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1. 发明申请

US20110299972A1 IMPELLER BACKFACE SHROUD FOR USE WITH A GAS TURBINE ENGINE 有权
标题翻译：使用燃气涡轮发动机的叶轮背面SHROUD
公开(公告)号：US20110299972A1
公开(公告)日：2011-12-08
申请号：US12794433
申请日：2010-06-04
申请人： Mark C. Morris , Alexander MirzaMoghadam , Khosro Molla Hosseini , Kin Poon , Jeff Howe , Alan G. Tiltman
发明人： Mark C. Morris , Alexander MirzaMoghadam , Khosro Molla Hosseini , Kin Poon , Jeff Howe , Alan G. Tiltman
IPC分类号： F01D1/00
CPC分类号： F01D3/025
摘要： An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.
摘要翻译：公开了一种用于燃气涡轮发动机的叶轮或轴向级压缩机盘背面罩。背面护罩包括但不限于具有表面的大致漏斗形的主体。基本上漏斗形的主体构造成与叶轮或轴向级压缩机盘基本上同轴地静态地安装到燃气涡轮发动机。当基本上漏斗形的主体与叶轮或轴向级压缩机盘同轴地安装并且与其轴向间隔开时，叶轮或轴向级压缩机盘的表面和背面形成空腔，该空腔将气流部分引导到涡轮机。气流部分具有切向速度，并且背面护罩的表面中的凹槽通常横向于切向速度定向，以至少部分地干扰气流部分，从而影响空腔中的静压力。

2. 发明授权

US08616832B2 Turbine assemblies with impingement cooling 有权
标题翻译：具有冲击冷却的涡轮机组件
公开(公告)号：US08616832B2
公开(公告)日：2013-12-31
申请号：US12627609
申请日：2009-11-30
申请人： Jason Smoke , Bradley Reed Tucker , Bob Mitlin , Dan Crites , Rajiv Rana , Alexander MirzaMoghadam
发明人： Jason Smoke , Bradley Reed Tucker , Bob Mitlin , Dan Crites , Rajiv Rana , Alexander MirzaMoghadam
IPC分类号： F01D5/14
CPC分类号： F01D5/087 , F01D5/187 , F05D2240/81 , F05D2260/201 , Y02T50/676
摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.
摘要翻译：燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气体流动路径的环形管道壁; 具有延伸到主流气流中的定子叶片的定子组件; 以及在定子组件上游的涡轮转子组件，并且与定子组件限定涡轮机空腔。涡轮转子组件包括具有前侧和后侧的转子盘，位于转子盘的周边上的转子平台，转子平台限定了后流动盘旋器，安装在转子平台上的转子叶片延伸到主流气流和安装在转子盘的后侧的后密封板。尾部密封板具有使得后部密封板保护转子盘免受热气体摄取的半径。

3. 发明授权

US08381533B2 Direct transfer axial tangential onboard injector system (TOBI) with self-supporting seal plate 有权
标题翻译：直接传递轴向切向机载喷油器系统（TOBI），带有自支撑密封板
公开(公告)号：US08381533B2
公开(公告)日：2013-02-26
申请号：US12433634
申请日：2009-04-30
申请人： Jason Smoke , Bob Mitlin , Alexander MirzaMoghadam
发明人： Jason Smoke , Bob Mitlin , Alexander MirzaMoghadam
IPC分类号： F02C7/18 , F01D5/00
CPC分类号： F02C7/18 , F01D5/081 , Y02T50/673 , Y02T50/676
摘要： An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air. The self-supporting seal plate comprises a plurality of shaped cooling holes in fluid communication with the flow of cooling air emanating from the TOBI. The rotating disk includes a plurality of turbine blade slots formed therein. The plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to the plurality of turbine blades. The plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment and optimized to minimize radial and hoop stresses.
摘要翻译：一种用于冷却涡轮发动机中的涡轮叶片的装置，包括用于涡轮转子的直接传递轴向切向板载喷射器（TOBI）和设置在涡轮发动机的旋转盘上的自支撑密封板。 TOBI包括散发冷却空气流的多个开口。自支撑密封板包括与从TOBI发出的冷却空气流体流体连通的多个成形冷却孔。旋转盘包括形成在其中的多个涡轮叶片槽。多个冷却孔与多个涡轮叶片槽流体连通，用于引导冷却空气的流动以向多个涡轮机叶片提供冷却。多个开口，多个冷却孔和多个涡轮叶片槽位于轴向对准并且被优化以最小化径向和环向应力。

