专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20100008760A1 GAS TURBINE ENGINE ASSEMBLIES WITH RECIRCULATED HOT GAS INGESTION 有权
标题翻译：燃气涡轮发动机组件与循环热气体吸收
公开(公告)号：US20100008760A1
公开(公告)日：2010-01-14
申请号：US12171000
申请日：2008-07-10
申请人： Mark C. Morris , Jeff Howe , Greg Heitland , Jason Smoke
发明人： Mark C. Morris , Jeff Howe , Greg Heitland , Jason Smoke
IPC分类号： F01D1/02
CPC分类号： F01D11/001 , F01D5/143 , F01D5/145 , F01D11/02 , F01D11/04 , Y02T50/673
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 configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.
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流动路径的环形管道壁，所述主流热气体流动路径被配置为接收主流热气流。组件还包括定子组件，该定子组件包括延伸到主流热气流路径中的定子叶片和在定子组件下游的涡轮转子组件，该涡轮转子组件包括涡轮盘和从涡轮盘延伸到主流热气流中的涡轮叶片路径。定子组件和涡轮机组件限定涡轮机盘腔，并且涡轮机盘腔包括再循环空腔，其被配置成将从主流热气流路径吸入的气体再循环回主流热气流路径。

2. 发明授权

US08262342B2 Gas turbine engine assemblies with recirculated hot gas ingestion 有权
标题翻译：具有再循环热气体摄入的燃气涡轮发动机组件
公开(公告)号：US08262342B2
公开(公告)日：2012-09-11
申请号：US12171000
申请日：2008-07-10
申请人： Mark C. Morris , Jeff Howe , Greg Heitland , Jason Smoke
发明人： Mark C. Morris , Jeff Howe , Greg Heitland , Jason Smoke
IPC分类号： F01D5/14
CPC分类号： F01D11/001 , F01D5/143 , F01D5/145 , F01D11/02 , F01D11/04 , Y02T50/673
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 configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.
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流动路径的环形管道壁，所述主流热气体流动路径被配置为接收主流热气流。组件还包括定子组件，该定子组件包括延伸到主流热气流路径中的定子叶片和在定子组件下游的涡轮转子组件，该涡轮转子组件包括涡轮盘和从涡轮盘延伸到主流热气流中的涡轮叶片路径。定子组件和涡轮机组件限定涡轮机盘腔，并且涡轮机盘腔包括再循环空腔，其被配置成将从主流热气流路径吸入的气体再循环回主流热气流路径。

3. 发明授权

US08167557B2 Gas turbine engine assemblies with vortex suppression and cooling film replenishment 有权
标题翻译：具有涡流抑制和冷却膜补充的燃气涡轮发动机组件
公开(公告)号：US08167557B2
公开(公告)日：2012-05-01
申请号：US12187791
申请日：2008-08-07
申请人： Tom Elliott , Greg Heitland , Jeff Howe , Mark C. Morris
发明人： Tom Elliott , Greg Heitland , Jeff Howe , Mark C. Morris
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2240/127 , F05D2240/81 , F05D2260/2212 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembly and comprising a turbine platform and a turbine rotor blade extending from the turbine platform into the mainstream combustion gases flow path. The turbine rotor blade includes a pressure side and a suction side opposing the pressure side that extend from a leading edge to a trailing edge. The combustion gases form horseshoe vortices at a formation area adjacent the leading edge of the turbine rotor blade, and the turbine rotor assembly further includes a first set of holes in the turbine platform for directing first jets into the formation area of the horseshoe vortices.
摘要翻译：燃气涡轮发动机组件具有流过气体流路的燃烧气体。燃气涡轮发动机组件包括定子组件，该定子组件包括延伸到气体流路中的定子叶片; 以及在定子组件下游的涡轮机转子组件，并且包括涡轮机平台和从涡轮机平台延伸到主流燃烧气体流动路径中的涡轮机转子叶片。涡轮转子叶片包括压力侧和与从前缘延伸到后缘的压力侧相对的吸力侧。燃烧气体在与涡轮机转子叶片的前缘相邻的形成区域形成马蹄形旋涡，并且涡轮机转子组件还包括涡轮机平台中的第一组孔，用于将第一射流引导到马蹄形旋涡的形成区域中。

4. 发明申请

US20100034663A1 GAS TURBINE ENGINE ASSEMBLIES WITH VORTEX SUPPRESSION AND COOLING FILM REPLENISHMENT 有权
标题翻译：燃油涡轮发动机组件与VORTEX抑制和冷却膜补偿
公开(公告)号：US20100034663A1
公开(公告)日：2010-02-11
申请号：US12187791
申请日：2008-08-07
申请人： Tom Elliott , Greg Heitland , Jeff Howe , Mark C. Morris
发明人： Tom Elliott , Greg Heitland , Jeff Howe , Mark C. Morris
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2240/127 , F05D2240/81 , F05D2260/2212 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembly and comprising a turbine platform and a turbine rotor blade extending from the turbine platform into the mainstream combustion gases flow path. The turbine rotor blade includes a pressure side and a suction side opposing the pressure side that extend from a leading edge to a trailing edge. The combustion gases form horseshoe vortices at a formation area adjacent the leading edge of the turbine rotor blade, and the turbine rotor assembly further includes a first set of holes in the turbine platform for directing first jets into the formation area of the horseshoe vortices.
摘要翻译：燃气涡轮发动机组件具有流过气体流路的燃烧气体。燃气涡轮发动机组件包括定子组件，该定子组件包括延伸到气体流路中的定子叶片; 以及在定子组件下游的涡轮机转子组件，并且包括涡轮机平台和从涡轮机平台延伸到主流燃烧气体流动路径中的涡轮机转子叶片。涡轮转子叶片包括压力侧和与从前缘延伸到后缘的压力侧相对的吸力侧。燃烧气体在与涡轮机转子叶片的前缘相邻的形成区域形成马蹄形旋涡，并且涡轮机转子组件还包括涡轮机平台中的第一组孔，用于将第一射流引导到马蹄形旋涡的形成区域中。

