公开(公告)号：US08678764B1

公开(公告)日：2014-03-25

申请号：US12606463

申请日：2009-10-27

申请人： Keith D Kimmel

发明人： Keith D Kimmel

IPC分类号： F01D5/14

CPC分类号： F01D5/20 ,  F01D5/147

摘要： A turbine rotor blade with a spar and shell construction, and a tip cap that includes a row of lugs extending from a bottom side that form dovetail grooves that engage with similar shaped lugs and grooves on a tip end of the spar to secure the tip cap to the spar against radial displacement. The lug on the trailing edge end of the tip cap is aligned perpendicular to a chordwise line of the blade in the trailing edge region in order to minimize stress due to the lugs wanting to bend under high centrifugal loads. A two piece tip cap with lugs at different angles will reduce the bending stress even more.

摘要翻译： 具有翼梁和壳体结构的涡轮机转子叶片，以及尖端盖，其包括从底侧延伸的一排凸耳，其形成燕尾槽，其与类似形状的凸耳接合，并在翼梁的尖端上固定顶盖 对抗径向位移。 尖端盖的后缘端部上的凸耳在后缘区域垂直于叶片的弦线对齐，以便最小化由于在高离心载荷下弯曲的凸耳所引起的应力。 具有不同角度的凸耳的两件式顶盖将更多地减少弯曲应力。

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：US07828515B1

公开(公告)日：2010-11-09

申请号：US12468349

申请日：2009-05-19

申请人： Keith D Kimmel

发明人： Keith D Kimmel

IPC分类号： F01D9/06 ,  F01D5/18

CPC分类号： F01D5/189 ,  Y02T50/672 ,  Y02T50/676

摘要： A turbine airfoil, such as a rotor blade or a stator vane, for a gas turbine engine, the airfoil formed as a shell and spar construction with a plurality of hook shaped struts each mounted within channels extending in a spanwise direction of the spar and the shell to allow for relative motion between the spar and shell in the airfoil chordwise direction while also fanning a seal between adjacent cooling channels. The struts provide the seal as well as prevent bulging of the shell from the spar due to the cooling air pressure. The hook struts have a hooked shaped end and a rounded shaped end in order to insert the struts into the spar.

摘要翻译： 用于燃气涡轮发动机的诸如转子叶片或定子叶片的涡轮机翼片，形成为壳体的翼型件和具有多个钩状支撑件的翼梁结构，每个悬挂梁支撑件安装在沿着翼梁的翼展方向延伸的通道内， 壳体，以允许翼型件和翼壳在翼型方向上的相对运动，同时还在相邻的冷却通道之间进行密封。 由于冷却空气压力，支柱提供密封以及防止壳体从翼梁膨胀。 钩支柱具有钩形端和圆形端，以将支柱插入翼梁。

公开(公告)号：US08366398B1

公开(公告)日：2013-02-05

申请号：US12795796

申请日：2010-06-08

申请人： Keith D Kimmel

发明人： Keith D Kimmel

IPC分类号： B64C11/20

CPC分类号： F01D5/147 ,  F05D2230/51 ,  F05D2300/13

摘要： An air cooled turbine blade or vane of a spar and shell construction with the shell made from a high temperature resistant material that must be formed from an EDM process. The shell and the spar both have a number of hooks extending in a spanwise direction and forming a contact surface that is slanted such that a contact force increases as the engaging hooks move away from one another. The slanted contact surfaces on the hooks provides for an better seal and allows for twisting between the shell and the spar while maintaining a tight fit.

摘要翻译： 具有由耐高温材料制成的壳体的翼梁和壳体结构的空气冷却涡轮机叶片或叶片，其必须由EDM工艺形成。 壳体和翼梁都具有沿翼展方向延伸的多个钩，并且形成倾斜的接触表面，使得接合力随着接合钩彼此远离而增加。 钩上的倾斜接触表面提供了更好的密封，并且允许壳体和翼梁之间的扭转同时保持紧密配合。

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：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：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：US07824150B1

公开(公告)日：2010-11-02

申请号：US12467009

申请日：2009-05-15

申请人： Keith D Kimmel ,  Jack W. Wilson, Jr.

发明人： Keith D Kimmel ,  Jack W. Wilson, Jr.

IPC分类号： F01D9/06 ,  F01D5/18

CPC分类号： F01D5/189 ,  F01D5/147 ,  F05D2230/642 ,  F05D2300/13 ,  F05D2300/131 ,  F05D2300/50212 ,  Y02T50/672 ,  Y02T50/676

摘要： A turbine airfoil, such as a rotor blade or a stator vane, for a gas turbine engine, the airfoil formed as a shell and spar construction with a plurality of dog bone struts each mounted within openings formed within the shell and spar to allow for relative motion between the spar and shell in the airfoil chordwise direction while also forming a seal between adjacent cooling channels. The struts provide the seal as well as prevent bulging of the shell from the spar due to the cooling air pressure.

摘要翻译： 用于燃气涡轮发动机的诸如转子叶片或定子叶片的涡轮机翼片，形成为壳体的翼型件和具有多个狗骨架的翼梁结构，每个支架安装在形成在壳体和翼梁内的开口内，以允许相对 叶片和翼壳在翼型方向上的运动，同时在相邻的冷却通道之间形成密封。 由于冷却空气压力，支柱提供密封以及防止壳体从翼梁膨胀。

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。