公开(公告)号：US20120045312A1

公开(公告)日：2012-02-23

申请号：US12859904

申请日：2010-08-20

申请人： Keith D. Kimmel ,  Jack Wilson

发明人： Keith D. Kimmel ,  Jack Wilson

IPC分类号： F04D27/02 ,  F01D25/26

CPC分类号： F04D29/541 ,  F01D9/041 ,  F01D11/18 ,  F01D25/246 ,  F01D25/26 ,  F04D29/542

摘要： A vane carrier assembly is provided for supporting vanes within a main engine casing of a gas turbine engine. The vane carrier assembly comprises a plurality of vane support panels positioned adjacent to one another so as to define a vane support assembly. The support panels are assembled such that the support panels expand circumferentially to minimize radial expansion of the vane support assembly during operation of the gas turbine engine. A control ring is coupled to the main engine casing, and the vane support assembly is coupled to the control ring. The control ring may be formed from a material having a coefficient of thermal expansion less than that of the material from which the vane support assembly is formed.

摘要翻译： 提供了一种用于支撑在燃气涡轮发动机的主发动机壳体内的叶片的叶片承载器组件。 叶片承载组件包括彼此相邻定位的多个叶片支撑板，以便限定叶片支撑组件。 支撑板被组装成使得支撑板在圆周方向上扩展以最小化在燃气涡轮发动机操作期间叶片支撑组件的径向膨胀。 控制环联接到主发动机壳体，并且叶片支撑组件联接到控制环。 控制环可以由热膨胀系数小于形成叶片支撑组件的材料的热膨胀系数的材料形成。

公开(公告)号：US09835171B2

公开(公告)日：2017-12-05

申请号：US12859904

申请日：2010-08-20

申请人： Keith D. Kimmel ,  Jack Wilson

发明人： Keith D. Kimmel ,  Jack Wilson

IPC分类号： F01D9/04 ,  F01D25/26 ,  F04D29/54 ,  F01D11/18 ,  F01D25/24

CPC分类号： F04D29/541 ,  F01D9/041 ,  F01D11/18 ,  F01D25/246 ,  F01D25/26 ,  F04D29/542

摘要： A vane carrier assembly is provided for supporting vanes within a main engine casing of a gas turbine engine. The vane carrier assembly comprises a plurality of vane support panels positioned adjacent to one another so as to define a vane support assembly. The support panels are assembled such that the support panels expand circumferentially to minimize radial expansion of the vane support assembly during operation of the gas turbine engine. A control ring is coupled to the main engine casing, and the vane support assembly is coupled to the control ring. The control ring may be formed from a material having a coefficient of thermal expansion less than that of the material from which the vane support assembly is formed.

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。

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。

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。

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。

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。

公开(公告)号：US09394795B1

公开(公告)日：2016-07-19

申请号：US12706241

申请日：2010-02-16

申请人： Keith D. Kimmel ,  William L. Plank

发明人： Keith D. Kimmel ,  William L. Plank

IPC分类号： F01D5/14 ,  F01D5/30

CPC分类号： F01D5/147 ,  F01D5/3007 ,  F05D2240/30 ,  F05D2240/307 ,  F05D2260/36 ,  F05D2300/13 ,  F05D2300/173

摘要： A spar and shell turbine rotor blade with a spar and a tip cap formed as a single piece, the spar includes a bottom end with dovetail or fir tree slots that engage with slots on a top end of a root section, and a platform includes an opening on a top surface for insertion of the spar in which a shell made from an exotic high temperature resistant material is secured between the tip cap and the platform. The spar is tapered to form thinner walls at the tip end to further reduce the weight and therefore a pulling force due to blade rotation. The spar and tip cap piece is made from a NiAL material to further reduce the weight and the pulling force.

摘要翻译： 一种翼梁和壳体涡轮转子叶片，其具有形成为单件的翼梁和尖端盖，所述翼梁包括具有与根部的顶端上的槽接合的燕尾或杉树槽的底端，并且平台包括 在顶表面上开口，用于插入翼片，其中由异种耐高温材料制成的壳体固定在尖端盖和平台之间。 翼梁是锥形的，以在顶端处形成较薄的壁，以进一步减轻重量并因此减小由于叶片旋转引起的拉力。 翼片和尖端帽由NiAL材料制成，以进一步减轻重量和拉力。

公开(公告)号：US08727703B2

公开(公告)日：2014-05-20

申请号：US12876375

申请日：2010-09-07

申请人： Vincent P. Laurello ,  Keith D. Kimmel ,  John Orosa

发明人： Vincent P. Laurello ,  Keith D. Kimmel ,  John Orosa

IPC分类号： F01D25/08

CPC分类号： F01D5/081

摘要： A gas turbine engine includes a diffuser section supplying cooling fluid, a rotatable shaft, shaft cover structure disposed about the rotatable shaft, support structure, and a cooling fluid channel between the shaft cover structure and the support structure. The support structure provides structural support for the shaft cover structure and receives cooling fluid from the diffuser section. One of the diffuser section and the support structure comprises a plurality of apertures through which at least a portion of the cooling fluid passes. The cooling fluid channel is in fluid communication with the apertures in the one of the diffuser section and the support structure for supplying cooling fluid to a blade disc structure located in a turbine section of the engine.

摘要翻译： 燃气涡轮发动机包括供应冷却流体的扩散器部分，可旋转轴，围绕可旋转轴设置的轴盖结构，支撑结构以及轴盖结构和支撑结构之间的冷却流体通道。 支撑结构为轴盖结构提供结构支撑，并从扩散器部分接收冷却流体。 扩散器部分和支撑结构中的一个包括多个孔，冷却流体的至少一部分通过该孔。 冷却流体通道与扩散器部分和支撑结构之一中的孔口流体连通，用于将冷却流体供应到位于发动机涡轮机部分中的叶片结构。

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。