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1. 发明申请

US20110250057A1 RADIAL PRE-SWIRL ASSEMBLY AND COOLING FLUID METERING STRUCTURE FOR A GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机的径向预冷组件和冷却流体测量结构
公开(公告)号：US20110250057A1
公开(公告)日：2011-10-13
申请号：US12859948
申请日：2010-08-20
申请人： Vincent P. Laurello , Keith D. Kimmel , Todd Ebert
发明人： Vincent P. Laurello , Keith D. Kimmel , Todd Ebert
IPC分类号： F01D5/08
CPC分类号： F01D5/081 , F01D5/082 , F02C7/28 , F05D2250/322 , F05D2260/20 , F05D2260/2212 , F05D2260/60
摘要： A gas turbine engine comprises a pre-swirl structure coupled to a shaft cover structure and located radially between a supply of cooling fluid and a flow path. The pre-swirl structure defines a flow passage and includes a plurality of swirl members in the flow passage. A flow direction of cooling fluid passing through the flow passage is altered by the swirl members such that the cooling fluid has a velocity component in a direction tangential to the circumferential direction. The bypass passages provide cooling fluid into a turbine rim cavity associated with a first row vane assembly to prevent hot gas ingestion into the turbine rim cavity from a hot gas flow path associated with a turbine section of the engine.
摘要翻译：燃气涡轮发动机包括联接到轴罩结构并且径向位于冷却流体供应源和流动路径之间的预旋转结构。预旋涡结构限定了流动通道并且在流动通道中包括多个涡流构件。通过流道的冷却流体的流动方向被涡旋部件改变，使得冷却流体在与圆周方向相切的方向上具有速度分量。旁路通道将冷却流体提供到与第一行叶片组件相关联的涡轮机边缘空腔中，以防止热气体从与发动机的涡轮机部分相关联的热气流路径进入涡轮机边缘空腔。

2. 发明授权

US08578720B2 Particle separator in a gas turbine engine 有权
标题翻译：燃气轮机中的颗粒分离器
公开(公告)号：US08578720B2
公开(公告)日：2013-11-12
申请号：US12758071
申请日：2010-04-12
申请人： Todd Ebert , Keith D. Kimmel , Vincent P. Laurello
发明人： Todd Ebert , Keith D. Kimmel , Vincent P. Laurello
IPC分类号： F02C7/18
CPC分类号： F02C7/12 , F01D5/081 , F05D2260/221 , F05D2260/607
摘要： A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, blade disc structure coupled to the shaft and having at least one bore for receiving cooling fluid, and a particle separator. The particle separator includes particle deflecting structure upstream from the blade disc structure, and a particle collection chamber. The particle deflecting structure deflects solid particles from the cooling fluid prior to the cooling fluid entering the at least one bore in the blade disc structure. The particle collection chamber is upstream from the particle deflecting structure and receives the solid particles deflected from the cooling fluid by the particle deflecting structure. The solid particles deflected by the particle deflecting structure flow upstream from the particle deflecting structure to the particle collection chamber.
摘要翻译：燃气涡轮发动机包括冷却流体供应源，可旋转的轴，联接到轴的叶片盘结构，并具有用于接收冷却流体的至少一个孔和颗粒分离器。颗粒分离器包括从叶片盘结构上游的颗粒偏转结构和颗粒收集室。在冷却流体进入叶片盘结构中的至少一个孔之前，颗粒偏转结构使固体颗粒从冷却流体偏转。颗粒收集室位于颗粒偏转结构的上游，并接收由颗粒偏转结构从冷却流体偏转的固体颗粒。由颗粒偏转结构偏转的固体颗粒从颗粒偏转结构的上游流向颗粒收集室。

