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1. 发明授权

US08172506B2 Method and system for cooling engine components 有权
标题翻译：冷却发动机部件的方法和系统
公开(公告)号：US08172506B2
公开(公告)日：2012-05-08
申请号：US12324324
申请日：2008-11-26
申请人： Rafal Piotr Pieczka , Craig William Higgins , Piotr Edward Kobek , Jan Franciszek Sikorski , Edward Donald Michaels
发明人： Rafal Piotr Pieczka , Craig William Higgins , Piotr Edward Kobek , Jan Franciszek Sikorski , Edward Donald Michaels
IPC分类号： F03B11/00 , F01D5/14 , F03D11/00 , F04D31/00
CPC分类号： F01D5/082 , F01D25/12 , F05D2250/14 , F05D2250/232 , F05D2260/14 , F05D2260/941 , Y02T50/676 , Y10T29/49316
摘要： A method and system for a rotatable member of a turbine engine are provided. The rotatable member includes a substantially cylindrical shaft rotatable about a longitudinal axis, and a hub coupled to the cylindrical shaft through a conical shaft portion wherein the conical shaft portion includes a plurality of circumferentially-spaced air passages and wherein at least one of the plurality of air passages includes a non-circular cross section.
摘要翻译：提供了一种用于涡轮发动机的可旋转构件的方法和系统。可旋转构件包括可围绕纵向轴线旋转的基本上圆柱形的轴，以及通过锥形轴部分联接到圆柱形轴的轮毂，其中锥形轴部分包括多个周向间隔开的空气通道，并且其中多个空气通道包括非圆形横截面。

2. 发明申请

US20100129197A1 METHOD AND SYSTEM FOR COOLING ENGINE COMPONENTS 有权
标题翻译：冷却发动机组件的方法和系统
公开(公告)号：US20100129197A1
公开(公告)日：2010-05-27
申请号：US12324324
申请日：2008-11-26
申请人： Rafal Piotr Pieczka , Craig William Higgins , Piotr Edward Kobek , Jan Franciszek Sikorski , Edward Donald Michaels
发明人： Rafal Piotr Pieczka , Craig William Higgins , Piotr Edward Kobek , Jan Franciszek Sikorski , Edward Donald Michaels
IPC分类号： F02C7/18 , B23P15/04
CPC分类号： F01D5/082 , F01D25/12 , F05D2250/14 , F05D2250/232 , F05D2260/14 , F05D2260/941 , Y02T50/676 , Y10T29/49316
摘要： A method and system for a rotatable member of a turbine engine are provided. The rotatable member includes a substantially cylindrical shaft rotatable about a longitudinal axis, and a hub coupled to the cylindrical shaft through a conical shaft portion wherein the conical shaft portion includes a plurality of circumferentially-spaced air passages and wherein at least one of the plurality of air passages includes a non-circular cross section.
摘要翻译：提供了一种用于涡轮发动机的可旋转构件的方法和系统。可旋转构件包括可围绕纵向轴线旋转的基本上圆柱形的轴，以及通过锥形轴部分联接到圆柱形轴的轮毂，其中锥形轴部分包括多个周向间隔开的空气通道，并且其中多个空气通道包括非圆形横截面。

