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1. 发明授权

US07238002B2 Damper seal system and method 失效
标题翻译：阻尼密封系统和方法
公开(公告)号：US07238002B2
公开(公告)日：2007-07-03
申请号：US11265384
申请日：2005-11-03
申请人： Ronald Ralph Cairo , Kevin Leon Bruce , Thomas Raymond Farrell
发明人： Ronald Ralph Cairo , Kevin Leon Bruce , Thomas Raymond Farrell
IPC分类号： F01D5/20
CPC分类号： F01D25/005 , F01D11/005 , F01D11/08 , F01D25/04 , F05D2240/11 , F05D2260/30 , F05D2300/603
摘要： A damper and seal system for a stage of a turbine that includes inner shrouds disposed circumferentially of a hot gas path through the turbine stage and shroud body(s) for supporting the inner shroud(s). A damper block engages a backside surface of the inner shroud and a damping mechanism is carried by the shroud body and connected to the damper block for applying a load to the damper block and inner shroud through the engagement of the block with the backside surface of the inner shroud, thereby damping vibratory movement of the inner shroud. The seal system includes at least one primary, integral seal and at least one secondary, non-integral seal to limit axial and radial hot gas leakage through the stage.
摘要翻译：一种用于涡轮级的阻尼器和密封系统，其包括设置在通过涡轮级的热气路径周向设置并且用于支撑内护罩的护罩体的内护罩。阻尼器块接合内护罩的后侧表面，并且阻尼机构由护罩主体承载并且连接到阻尼器块，用于通过块与其后侧表面的接合来向阻尼块和内护罩施加负载内护罩，从而阻止内护罩的振动运动。密封系统包括至少一个主要的，整体的密封件和至少一个次要的，非整体的密封件，以限制通过该台阶段的轴向和径向的热气体泄漏。

2. 发明申请

US20090202344A1 ROTATING ASSEMBLY FOR A TURBOMACHINE 审中-公开
标题翻译：旋转组件用于涡轮机
公开(公告)号：US20090202344A1
公开(公告)日：2009-08-13
申请号：US12030317
申请日：2008-02-13
申请人： Kevin Leon Bruce , Ronald Ralph Cairo , Richard Gordon Rollings
发明人： Kevin Leon Bruce , Ronald Ralph Cairo , Richard Gordon Rollings
IPC分类号： F01D5/02
CPC分类号： F01D5/225
摘要： A rotating assembly for a turbomachine includes a plurality of rotating members that extend radially outward from a central hub. Each of the plurality of rotating members includes a base portion detachably mounted to the central hub, a tip portion, a mid-span portion that extends between the base portion and the tip portion, and a shroud portion positioned at one of the tip portion and the mid-span portion. The shroud portion includes a pressure side and a suction side. At least one hard face interface member is secured to at least one of the suction side and the pressure side of the shroud portion. The at least one hard face interface member is both mechanically interlocked with, and metallurgically bonded to, the shroud portion.
摘要翻译：用于涡轮机的旋转组件包括从中心毂径向向外延伸的多个旋转构件。所述多个旋转构件中的每一个包括可拆卸地安装到所述中心毂的基部，尖端部，在所述基部和所述尖端部之间延伸的中跨部，以及位于所述尖端部和中跨部分。护罩部分包括压力侧和吸力侧。至少一个硬面接口构件固定到护罩部分的吸力侧和压力侧中的至少一个。所述至少一个硬面接口构件与所述护罩部分机械地互锁并与其冶金结合。