5. 发明授权

US08147197B2 Turbine blade platform 有权
标题翻译：涡轮叶片平台
公开(公告)号：US08147197B2
公开(公告)日：2012-04-03
申请号：US12401037
申请日：2009-03-10
申请人： Mark C. Morris , Jason Smoke , Jeff Howe , Bob Mitlin
发明人： Mark C. Morris , Jason Smoke , Jeff Howe , Bob Mitlin
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/30 , F05B2240/33 , F05D2240/81 , F05D2250/292 , F05D2260/201 , Y02T50/676 , Y10S416/50
摘要： A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface.
摘要翻译：提供涡轮叶片组件。涡轮机叶片组件包括涡轮机叶片，其包括空腔和支撑涡轮叶片的叶片平台，空腔延伸到叶片平台中。叶片平台包括邻近涡轮机叶片的上表面和下表面，下表面包括第一肋，空腔延伸到第一肋中，第一肋联接到下表面，当其远离涡轮叶片延伸时逐渐变细，并且包括第一端口从空腔延伸到上表面。

6. 发明申请

US20100232975A1 TURBINE BLADE PLATFORM 有权
标题翻译：涡轮叶片平台
公开(公告)号：US20100232975A1
公开(公告)日：2010-09-16
申请号：US12401037
申请日：2009-03-10
申请人： Mark C. Morris , Jason Smoke , Jeff Howe , Bob Mitlin
发明人： Mark C. Morris , Jason Smoke , Jeff Howe , Bob Mitlin
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/30 , F05B2240/33 , F05D2240/81 , F05D2250/292 , F05D2260/201 , Y02T50/676 , Y10S416/50
摘要： A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface.
摘要翻译：提供涡轮叶片组件。涡轮机叶片组件包括涡轮机叶片，其包括空腔和支撑涡轮叶片的叶片平台，空腔延伸到叶片平台中。叶片平台包括邻近涡轮机叶片的上表面和下表面，下表面包括第一肋，空腔延伸到第一肋中，第一肋联接到下表面，当其远离涡轮叶片延伸时逐渐变细，并且包括第一端口从空腔延伸到上表面。

7. 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。

8. 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。

9. 发明授权

US08206080B2 Gas turbine engine with improved thermal isolation 失效
标题翻译：具有改善热隔离性能的燃气轮机
公开(公告)号：US08206080B2
公开(公告)日：2012-06-26
申请号：US12138108
申请日：2008-06-12
申请人： Jeff Howe , Mark C. Morris , Khosro Molla Hosseini
发明人： Jeff Howe , Mark C. Morris , Khosro Molla Hosseini
IPC分类号： F01D25/00
CPC分类号： F01D11/001 , F01D5/08 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path. The contoured shroud includes a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction. The end wall terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening.
摘要翻译：燃气涡轮发动机包括壳体，其具有限定用于燃烧气体通过的大致环形且轴向伸长的热气体流路的管道壁。发动机还包括安装在内部发动机腔内的轮廓罩，并且限定热气体再循环袋，用于接收从热气流通道穿过环形空间摄取的热气体，并将所摄取的热气体通过环形空间循环回热气体流路。成型护罩包括从管道壁径向向内延伸的底壁，从底壁沿轴向方向朝向转子延伸的内壁，以及从内侧壁沿径向向外的方向延伸的端壁。端壁终止于靠近环形空间设置的周向延伸的自由边缘。端壁限定开口。

10. 发明申请

US20090317244A1 GAS TURBINE ENGINE WITH IMPROVED THERMAL ISOLATION 失效
标题翻译：具有改进的热隔离的气体涡轮发动机
公开(公告)号：US20090317244A1
公开(公告)日：2009-12-24
申请号：US12138108
申请日：2008-06-12
申请人： Jeff Howe , Mark C. Morris , Khosro Molla Hosseini
发明人： Jeff Howe , Mark C. Morris , Khosro Molla Hosseini
IPC分类号： F02C7/12
CPC分类号： F01D11/001 , F01D5/08 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path. The contoured shroud includes a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction. The end wall terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening.
摘要翻译：燃气涡轮发动机包括壳体，其具有限定用于燃烧气体通过的大致环形且轴向伸长的热气体流路的管道壁。发动机还包括安装在内部发动机腔内的轮廓罩，并且限定热气体再循环袋，用于接收从热气流通道穿过环形空间摄取的热气体，并将所摄取的热气体通过环形空间循环回热气体流路。成型护罩包括从管道壁径向向内延伸的底壁，从底壁沿轴向方向朝向转子延伸的内壁，以及从内侧壁沿径向向外的方向延伸的端壁。端壁终止于靠近环形空间设置的周向延伸的自由边缘。端壁限定开口。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式