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1. 发明申请

US20090104028A1 METHOD AND APPARATUS FOR DISTRIBUTING FLUID INTO A TURBOMACHINE 审中-公开
标题翻译：将流体分配到涡轮机中的方法和装置
公开(公告)号：US20090104028A1
公开(公告)日：2009-04-23
申请号：US12119541
申请日：2008-05-13
申请人： Richard Robert Trewin , Jason Paul Mortzheim , Edip Sevincer , Kevin Richard Kirtley , Roointon Erach Pavri , Xiaoyue Liu
发明人： Richard Robert Trewin , Jason Paul Mortzheim , Edip Sevincer , Kevin Richard Kirtley , Roointon Erach Pavri , Xiaoyue Liu
IPC分类号： F01D5/08 , F01D5/14
CPC分类号： F01D25/14 , F01D9/065 , F02C7/1435 , F04D29/5846
摘要： An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distribute a fluid in a gas flow path inside a turbomachine, the method comprising: machining a casing groove along an inner surface of a casing; machining at least one port into the casing that is in fluid communication with the casing groove; machining an internal cavity in at least one stator blade that is in fluid communication with the casing groove; machining at least one orifice, that is in fluid communication with the internal cavity, on an orifice surface of the stator blade; and coupling a fluid supply to the at least one port.
摘要翻译：一种用于在涡轮机内部的气体流路中分配流体的装置，包括：用于将流体引入气体流路的装置; 并且其中所述装置位于所述气体流动路径内。一种用于安装将流体分配在涡轮机内部的气体流路中的装置的方法，所述方法包括：沿壳体的内表面加工套管槽; 将至少一个端口加工到与壳体槽流体连通的壳体中; 在至少一个与所述壳体沟槽流体连通的定子叶片中加工内腔; 在定子叶片的孔表面上加工至少一个与内腔流体连通的孔口; 以及将流体供应联接到所述至少一个端口。

2. 发明申请

US20130170982A1 TURBINE AND METHOD FOR SEPARATING PARTICULATES FROM A FLUID 有权
标题翻译：用于从流体分离颗粒物的涡轮机和方法
公开(公告)号：US20130170982A1
公开(公告)日：2013-07-04
申请号：US13342556
申请日：2012-01-03
申请人： Adebukola Oluwaseun Benson , Gary Michael Itzel , Kevin Richard Kirtley
发明人： Adebukola Oluwaseun Benson , Gary Michael Itzel , Kevin Richard Kirtley
IPC分类号： F01D5/18 , F02C3/04
CPC分类号： F01D5/187 , F05D2250/71 , F05D2260/607 , F05D2300/612
摘要： According to one aspect of the invention, a turbine airfoil includes a first cavity inside the turbine airfoil configured to receive a fluid and a second cavity inside the turbine airfoil. The turbine airfoil also includes a passage inside the turbine airfoil that provides fluid communication between the first and second cavities, wherein the passage includes a curved portion configured to separate particulates from the fluid as the fluid flows through the passage.
摘要翻译：根据本发明的一个方面，涡轮机翼型件包括在涡轮机翼型内部的第一空腔，其构造成接收流体，涡轮机翼内部具有第二空腔。涡轮机翼片还包括在涡轮机翼片内部的通道，其在第一和第二空腔之间提供流体连通，其中通道包括弯曲部分，该弯曲部分构造成当流体流过通道时将颗粒与流体分离。

3. 发明授权

US08206115B2 Scalloped surface turbine stage with trailing edge ridges 有权
标题翻译：具有后缘脊的扇形水轮机台
公开(公告)号：US08206115B2
公开(公告)日：2012-06-26
申请号：US12238785
申请日：2008-09-26
申请人： Anurag Gupta , Brian Chandler Barr , Kevin Richard Kirtley , Anna Tam
发明人： Anurag Gupta , Brian Chandler Barr , Kevin Richard Kirtley , Anna Tam
IPC分类号： F01D5/30 , F03D11/00
CPC分类号： F01D5/143 , F01D9/04 , F05D2240/301 , F05D2240/80 , F05D2250/20 , F05D2260/231 , F05D2270/17 , Y02T50/673 , Y02T50/675
摘要： An engine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Extending from a surface of the platforms is a trailing edge ridge structure which adjoins the pressure sides, suction sides, and trailing edges of the airfoils with their respective platforms.
摘要翻译：发动机平台包括连接到相应平台的一排翼型件，以限定它们之间的流动通道。每个翼型件包括相对的压力和吸力侧面，并且在相对的前缘和后缘之间延伸成弦。从平台的表面延伸是后缘脊结构，其与各自的平台邻接翼型的压力侧，吸力侧和后缘。