3. 发明授权

US08677766B2 Radial pre-swirl assembly and cooling fluid metering structure for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的径向预旋组件和冷却流体计量结构
公开(公告)号：US08677766B2
公开(公告)日：2014-03-25
申请号：US12859948
申请日：2010-08-20
申请人： Vincent P. Laurello , Keith D. Kimmel , Todd Ebert
发明人： Vincent P. Laurello , Keith D. Kimmel , Todd Ebert
IPC分类号： F02C7/18 , F01D5/08
CPC分类号： F01D5/081 , F01D5/082 , F02C7/28 , F05D2250/322 , F05D2260/20 , F05D2260/2212 , F05D2260/60
摘要： A gas turbine engine comprises a pre-swirl structure coupled to a shaft cover structure and located radially between a supply of cooling fluid and a flow path. The pre-swirl structure defines a flow passage and includes a plurality of swirl members in the flow passage. A flow direction of cooling fluid passing through the flow passage is altered by the swirl members such that the cooling fluid has a velocity component in a direction tangential to the circumferential direction. The bypass passages provide cooling fluid into a turbine rim cavity associated with a first row vane assembly to prevent hot gas ingestion into the turbine rim cavity from a hot gas flow path associated with a turbine section of the engine.
摘要翻译：燃气涡轮发动机包括联接到轴罩结构并且径向位于冷却流体供应源和流动路径之间的预旋转结构。预旋涡结构限定了流动通道并且在流动通道中包括多个涡流构件。通过流道的冷却流体的流动方向被涡旋部件改变，使得冷却流体在与圆周方向相切的方向上具有速度分量。旁路通道将冷却流体提供到与第一行叶片组件相关联的涡轮机边缘空腔中，以防止热气体从与发动机的涡轮机部分相关联的热气流路径进入涡轮机边缘空腔。

4. 发明申请

US20110247346A1 COOLING FLUID METERING STRUCTURE IN A GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机冷却流量计结构
公开(公告)号：US20110247346A1
公开(公告)日：2011-10-13
申请号：US12758069
申请日：2010-04-12
申请人： Keith D. Kimmel , Vincent P. Laurello , Todd Ebert
发明人： Keith D. Kimmel , Vincent P. Laurello , Todd Ebert
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D5/081 , F05D2260/221
摘要： A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, structure defining at least one bypass passage in fluid communication with the supply of cooling fluid for supplying cooling fluid from the supply of cooling fluid, and metering structure located at an outlet of the at least one bypass passage. The metering structure includes at least one flow passageway extending therethrough at an angle to a central axis of the engine for permitting cooling fluid in the bypass passage to pass into a turbine rim cavity. The cooling fluid flowing out of the flow passageway has a velocity component in a direction tangential to the circumferential direction in the same direction as a rotation direction of the shaft.
摘要翻译：燃气涡轮发动机包括冷却流体供应源，旋转轴结构，其限定至少一个旁路通道，其与冷却流体供应流体连通，用于从冷却流体供应源供应冷却流体;以及计量结构，位于出口处所述至少一个旁通通道。计量结构包括至少一个流动通道，其以与发动机的中心轴线成一定角度的方式延伸，以允许旁路通道中的冷却流体进入涡轮机边缘腔。从流动通道流出的冷却流体在与轴的旋转方向相同的方向上具有与圆周方向相切的方向的速度分量。

5. 发明申请

US20110247345A1 COOLING FLUID PRE-SWIRL ASSEMBLY FOR A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的冷却流体预冷组件
公开(公告)号：US20110247345A1
公开(公告)日：2011-10-13
申请号：US12758065
申请日：2010-04-12
申请人： Vincent P. Laurello , Keith D. Kimmel , Todd Ebert
发明人： Vincent P. Laurello , Keith D. Kimmel , Todd Ebert
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D5/081 , F05D2260/221
摘要： A gas turbine engine includes a pre-swirl structure. Inner and outer wall structures of the pre-swirl structure define a flow passage in which swirl members are located. The swirl members include a leading edge and a circumferentially offset trailing edge. Cooling fluid exits the flow passage with a velocity component in a direction tangential to the circumferential direction, wherein a swirl ratio defined as the velocity component in the direction tangential to the circumferential direction of the cooling fluid to a velocity component of a rotating shaft in the direction tangential to the circumferential direction is greater than one as the cooling fluid exits the flow passage outlet, and the swirl ratio is about one as the cooling fluid enters at least one bore formed in a blade disc structure. An annular cavity extends between the flow passage and the at least one bore formed in the blade disc structure.
摘要翻译：燃气涡轮发动机包括预涡旋结构。预旋结构的内壁和外壁结构限定了流动通道，涡流构件位于该流动通道中。涡旋构件包括前缘和周向偏移的后缘。冷却流体以与圆周方向相切的方向的速度分量离开流道，其中定义为与冷却流体的圆周方向相切的方向上的速度分量相对于旋转轴的速度分量的涡流比随着冷却流体离开流道出口，与圆周方向相切的方向大于一个，当冷却流体进入形成在叶片盘结构中的至少一个孔时，涡流比约为1。环形空腔在流动通道和形成在叶片盘结构中的至少一个孔之间延伸。