3. 发明授权

US07556475B2 Methods and apparatus for assembling turbine engines 有权
标题翻译：涡轮发动机组装方法及装置
公开(公告)号：US07556475B2
公开(公告)日：2009-07-07
申请号：US11443723
申请日：2006-05-31
申请人： Herbert Chidsey Roberts, III , Kevin Leon Bruce , Gerald Kent Blow , Ronald Ralph Cairo
发明人： Herbert Chidsey Roberts, III , Kevin Leon Bruce , Gerald Kent Blow , Ronald Ralph Cairo
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F05D2230/64 , F05D2240/11 , Y10T29/4932
摘要： A method facilitates the assembly of a turbine engine. The method includes providing a shroud support block having a forward end and an aft end, coupling a forward end of a shroud to the shroud support block using a forward fastener, and coupling an aft end of the shroud to the shroud support block using an aft fastener. The method also includes installing a locking pin through the aft fastener to retain the aft fastener, and staking the locking pin in the shroud support block, such that the locking pin is securely coupled to the shroud support block.
摘要翻译：一种方法有助于涡轮发动机的组装。该方法包括提供具有前端和后端的护罩支撑块，使用前向紧固件将护罩的前端连接到护罩支撑块，并且使用后部将护罩的后端连接到护罩支撑块紧固件。该方法还包括通过后部紧固件安装锁定销以保持后部紧固件，并将锁定销钉固定在护罩支撑块中，使得锁定销牢固地联接到护罩支撑块。

4. 发明授权

US06942203B2 Spring mass damper system for turbine shrouds 有权
标题翻译：涡轮罩的弹簧质量阻尼器系统
公开(公告)号：US06942203B2
公开(公告)日：2005-09-13
申请号：US10700251
申请日：2003-11-04
申请人： Mark Stewart Schroder , Ronald Ralph Cairo , Christopher Grace , Todd Garrett Wetzel , Kevin Leon Bruce , Andrew William Miller , Ronald Phillip Nimmer
发明人： Mark Stewart Schroder , Ronald Ralph Cairo , Christopher Grace , Todd Garrett Wetzel , Kevin Leon Bruce , Andrew William Miller , Ronald Phillip Nimmer
IPC分类号： F01D11/08 , F01D9/04 , F01D25/04 , F01D25/24 , F02C7/18 , F02C7/24 , F02C7/28 , F16F1/18
CPC分类号： F01D25/005 , F01D9/04 , F01D11/08 , F01D25/04 , F01D25/246
摘要： The damper system includes a ceramic composite shroud in part defining the hot gas path of a turbine and a spring-biased piston and damper block which bears against the backside surface of the shroud to tune the vibratory response of the shroud relative to pressure pulses of the hot gas path in a manner to avoid near or resonant frequency response. The damper block has projections specifically located to bear against the shroud to dampen the frequency response of the shroud and provide a thermal insulating layer between the shroud and the damper block.
摘要翻译：阻尼器系统包括部分限定涡轮机的热气体路径的陶瓷复合护罩，以及弹簧偏置的活塞和阻尼器块，其抵靠护罩的后侧表面以调节护罩相对于压力脉冲的压力脉冲的振动响应热气路以避免接近或谐振频率响应的方式。阻尼器块具有突出部分，该突出部具体地定位成抵靠护罩，以抑制护罩的频率响应，并且在护罩和阻尼器块之间提供隔热层。

5. 发明申请

US20130202439A1 ROTATING ASSEMBLY FOR A TURBINE ASSEMBLY 审中-公开
标题翻译：旋转总成用于涡轮组件
公开(公告)号：US20130202439A1
公开(公告)日：2013-08-08
申请号：US13368931
申请日：2012-02-08
申请人： Kevin Leon Bruce , Ronald Ralph Cairo , Matthew Robert Piersall , Richard Gordon Rollings
发明人： Kevin Leon Bruce , Ronald Ralph Cairo , Matthew Robert Piersall , Richard Gordon Rollings
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F05D2230/22 , F05D2250/23 , F05D2250/282 , F05D2250/283 , F05D2250/294 , F05D2250/75
摘要： A rotating assembly for a turbine assembly includes an airfoil extending radially outward from, and rotatable about, an axial centerline. Also included is a tip shroud integrally connected proximate a radially outer tip of the airfoil. Further included is a substrate operably coupled to the tip shroud. Yet further included is at least one hard face interface member secured to the substrate.
摘要翻译：用于涡轮组件的旋转组件包括从轴向中心线径向向外延伸并且可绕其旋转的翼型件。还包括一个靠近翼型件的径向外部末端一体连接的尖端罩。还包括可操作地联接到尖端护罩的衬底。还包括至少一个固定到基底的硬面接口构件。