3. 发明授权

US08608436B2 Tapered collet connection of rotor components 有权
标题翻译：转子零件的锥形夹头连接
公开(公告)号：US08608436B2
公开(公告)日：2013-12-17
申请号：US12872376
申请日：2010-08-31
申请人： Daniel Edward Wines , James Hamilton Grooms , Craig William Higgins
发明人： Daniel Edward Wines , James Hamilton Grooms , Craig William Higgins
IPC分类号： F01D5/02 , F01D11/00
CPC分类号： F01D5/3015 , F01D5/066 , F01D11/001 , F01D11/005 , F05D2230/64 , F05D2260/30
摘要： A connection between an annular sleeve on a gas turbine engine first rotor component includes an annular tapered conical slot extending axially inwardly into the sleeve from an annular opening and tapers axially into the sleeve from the opening. An annular rim of a second rotor component is received within the conical slot and includes a rim inner conical surface mating with and contacting a sleeve inner conical surface in part bounding the conical slot. A sleeve cylindrical outer surface in part bounds the conical slot in the sleeve and a rim outer cylindrical surface on the annular rim contacts the sleeve cylindrical outer surface. An annular lip may extend radially inwardly from the sleeve and sleeve inner conical surface at the annular opening to the conical slot. The connection may be used between a first stage disk and an interstage seal.
摘要翻译：燃气涡轮发动机第一转子部件上的环形套筒之间的连接包括从环形开口轴向向内延伸到套筒中的环形锥形锥形槽，并且从开口轴向地锥形地套入套筒。第二转子部件的环形边缘被容纳在锥形槽内，并且包括边缘内圆锥形表面，该边缘内锥形表面与限定锥形槽的部分的套筒内锥形表面配合并接触。套筒圆柱形外表面部分地限制在套筒中的锥形槽，并且环形边缘上的边缘外圆柱形表面接触套筒圆柱形外表面。环形唇缘可以从环形开口处的套筒和套筒内锥形表面径向向内延伸到锥形槽。连接可以在第一级盘和级间密封之间使用。

4. 发明授权

US07578656B2 High pressure turbine disk hub with reduced axial stress and method 有权
标题翻译：具有降低轴向应力和方法的高压涡轮盘毂
公开(公告)号：US07578656B2
公开(公告)日：2009-08-25
申请号：US11306224
申请日：2005-12-20
申请人： Craig William Higgins , Charles Chris England , Joeseph Charles Kulesa , Andrew John Lammas
发明人： Craig William Higgins , Charles Chris England , Joeseph Charles Kulesa , Andrew John Lammas
IPC分类号： F01D5/02
CPC分类号： F01D5/02 , F05D2230/10 , F05D2250/182 , F05D2250/291 , F05D2250/292 , Y02T50/671
摘要： A gas turbine engine disk that includes a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a radially-displaced annular hub surface exposed to high pressure, high temperature discharge gases during engine operation. The radially-displaced annular hub surface acts as an axial free surface mitigating the formation undesirable axial stress in the disk hub.
摘要翻译：一种燃气涡轮发动机盘，包括中心设置的盘毂，其具有在外端终止的一体形成的径向向外延伸的腹板。在发动机运行期间，盘毂具有暴露于高压高温放电气体的径向移位的环形毂表面。径向位移的环形毂表面用作轴向自由表面，减轻了盘毂中形成不期望的轴向应力。

5. 发明授权

US06860722B2 Snap on blade shim 有权
标题翻译：抓住刀片垫片
公开(公告)号：US06860722B2
公开(公告)日：2005-03-01
申请号：US10356238
申请日：2003-01-31
申请人： James Michael Forrester , Emily Anne Clausing , Robert Russell Grant , John Gregory Cargill , Craig William Higgins
发明人： James Michael Forrester , Emily Anne Clausing , Robert Russell Grant , John Gregory Cargill , Craig William Higgins
IPC分类号： F01D5/30
CPC分类号： F01D5/3092 , F05D2250/00
摘要： A gas turbine engine blade root shim includes a dovetail shim portion with a dovetail shape and a longitudinally extending substantially flat base and distal first and second longitudinally spaced apart forward and aft ends. Transversely spaced apart first and second walls extend upwardly from the base which includes at least two longitudinally extending elongated base apertures. Each of the base apertures includes a main region and longitudinally spaced apart rounded end regions. Dog-bone-shaped base apertures or rounded end base apertures having semi-circular rounded end regions may be used. The shim is designed for a blade dovetail root with a root slot formed in a bottom of the dovetail root. The dovetail shim portion with the dovetail shape substantially conforms to at least a portion of a cross-sectional dovetail shape of the dovetail root through the root slot. The base is disposed within the root slot.
摘要翻译：燃气涡轮发动机叶片根垫片包括具有燕尾形状的燕尾垫片部分和纵向延伸的基本上平坦的基部和远端的第一和第二纵向间隔开的前后端部。横向间隔开的第一和第二壁从基部向上延伸，其包括至少两个纵向延伸的细长基部孔。每个基座孔包括主区域和纵向间隔开的圆形端部区域。可以使用具有半圆形圆形端部区域的狗骨形基部孔或圆形端部基部孔。垫片设计用于具有形成在燕尾根底部的根槽的叶片燕尾根。具有燕尾形状的燕尾形垫片部分基本上符合燕尾根的横截面燕尾形状的至少一部分，通过根槽。基部设置在根槽内。