6. 发明授权

US08613199B2 Cooling fluid metering structure in a gas turbine engine 有权
标题翻译：燃气涡轮发动机中的冷却液计量结构
公开(公告)号：US08613199B2
公开(公告)日：2013-12-24
申请号：US12758069
申请日：2010-04-12
申请人： Keith D. Kimmel , Vincent P. Laurello , Todd Ebert
发明人： Keith D. Kimmel , Vincent P. Laurello , Todd Ebert
IPC分类号： F02C7/18
CPC分类号： F02C7/12 , F01D5/081 , F05D2260/221
摘要： A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, structure defining at least one bypass passage in fluid communication with the supply of cooling fluid for supplying cooling fluid from the supply of cooling fluid, and metering structure located at an outlet of the at least one bypass passage. The metering structure includes at least one flow passageway extending therethrough at an angle to a central axis of the engine for permitting cooling fluid in the bypass passage to pass into a turbine rim cavity. The cooling fluid flowing out of the flow passageway has a velocity component in a direction tangential to the circumferential direction in the same direction as a rotation direction of the shaft.
摘要翻译：燃气涡轮发动机包括冷却流体供应源，旋转轴结构，其限定至少一个旁路通道，其与冷却流体供应流体连通，用于从冷却流体供应源供应冷却流体;以及计量结构，位于出口处所述至少一个旁通通道。计量结构包括至少一个流动通道，其以与发动机的中心轴线成一定角度的方式延伸，以允许旁路通道中的冷却流体进入涡轮机边缘腔。从流动通道流出的冷却流体在与轴的旋转方向相同的方向上具有与圆周方向相切的方向的速度分量。

7. 发明授权

US08584469B2 Cooling fluid pre-swirl assembly for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的冷却液预旋组件
公开(公告)号：US08584469B2
公开(公告)日：2013-11-19
申请号：US12758065
申请日：2010-04-12
申请人： Vincent P. Laurello , Keith D. Kimmel , Todd Ebert
发明人： Vincent P. Laurello , Keith D. Kimmel , Todd Ebert
IPC分类号： F02C7/18
CPC分类号： F02C7/12 , F01D5/081 , F05D2260/221
摘要： A gas turbine engine includes a pre-swirl structure. Inner and outer wall structures of the pre-swirl structure define a flow passage in which swirl members are located. The swirl members include a leading edge and a circumferentially offset trailing edge. Cooling fluid exits the flow passage with a velocity component in a direction tangential to the circumferential direction, wherein a swirl ratio defined as the velocity component in the direction tangential to the circumferential direction of the cooling fluid to a velocity component of a rotating shaft in the direction tangential to the circumferential direction is greater than one as the cooling fluid exits the flow passage outlet, and the swirl ratio is about one as the cooling fluid enters at least one bore formed in a blade disc structure. An annular cavity extends between the flow passage and the at least one bore formed in the blade disc structure.
摘要翻译：燃气涡轮发动机包括预涡旋结构。预旋结构的内壁和外壁结构限定了流动通道，涡流构件位于该流动通道中。涡旋构件包括前缘和周向偏移的后缘。冷却流体以与圆周方向相切的方向的速度分量离开流道，其中定义为与冷却流体的圆周方向相切的方向上的速度分量相对于旋转轴的速度分量的涡流比随着冷却流体离开流道出口，与圆周方向相切的方向大于一个，当冷却流体进入形成在叶片盘结构中的至少一个孔时，涡流比约为1。环形空腔在流动通道和形成在叶片盘结构中的至少一个孔之间延伸。