6. 发明授权

US08047773B2 Gas turbine shroud support apparatus 有权
标题翻译：燃气轮机护罩支撑装置
公开(公告)号：US08047773B2
公开(公告)日：2011-11-01
申请号：US11844046
申请日：2007-08-23
申请人： Kevin Leon Bruce , Ronald Ralph Cairo , Ronald Phillip Nimmer , Curtis Alan Johnson , Gregory Scot Corman , Herbert Chidsey Roberts, III
发明人： Kevin Leon Bruce , Ronald Ralph Cairo , Ronald Phillip Nimmer , Curtis Alan Johnson , Gregory Scot Corman , Herbert Chidsey Roberts, III
IPC分类号： F01D11/12
CPC分类号： F01D25/04 , F01D25/246 , F05D2250/41 , F05D2260/96
摘要： A support apparatus for a gas turbine shroud is disclosed. The apparatus includes an outer shroud block having a coupling connectable to a casing of the gas turbine and a shroud component having a forward flange and an aft flange. The shroud component is attached to the outer shroud block via the forward flange and the aft flange. The apparatus further includes a damper disposed between the outer shroud block and the shroud component and a biasing element disposed within the outer shroud block. A translational degree of freedom between the damper and the outer shroud block defines a direction of motion of the damper. The biasing element is in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper.
摘要翻译：公开了一种用于燃气轮机罩的支撑装置。该装置包括具有可连接到燃气涡轮机壳体的联接件和具有前凸缘和后凸缘的护罩部件的外护罩块。护罩部件经由前凸缘和后凸缘附接到外护罩块。该装置还包括设置在外护罩块和护罩部件之间的阻尼器和设置在外护罩块内的偏置元件。阻尼器和外护罩块之间的平移自由度限定了阻尼器的运动方向。偏压元件经由阻尼器在外护罩块和护罩部件之间可操作地连接，偏压元件的偏压力沿阻尼器的运动方向指向。

7. 发明申请

US20090053050A1 GAS TURBINE SHROUD SUPPORT APPARATUS 有权
标题翻译：气体涡轮支撑装置
公开(公告)号：US20090053050A1
公开(公告)日：2009-02-26
申请号：US11844046
申请日：2007-08-23
申请人： Kevin Leon Bruce , Ronald Ralph Cairo , Ronald Phillip Nimmer , Curtis Alan Johnson , Gregory Scot Corman , Herbert Chidsey Roberts, III
发明人： Kevin Leon Bruce , Ronald Ralph Cairo , Ronald Phillip Nimmer , Curtis Alan Johnson , Gregory Scot Corman , Herbert Chidsey Roberts, III
IPC分类号： F01D25/28
CPC分类号： F01D25/04 , F01D25/246 , F05D2250/41 , F05D2260/96
摘要： A support apparatus for a gas turbine shroud is disclosed. The apparatus includes an outer shroud block having a coupling connectable to a casing of the gas turbine and a shroud component having a forward flange and an aft flange. The shroud component is attached to the outer shroud block via the forward flange and the aft flange. The apparatus further includes a damper disposed between the outer shroud block and the shroud component and a biasing element disposed within the outer shroud block. A translational degree of freedom between the damper and the outer shroud block defines a direction of motion of the damper. The biasing element is in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper.
摘要翻译：公开了一种用于燃气轮机罩的支撑装置。该装置包括具有可连接到燃气涡轮机壳体的联接件和具有前凸缘和后凸缘的护罩部件的外护罩块。护罩部件经由前凸缘和后凸缘附接到外护罩块。该装置还包括设置在外护罩块和护罩部件之间的阻尼器和设置在外护罩块内的偏置元件。阻尼器和外护罩块之间的平移自由度限定了阻尼器的运动方向。偏压元件经由阻尼器在外护罩块和护罩部件之间可操作地连接，偏压元件的偏压力沿阻尼器的运动方向指向。