6. 发明申请

US20120051917A1 TAPERED COLLET CONNECTION OF ROTOR COMPONENTS 有权
标题翻译：转子组件的锥形接头连接
公开(公告)号：US20120051917A1
公开(公告)日：2012-03-01
申请号：US12872376
申请日：2010-08-31
申请人： Daniel Edward Wines , James Hamilton Grooms , Craig William Higgins
发明人： Daniel Edward Wines , James Hamilton Grooms , Craig William Higgins
IPC分类号： F01D5/22 , F01D5/30
CPC分类号： F01D5/3015 , F01D5/066 , F01D11/001 , F01D11/005 , F05D2230/64 , F05D2260/30
摘要： A connection between an annular sleeve on a gas turbine engine first rotor component includes an annular tapered conical slot extending axially inwardly into the sleeve from an annular opening and tapers axially into the sleeve from the opening. An annular rim of a second rotor component is received within the conical slot and includes a rim inner conical surface mating with and contacting a sleeve inner conical surface in part bounding the conical slot. A sleeve cylindrical outer surface in part bounds the conical slot in the sleeve and a rim outer cylindrical surface on the annular rim contacts the sleeve cylindrical outer surface. An annular lip may extend radially inwardly from the sleeve and sleeve inner conical surface at the annular opening to the conical slot. The connection may be used between a first stage disk and an interstage seal.
摘要翻译：燃气涡轮发动机第一转子部件上的环形套筒之间的连接包括从环形开口轴向向内延伸到套筒中的环形锥形锥形槽，并且从开口轴向地锥形地套入套筒。第二转子部件的环形边缘被容纳在锥形槽内，并且包括边缘内圆锥形表面，该边缘内锥形表面与限定锥形槽的部分的套筒内锥形表面配合并接触。套筒圆柱形外表面部分地限制在套筒中的锥形槽，并且环形边缘上的边缘外圆柱形表面接触套筒圆柱形外表面。环形唇缘可以从环形开口处的套筒和套筒内锥形表面径向向内延伸到锥形槽。连接可以在第一级盘和级间密封之间使用。

7. 发明授权

US07331763B2 Turbine disk 有权
标题翻译：涡轮盘
公开(公告)号：US07331763B2
公开(公告)日：2008-02-19
申请号：US11306226
申请日：2005-12-20
申请人： Craig William Higgins , Matthew Lee Krumanaker
发明人： Craig William Higgins , Matthew Lee Krumanaker
IPC分类号： F01D25/08
CPC分类号： F01D5/08 , F01D11/02 , F05D2250/71 , F05D2260/94 , F05D2260/941 , F05D2300/50211 , Y02T50/671 , Y02T50/676
摘要： A gas turbine section of a gas turbine engine, including a first stage turbine disk, a forward outer seal carried on the turbine disk and a forward shaft cooperating with the first stage turbine disk for transmitting torque generated by the turbine section to a compressor section of the engine. The forward shaft intersects the first stage turbine disk at a non-perpendicular angle in the area of the disk hub for directing sufficient hot air against the disk hub to balance the thermal response rate of the disk hub to the thermal expansion rate of the forward outer seal.
摘要翻译：一种燃气涡轮发动机的燃气轮机部分，包括第一级涡轮盘，承载在涡轮盘上的前外密封件和与第一级涡轮盘协作的前轴，用于将由涡轮部分产生的扭矩传递到涡轮机部分的压缩机部分引擎。前轴在盘毂区域以非垂直的角度与第一级涡轮盘相交，用于将足够的热空气引导到盘毂上，以平衡盘毂的热响应速率与前外侧的热膨胀率密封。