8. 发明申请

US20110247347A1 PARTICLE SEPARATOR IN A GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机中的颗粒分离器
公开(公告)号：US20110247347A1
公开(公告)日：2011-10-13
申请号：US12758071
申请日：2010-04-12
申请人： Todd Ebert , Keith D. Kimmel , Vincent P. Laurello
发明人： Todd Ebert , Keith D. Kimmel , Vincent P. Laurello
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D5/081 , F05D2260/221 , F05D2260/607
摘要： A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, blade disc structure coupled to the shaft and having at least one bore for receiving cooling fluid, and a particle separator. The particle separator includes particle deflecting structure upstream from the blade disc structure, and a particle collection chamber. The particle deflecting structure deflects solid particles from the cooling fluid prior to the cooling fluid entering the at least one bore in the blade disc structure. The particle collection chamber is upstream from the particle deflecting structure and receives the solid particles deflected from the cooling fluid by the particle deflecting structure. The solid particles deflected by the particle deflecting structure flow upstream from the particle deflecting structure to the particle collection chamber.
摘要翻译：燃气涡轮发动机包括冷却流体供应源，可旋转的轴，联接到轴的叶片盘结构，并具有用于接收冷却流体的至少一个孔和颗粒分离器。颗粒分离器包括从叶片盘结构上游的颗粒偏转结构和颗粒收集室。在冷却流体进入叶片盘结构中的至少一个孔之前，颗粒偏转结构使固体颗粒从冷却流体偏转。颗粒收集室位于颗粒偏转结构的上游，并接收由颗粒偏转结构从冷却流体偏转的固体颗粒。由颗粒偏转结构偏转的固体颗粒从颗粒偏转结构的上游流向颗粒收集室。

9. 发明授权

US08376697B2 Gas turbine sealing apparatus 有权
标题翻译：燃气轮机密封装置
公开(公告)号：US08376697B2
公开(公告)日：2013-02-19
申请号：US12611241
申请日：2009-11-03
申请人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
发明人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
IPC分类号： F02C7/28
CPC分类号： F01D11/001 , F01D11/005
摘要： A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.
摘要翻译：燃气轮机包括可旋转叶片的前排和后排，在可旋转叶片的前排和后排之间的一排固定叶片，环形中间盘和密封件收纳装置。可旋转刀片的前排和后排被联接到盘/转子组件的相应的第一和第二部分。环形中间盘联接到盘/转子组件，以在燃气轮机的运行期间与盘/转子组件一起旋转。环形中间盘包括联接到盘/转子组件的第一部分的前侧和联接到盘/转子组件的第二部分的后侧。密封壳体装置联接到环形中间盘，以在燃气轮机的操作期间与环形中间盘和盘/转子组件一起旋转。

10. 发明申请

US20100074731A1 Gas Turbine Sealing Apparatus 有权
标题翻译：燃气轮机封口机
公开(公告)号：US20100074731A1
公开(公告)日：2010-03-25
申请号：US12611241
申请日：2009-11-03
申请人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
发明人： David J. Wiebe , Brian J. Wessell , Todd Ebert , Alexander Beeck , George Liang , Walter H. Marussich
IPC分类号： F02C7/28
CPC分类号： F01D11/001 , F01D11/005
摘要： A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.
摘要翻译：燃气轮机包括可旋转叶片的前排和后排，在可旋转叶片的前排和后排之间的一排固定叶片，环形中间盘和密封件收纳装置。可旋转刀片的前排和后排被联接到盘/转子组件的相应的第一和第二部分。环形中间盘联接到盘/转子组件，以在燃气轮机的运行期间与盘/转子组件一起旋转。环形中间盘包括联接到盘/转子组件的第一部分的前侧和联接到盘/转子组件的第二部分的后侧。密封壳体装置联接到环形中间盘，以在燃气轮机的操作期间与环形中间盘和盘/转子组件一起旋转。

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