4. 发明申请

US20130051976A1 FLOW CONTROL MODULE FOR A TURBOMACHINE 审中-公开
标题翻译：涡轮控制模块
公开(公告)号：US20130051976A1
公开(公告)日：2013-02-28
申请号：US13220008
申请日：2011-08-29
申请人： Kevin Richard Kirtley
发明人： Kevin Richard Kirtley
IPC分类号： F04D27/00 , F01D17/00
CPC分类号： F01D17/14 , F02C9/16 , F02C9/18
摘要： A flow control module for a turbomachine includes an inlet extending to an outlet through a flow passage having at least one side wall. A flow control member is arranged within the flow control module. The flow control member is secured to the at least one side wall between the inlet and the outlet. The flow control member is selectively passively activated to extend into the flow passage to block cooling fluid passing through the flow control module.
摘要翻译：用于涡轮机的流量控制模块包括通过具有至少一个侧壁的流动通道延伸到出口的入口。流量控制部件设置在流量控制模块内。流动控制构件固定到入口和出口之间的至少一个侧壁。流动控制构件被选择性地被动地启动以延伸到流动通道中以阻挡通过流量控制模块的冷却流体。

5. 发明申请

US20110097210A1 TURBINE AIRFOIL 有权
标题翻译：涡轮机空气
公开(公告)号：US20110097210A1
公开(公告)日：2011-04-28
申请号：US12605054
申请日：2009-10-23
申请人： Kevin Richard Kirtley
发明人： Kevin Richard Kirtley
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/301
摘要： An airfoil is provided and includes a pressure surface and a suction surface. Radially corresponding surface characteristics of the pressure and suction surfaces at a spanwise local portion of the airfoil are formed to cooperatively define at least one of a camber line and a thickness distribution plot of the airfoil as having a radius of curvature with at least two sign changes. The number of sign changes decreases along a radial dimension of the airfoil measured from the spanwise local portion.
摘要翻译：提供翼型件，其包括压力表面和吸力表面。形成在翼型的翼展方向局部部分处的压力和吸力表面的径向对应的表面特征，以协同地限定翼型件的弯度线和厚度分布图中的至少一个，其具有至少两个符号变化的曲率半径。符号变化的数量沿着从翼展方向局部部分测量的翼型件的径向尺寸减小。

6. 发明申请

US20100143152A1 METHOD AND APPARATUS FOR INCREASING LIFT ON WIND TURBINE BLADE 有权
标题翻译：用于增加风力涡轮叶片升力的方法和装置
公开(公告)号：US20100143152A1
公开(公告)日：2010-06-10
申请号：US12494895
申请日：2009-06-30
申请人： Balaji Subramanian , Kevin Richard Kirtley , Kevin James Standish
发明人： Balaji Subramanian , Kevin Richard Kirtley , Kevin James Standish
IPC分类号： F03D1/06 , B23P15/04
CPC分类号： F03D1/0608 , F03D1/06 , F03D1/0675 , F03D7/0232 , F05B2240/202 , F05B2240/301 , F05B2240/31 , F05B2240/313 , Y02E10/721 , Y02E10/723 , Y10T29/49337
摘要： A lift device for a wind turbine blade. The lift device includes a first sidewall and an opposing second sidewall. The lift device is configured to be coupled to the wind turbine blade along a leading edge of the wind turbine blade, and to generate lift when airflow is directed across a surface of the lift device.
摘要翻译：用于风力涡轮机叶片的升降装置。提升装置包括第一侧壁和相对的第二侧壁。升降装置构造成沿着风力涡轮机叶片的前缘连接到风力涡轮机叶片，并且当气流被引导穿过提升装置的表面时产生升力。