8. 发明授权

US07458774B2 High pressure turbine disk hub with curved hub surface and method 有权
标题翻译：具有弯曲轮毂表面和方法的高压涡轮盘毂
公开(公告)号：US07458774B2
公开(公告)日：2008-12-02
申请号：US11306227
申请日：2005-12-20
申请人： Richard William Albrecht, Jr. , Craig William Higgins
发明人： Richard William Albrecht, Jr. , Craig William Higgins
IPC分类号： F01D5/02
CPC分类号： F01D5/00 , F01D5/02 , F01D5/06 , F01D5/08 , F01D5/30 , Y02T50/671 , Y02T50/676
摘要： A first stage turbine disk section for a gas turbine engine, including a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a convex, curved hub surface exposed to high pressure, high temperature compressor bleed and discharge gases during engine operation, and the convex, curved hub surface acts to reduce the axial constraint at the location of peak axial stress, thereby mitigating the formation of undesirable axial stress in the disk hub and allows separation of the peak axial and hoop stresses, thereby reducing the magnitude of the peak hub surface effective stress.
摘要翻译：用于燃气涡轮发动机的第一级涡轮盘部分，包括中心设置的盘毂，其具有终止于外端的一体形成的径向向外延伸的纤维网。盘毂具有在发动机运行期间暴露于高压，高温压缩机排气和放电气体的凸形弯曲毂表面，并且凸形弯曲毂表面用于减小在轴向应力峰值位置处的轴向约束，从而减轻在盘毂中形成不期望的轴向应力并允许峰值轴向和环向应力的分离，从而减小峰值毂表面有效应力的大小。

9. 发明授权

US06735281B2 Rotating anode for X-ray tube using interference fit 有权
标题翻译：使用干涉配合旋转X射线管阳极
公开(公告)号：US06735281B2
公开(公告)日：2004-05-11
申请号：US10063850
申请日：2002-05-17
申请人： Craig William Higgins , Gregory Alan Steinlage
发明人： Craig William Higgins , Gregory Alan Steinlage
IPC分类号： H01J3510
CPC分类号： H01J35/26
摘要： A method for assembling a rotating X-ray tube, the X-ray tube having a cathode for emitting electrons, and a rotor and a bearing assembly for facilitating rotation of an anode. The method includes using an interference fit assembly between the bearing assembly and the rotor to provide a joint having balance retention. The using interference fit assembly further includes selecting a rotor hub of the rotor having a coefficient of thermal expansion which results in a composite coefficient of thermal expansion for the rotor assembly which closely matches that of a shaft of the bearing assembly. An interference fit joint between a shaft extending from a bearing assembly and a rotor hub is also disclosed, wherein the joint is completed without using any mechanical fasteners or metallurgical bonding, yet can carry all of the operational loads placed on the joint.
摘要翻译：一种用于组装旋转X射线管的方法，具有用于发射电子的阴极的X射线管以及用于促进阳极旋转的转子和轴承组件。该方法包括在轴承组件和转子之间使用过盈配合组件以提供具有平衡保持力的接头。使用干涉配合组件还包括选择具有热膨胀系数的转子的转子轮毂，其导致转子组件的复合热膨胀系数与轴承组件的轴的热膨胀系数相匹配。还公开了从轴承组件和转子轮毂延伸的轴之间的过盈配合接头，其中接头在不使用任何机械紧固件或冶金接合的情况下完成，但是可以承载放置在接头上的所有操作负载。

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