公开(公告)号：US09845691B2

公开(公告)日：2017-12-19

申请号：US13662284

申请日：2012-10-26

Applicant: General Electric Company

Inventor： Marshall Scott Allen ,  Victor Hugo Silva Correia ,  Robert Proctor ,  Jared Peter Buhler

IPC: F01D9/04 ,  F01D25/00 ,  F01D5/18

CPC classification number: F01D9/041 ,  F01D5/189 ,  F01D25/00 ,  F05B2230/237 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/676

Abstract: A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.

公开(公告)号：US20170138372A1

公开(公告)日：2017-05-18

申请号：US14941995

申请日：2015-11-16

Applicant: General Electric Company

Inventor： Sesha Subramanian ,  Monty Lee Shelton ,  Robert Proctor ,  Mohamed Musthafa Thoppil ,  Venkateswararao Gurram ,  Josiah Warren Joiner ,  Wojciech Sak

IPC: F04D29/58 ,  F04D29/54 ,  F04D29/08 ,  F04D29/32

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.

公开(公告)号：US20160333719A1

公开(公告)日：2016-11-17

申请号：US15222328

申请日：2016-07-28

Applicant: General Electric Company

Inventor： Joseph C. Albers ,  Monty Lee Shelton ,  Robert Proctor ,  Richard Russo, JR.

IPC: F01D11/12 ,  F02C7/28 ,  F01D25/24

CPC classification number: F01D11/122 ,  F01D11/005 ,  F01D11/127 ,  F01D25/246 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/57 ,  Y02T50/671

Abstract: A method of making a shroud assembly by: forming a shroud frame consisting of a one-piece hook and rail assembly which includes a first rail and a second rail disposed at lateral edges and a first support and a second support connected to the first rail and the second rail, the first and second rails and the first and second supports being integrally joined to one another and defining a central aperture therebetween; joining a metallic backsheet to the shroud frame covering the central aperture; and attaching a honeycomb rubs strip to the metallic backsheet via an upper edge of the honeycomb seal structure.

Abstract translation: 一种制造护罩组件的方法，其特征在于：形成由单件式钩和导轨组件组成的护罩框架，该护罩框架包括设置在侧边缘处的第一轨道和第二轨道，以及连接到第一轨道的第一支撑件和第二支撑件， 所述第二轨道，所述第一轨道和所述第二轨道以及所述第一和第二支撑件彼此一体地连接并且在它们之间限定中心孔; 将金属底片连接到覆盖中心孔的护罩框架; 以及通过蜂窝密封结构的上边缘将蜂窝状擦拭条附着在金属底片上。

公开(公告)号：US09341074B2

公开(公告)日：2016-05-17

申请号：US13743818

申请日：2013-01-17

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Daniel John Fusinato ,  John Carl Glessner ,  Dan Nicholas Mirkovich ,  Robert Proctor

IPC: F01D11/24 ,  F01D25/12 ,  F01D25/14

CPC classification number: F01D11/24 ,  F01D25/12 ,  F01D25/14 ,  F05D2200/33 ,  F05D2260/201 ,  F05D2260/30 ,  Y02T50/676

Abstract: Active clearance control systems for gas turbine engines are disclosed. An example active clearance control system may include a generally circumferentially mounted spray tube comprising a plurality of impingement holes arranged to impinge thermal control air on a clearance control component of a case; a rigid mounting assembly substantially rigidly coupling the spray tube to the case; and/or a sliding mounting assembly coupling the spray tube to the case while permitting limited relative movement between the spray tube and the case in a direction generally parallel with an engine axis. The sliding mount may be coupled to the case generally axially forward of the rigid mount. A ratio of the stand-off distance to the impingement hole diameter may be less than about 8. A ratio of the arc spacing to the impingement hole diameter may be less than about 15.

Abstract translation: 公开了用于燃气涡轮发动机的主动间隙控制系统。 示例性主动间隙控制系统可以包括大致周向安装的喷射管，其包括多个冲击孔，其被布置成将热控制空气撞击到壳体的间隙控制部件上; 将喷射管基本上刚性地连接到壳体上的刚性安装组件; 和/或滑动安装组件，其将喷射管连接到壳体，同时允许喷射管和壳体在大致平行于发动机轴线的方向上的有限的相对运动。 滑动安装件可以连接到刚性安装座的大致轴向前方的壳体。 间隔距离与冲击孔直径的比值可以小于约8.弧距与冲击孔直径的比可以小于约15。