4. 发明授权

US08801364B2 Impeller backface shroud for use with a gas turbine engine 有权
标题翻译：用于燃气轮机的叶轮背面护罩
公开(公告)号：US08801364B2
公开(公告)日：2014-08-12
申请号：US12794433
申请日：2010-06-04
申请人： Mark C. Morris , Alexander MirzaMoghadam , Khosro Molla Hosseini , Kin Poon , Jeff Howe , Alan G. Tiltman
发明人： Mark C. Morris , Alexander MirzaMoghadam , Khosro Molla Hosseini , Kin Poon , Jeff Howe , Alan G. Tiltman
IPC分类号： F01D3/00
CPC分类号： F01D3/025
摘要： An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.
摘要翻译：公开了一种用于燃气涡轮发动机的叶轮或轴向级压缩机盘背面罩。背面护罩包括但不限于具有表面的大致漏斗形的主体。基本上漏斗形的主体构造成与叶轮或轴向级压缩机盘基本上同轴地静态地安装到燃气涡轮发动机。当基本上漏斗形的主体与叶轮或轴向级压缩机盘同轴地安装并且与其轴向间隔开时，叶轮或轴向级压缩机盘的表面和背面形成空腔，该空腔将气流部分引导到涡轮机。气流部分具有切向速度，并且背面护罩的表面中的凹槽通常横向于切向速度定向，以至少部分地干扰气流部分，从而影响空腔中的静压力。

5. 发明申请

US20110129342A1 TURBINE ASSEMBLIES WITH IMPINGEMENT COOLING 有权
标题翻译：涡轮组件与冲击冷却
公开(公告)号：US20110129342A1
公开(公告)日：2011-06-02
申请号：US12627609
申请日：2009-11-30
申请人： Jason Smoke , Bradley Reed Tucker , Bob Mitlin , Dan Crites , Rajiv Rana , Alexander MirzaMoghadam
发明人： Jason Smoke , Bradley Reed Tucker , Bob Mitlin , Dan Crites , Rajiv Rana , Alexander MirzaMoghadam
IPC分类号： F01D5/08
CPC分类号： F01D5/087 , F01D5/187 , F05D2240/81 , F05D2260/201 , Y02T50/676
摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.
摘要翻译：燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气体流动路径的环形管道壁; 具有延伸到主流气流中的定子叶片的定子组件; 以及在定子组件上游的涡轮转子组件，并且与定子组件限定涡轮机空腔。涡轮转子组件包括具有前侧和后侧的转子盘，位于转子盘的周边上的转子平台，转子平台限定了后流动盘旋器，安装在转子平台上的转子叶片延伸到主流气流和安装在转子盘的后侧的后密封板。尾部密封板具有使得后部密封板保护转子盘免受热气体摄取的半径。

6. 发明申请

US20100275612A1 DIRECT TRANSFER AXIAL TANGENTIAL ONBOARD INJECTOR SYSTEM (TOBI) WITH SELF-SUPPORTING SEAL PLATE 有权
标题翻译：具有自支撑密封板的直接传输轴向凸台式注射器系统（TOBI）
公开(公告)号：US20100275612A1
公开(公告)日：2010-11-04
申请号：US12433634
申请日：2009-04-30
申请人： Jason Smoke , Bob Mitlin , Alexander MirzaMoghadam
发明人： Jason Smoke , Bob Mitlin , Alexander MirzaMoghadam
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F01D5/081 , Y02T50/673 , Y02T50/676
摘要： An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air. The self-supporting seal plate comprises a plurality of shaped cooling holes in fluid communication with the flow of cooling air emanating from the TOBI. The rotating disk includes a plurality of turbine blade slots formed therein. The plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to the plurality of turbine blades. The plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment and optimized to minimize radial and hoop stresses.
摘要翻译：一种用于冷却涡轮发动机中的涡轮叶片的装置，包括用于涡轮转子的直接传递轴向切向板载喷射器（TOBI）和设置在涡轮发动机的旋转盘上的自支撑密封板。 TOBI包括散发冷却空气流的多个开口。自支撑密封板包括与从TOBI发出的冷却空气流体流体连通的多个成形冷却孔。旋转盘包括形成在其中的多个涡轮叶片槽。多个冷却孔与多个涡轮叶片槽流体连通，用于引导冷却空气的流动以向多个涡轮机叶片提供冷却。多个开口，多个冷却孔和多个涡轮叶片槽位于轴向对准并且被优化以最小化径向和环向应力。

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