7. 发明授权

US07549282B2 Multi-slot inter-turbine duct assembly for use in a turbine engine 失效
标题翻译：用于涡轮发动机的多槽涡轮机间导管组件
公开(公告)号：US07549282B2
公开(公告)日：2009-06-23
申请号：US11258547
申请日：2005-10-25
申请人： James Fredric Widenhoefer , Paolo Graziosi , Kevin Richard Kirtley
发明人： James Fredric Widenhoefer , Paolo Graziosi , Kevin Richard Kirtley
IPC分类号： F02C7/00
CPC分类号： F01D5/145 , F02C9/18 , F05D2260/606 , Y02T50/673 , Y10S415/914
摘要： A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the at least two injection openings is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation. Methods for optimizing the flow through the turbine engine are also disclosed.
摘要翻译：用于涡轮发动机的涡轮机间过渡管道组件中的旁通通道连接到设置在高压涡轮机上游的吸入口和设置在高压涡轮机下游的至少两个喷射开口。通过旁通通道的流动是由高压涡轮机两端的自然压差引起的。使用至少两个喷射开口的流动来激励高压涡轮机下游的边界层流，以便允许使用更积极地扩展的涡轮机间管道而没有边界层分离。还公开了优化通过涡轮发动机的流量的方法。

8. 发明授权

US07220100B2 Crescentic ramp turbine stage 有权
标题翻译：新月形斜坡涡轮机阶段
公开(公告)号：US07220100B2
公开(公告)日：2007-05-22
申请号：US11106198
申请日：2005-04-14
申请人： Ching-Pang Lee , Anna Tam , Kevin Richard Kirtley , Scott Henry Lamson
发明人： Ching-Pang Lee , Anna Tam , Kevin Richard Kirtley , Scott Henry Lamson
IPC分类号： F01D5/22
CPC分类号： F01D5/143 , F05D2250/711 , F05D2250/712 , Y02T50/673 , Y10S415/914
摘要： A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform includes a crescentic ramp increasing in height from the leading and trailing edges toward the midchord of the airfoil along the pressure side thereof.
摘要翻译：涡轮级包括连接到相应平台的一排翼型件，以限定它们之间的流动通道。每个翼型件包括相对的压力和吸力侧面，并且在相对的前缘和后缘之间延伸成弦。每个平台包括沿其压力侧从翼型的前缘和后缘向中部的高度增加的新月形斜面。

9. 发明授权

US09670785B2 Cooling assembly for a gas turbine system 有权
公开(公告)号：US09670785B2
公开(公告)日：2017-06-06
申请号：US13451053
申请日：2012-04-19
申请人： David Richard Johns , Kevin Richard Kirtley
发明人： David Richard Johns , Kevin Richard Kirtley
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/18 , F01D5/181 , F01D5/186 , F05D2240/81 , F05D2250/185 , F05D2260/201
摘要： A cooling assembly for a gas turbine system includes a turbine nozzle having at least one channel comprising a channel inlet configured to receive a cooling flow from a cooling source, wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet. Also included is an exit cavity for fluidly connecting the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure.

10. 发明授权

US08393872B2 Turbine airfoil 有权
标题翻译：涡轮翼型
公开(公告)号：US08393872B2
公开(公告)日：2013-03-12
申请号：US12605054
申请日：2009-10-23
申请人： Kevin Richard Kirtley
发明人： Kevin Richard Kirtley
IPC分类号： F03B3/12
CPC分类号： F01D5/141 , F05D2240/301
摘要： An airfoil is provided and includes a pressure surface and a suction surface. Radially corresponding surface characteristics of the pressure and suction surfaces at a spanwise local portion of the airfoil are formed to cooperatively define at least one of a camber line and a thickness distribution plot of the airfoil as having a radius of curvature with at least two sign changes. The number of sign changes decreases along a radial dimension of the airfoil measured from the spanwise local portion.
摘要翻译：提供翼型件，其包括压力表面和吸力表面。形成在翼型的翼展方向局部部分处的压力和吸力表面的径向对应的表面特征，以协同地限定翼型的弯度线和厚度分布图中的至少一个，其具有具有至少两个符号变化的曲率半径。符号变化的数量沿着从翼展方向局部部分测量的翼型件的径向尺寸减小。

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