8. 发明申请

US20070280820A1 Methods and apparatus for assembling turbine engines 有权
标题翻译：涡轮发动机组装方法及装置
公开(公告)号：US20070280820A1
公开(公告)日：2007-12-06
申请号：US11443723
申请日：2006-05-31
申请人： Herbert Chidsey Roberts , Kevin Leon Bruce , Gerald Kent Blow , Ronald Ralph Cairo
发明人： Herbert Chidsey Roberts , Kevin Leon Bruce , Gerald Kent Blow , Ronald Ralph Cairo
IPC分类号： F01D25/26
CPC分类号： F01D11/08 , F05D2230/64 , F05D2240/11 , Y10T29/4932
摘要： A method facilitates the assembly of a turbine engine. The method includes providing a shroud support block having a forward end and an aft end, coupling a forward end of a shroud to the shroud support block using a forward fastener, and coupling an aft end of the shroud to the shroud support block using an aft fastener. The method also includes installing a locking pin through the aft fastener to retain the aft fastener, and staking the locking pin in the shroud support block, such that the locking pin is securely coupled to the shroud support block.
摘要翻译：一种方法有助于涡轮发动机的组装。该方法包括提供具有前端和后端的护罩支撑块，使用前向紧固件将护罩的前端连接到护罩支撑块，并且使用后部将护罩的后端连接到护罩支撑块紧固件。该方法还包括通过后部紧固件安装锁定销以保持后部紧固件，并将锁定销钉固定在护罩支撑块中，使得锁定销牢固地联接到护罩支撑块。

9. 发明授权

US07044709B2 Methods and apparatus for coupling ceramic matrix composite turbine components 有权
标题翻译：用于耦合陶瓷基体复合涡轮机部件的方法和装置
公开(公告)号：US07044709B2
公开(公告)日：2006-05-16
申请号：US10758553
申请日：2004-01-15
申请人： Kevin Leon Bruce , David Vincent Bucci , Ronald Ralph Cairo , David Mitchell
发明人： Kevin Leon Bruce , David Vincent Bucci , Ronald Ralph Cairo , David Mitchell
IPC分类号： F01D11/08
CPC分类号： F01D9/04 , F01D11/08 , F01D25/08 , F05D2240/11 , F05D2260/231 , F05D2260/30
摘要： A method facilitates assembling a stator assembly for a turbine engine. The method comprises positioning a shroud fabricated from a ceramic matrix composite material adjacent a metallic stator block, and coupling the shroud to the stator block using a coupling arrangement such that a predetermined radial clearance is defined between the shroud and a rotor assembly coupled radially inward thereof.
摘要翻译：一种方法有利于组装用于涡轮发动机的定子组件。该方法包括定位由邻近金属定子块的陶瓷基体复合材料制成的护罩，并且使用联接装置将护罩耦合到定子块，使得在护罩与径向向内耦合的转子组件之间限定预定的径向游隙。

10. 发明授权

US08967957B2 Rotating airfoil component of a turbomachine 有权
标题翻译：涡轮机的旋翼型部件
公开(公告)号：US08967957B2
公开(公告)日：2015-03-03
申请号：US13288100
申请日：2011-11-03
申请人： Gary Michael Itzel , Christopher Michael Penny , Aaron Ezekiel Smith , Kevin Leon Bruce
发明人： Gary Michael Itzel , Christopher Michael Penny , Aaron Ezekiel Smith , Kevin Leon Bruce
IPC分类号： F04D29/08 , F01D11/02 , F01D5/28
CPC分类号： F01D11/02 , F01D5/288 , Y02T50/671
摘要： A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.
摘要翻译：装备有一个或多个天使翼的旋转翼型零件，其阻止热工作流体进入其中安装该部件的涡轮机的内部区域。该部件包括翼型件和用于安装部件以使部件在涡轮机内旋转的特征。天使翼从部件突出以具有面向翼型的第一表面，面对安装特征的相对设置的第二表面以及其间的至少一个侧表面。绝热涂层系统存在于第一表面上以抑制从工作流体传递到天使翼而不是在第二或侧面上的热传递，从而不会妨碍从天使翼的第二和侧面的热传递。

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