率直接联接到轴向压缩机，可变风扇入口导叶允许控制发动机稳定性的能力。风扇入口导向叶片可以从风扇入口导叶的内径致动。

5. 发明申请

US20120167593A1 TAPERED BEARINGS 审中-公开
标题翻译：锥形轴承
公开(公告)号：US20120167593A1
公开(公告)日：2012-07-05
申请号：US13346213
申请日：2012-01-09
申请人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
发明人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
IPC分类号： F02C7/36 , F01D15/12
摘要： A gearbox support assembly for a turbine engine includes an epicyclic gear arrangement and a first tapered bearing and a second tapered bearing spaced apart from the first tapered bearing. The first tapered bearing and the second tapered bearing support the epicyclic gear arrangement.
摘要翻译：用于涡轮发动机的齿轮箱支撑组件包括行星齿轮装置和第一锥形轴承以及与第一锥形轴承间隔开的第二锥形轴承。第一锥形轴承和第二锥形轴承支撑行星齿轮装置。

6. 发明授权

US09003768B2 Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method 有权
标题翻译：可变风机入口导叶组件，具有这种组件的涡轮发动机及相应的控制方法
公开(公告)号：US09003768B2
公开(公告)日：2015-04-14
申请号：US13023032
申请日：2011-02-08
申请人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
发明人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
IPC分类号： F02K3/02 , F01D17/16 , F02C3/073 , F02K3/068
CPC分类号： F01D17/162 , F02C3/073 , F02K3/068
摘要： A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.
摘要翻译：涡轮发动机包括多个可变风扇入口导向叶片。在涡轮发动机是顶端涡轮发动机的情况下，即使风扇 - 涡轮转子组件以固定的速率直接联接到轴向压缩机，可变风扇入口导叶允许控制发动机稳定性的能力。风扇入口导向叶片可以从风扇入口导叶的内径致动。

7. 发明申请

US20130323012A1 COMPRESSOR TIP CLEARANCE MANAGEMENT FOR A GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机压缩机提升间隙管理
公开(公告)号：US20130323012A1
公开(公告)日：2013-12-05
申请号：US13487632
申请日：2012-06-04
申请人： Yuan Dong , Lisa I. Brilliant , Daniel Carminati , Steven J. Sirica
发明人： Yuan Dong , Lisa I. Brilliant , Daniel Carminati , Steven J. Sirica
IPC分类号： F04D29/56
CPC分类号： F01D11/08 , F02C9/20 , F04D27/004 , F04D27/0246 , F04D29/164 , F04D29/563
摘要： A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream from the high pressure compressor. The variable stator vane is connected to an actuator, and a controller is in communication with the actuator. The controller is configured to provide a command to the actuator to move the variable stator vane in response to a high pressure compressor clearance condition. A high pressure compressor rotor speed is altered, and the high pressure compressor clearance condition is changed to a desired clearance.
摘要翻译：压缩机顶端间隙管理系统包括压缩机部分，其具有布置在低压压缩机下游的低压压缩机和高压压缩机。可变定子叶片布置在高压压缩机的上游。可变定子叶片连接到致动器，并且控制器与致动器连通。控制器构造成响应于高压压缩机间隙状况向致动器提供命令以移动可变定子叶片。改变高压压缩机转子速度，将高压压缩机间隙条件改变为期望的间隙。

8. 发明申请

US20130019585A1 VARIABLE FAN INLET GUIDE VANE FOR TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机可变风扇入口导向件
公开(公告)号：US20130019585A1
公开(公告)日：2013-01-24
申请号：US13340909
申请日：2011-12-30
申请人： Brian Merry , Gabriel L. Suciu , James W. Norris , Steven J. Sirica , Frederick M. Schwarz
发明人： Brian Merry , Gabriel L. Suciu , James W. Norris , Steven J. Sirica , Frederick M. Schwarz
IPC分类号： F02K3/04
CPC分类号： F01D17/162 , F02C3/073 , F02C3/08 , F02C3/107 , F02C7/36 , F02C9/20 , F02K3/068 , F05D2270/02 , F05D2270/101 , F05D2270/301 , F05D2270/304 , Y02T50/671
摘要： A turbine engine includes a compressor section, a combustor arranged in fluid-receiving communication with the compressor section, a turbine section arranged in fluid-receiving communication with the combustor and a gearbox assembly coupled to be driven by the turbine section. The gearbox assembly is located at an axial position that is aft of the compressor section.
摘要翻译：涡轮发动机包括压缩机部分，布置成与压缩机部分流体接收连通的燃烧器，与燃烧器配置成与流体接收连通的涡轮部分，以及耦合以由涡轮部分驱动的齿轮箱组件。齿轮箱组件位于在压缩机部分的后部的轴向位置处。

9. 发明申请

US20120121375A1 VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD 审中-公开
标题翻译：可变风扇入口导向风扇组件，具有这种组件的涡轮发动机和相应的控制方法
公开(公告)号：US20120121375A1
公开(公告)日：2012-05-17
申请号：US13023032
申请日：2011-02-08
申请人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
发明人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
IPC分类号： F01D17/14 , F01D17/00
CPC分类号： F01D17/162 , F02C3/073 , F02K3/068
摘要： A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.
摘要翻译：涡轮发动机包括多个可变风扇入口导向叶片。在涡轮发动机是顶端涡轮发动机的情况下，即使风扇 - 涡轮转子组件以固定的速率直接联接到轴向压缩机，可变风扇入口导叶允许控制发动机稳定性的能力。风扇入口导向叶片可以从风扇入口导叶的内径致动。

10. 发明申请

US20090139202A1 Convertible gas turbine propulsion system 有权
标题翻译：可转换燃气轮机推进系统
公开(公告)号：US20090139202A1
公开(公告)日：2009-06-04
申请号：US11998291
申请日：2007-11-29
申请人： Rajendra K. Agrawal , Steven J. Sirica , William F. Schneider
发明人： Rajendra K. Agrawal , Steven J. Sirica , William F. Schneider
IPC分类号： F02K3/04 , F02C3/06
CPC分类号： F02C6/206 , F02C7/36
摘要： A convertible gas turbine propulsion system operates in multiple output modes. The convertible gas turbine propulsion system comprises a gas generator, a first power turbine, a secondary propulsion system and an exhaust duct. The gas generator is configured to produce exhaust gas. The first power turbine is aligned with the gas generator to receive the exhaust gas. The secondary propulsion system is in series with the gas generator and the first power turbine. The exhaust duct coaxially extends from the first power turbine to the secondary propulsion system. The exhaust duct includes an exhaust port for opening the exhaust duct to ambient air pressure and permitting exhaust gas to bypass the secondary propulsion system. In various embodiments of the invention, the first power turbine is connected to a first rotary propulsion system, and the secondary propulsion system comprises a second power turbine or a nozzle.
摘要翻译：可转换燃气轮机推进系统以多种输出模式运行。可转换燃气轮机推进系统包括气体发生器，第一动力涡轮机，次推进系统和排气管道。气体发生器被配置成产生废气。第一动力涡轮机与气体发生器对准以接收废气。二次推进系统与气体发生器和第一动力涡轮机串联。排气管同时从第一动力涡轮机延伸到次推进系统。排气管道包括用于将排气管道打开到环境空气压力并允许废气绕过次级推进系统的排气口。在本发明的各种实施例中，第一动力涡轮机连接到第一旋转推进系统，而次级推进系统包括第二动力涡轮机或喷嘴。

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