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公开(公告)号：US11377957B2
公开(公告)日：2022-07-05
申请号：US15590363
申请日：2017-05-09
Applicant: General Electric Company
Inventor： Alan Glenn Turner , Monty Lee Shelton , Anand Roday , Aigbedion Akwara
Abstract: A gas turbine engine includes a compressor section having a high pressure compressor, the high pressure compressor including an aft-most compressor stage. The gas turbine engine also includes a combustion section having a stage of discharge nozzles, the stage of discharge nozzles located downstream of the aft-most compressor stage and upstream of a diffuser cavity. The gas turbine engine also includes a high pressure spool drivingly coupled to the high pressure compressor, the high pressure spool forming in part a compressor discharge pressure seal and including a forward spool section. The forward spool section extends between the compressor discharge pressure seal and the aft-most compressor stage, the forward spool section defining an airflow cavity for providing a cooling airflow from the diffuser cavity to the aft-most compressor stage.
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公开(公告)号：US20200011347A1
公开(公告)日：2020-01-09
申请号：US16555558
申请日：2019-08-29
Applicant: General Electric Company
Inventor： Sesha Subramanian , Monty Lee Shelton , Robert Proctor , Mohamed Musthafa Thoppil , Venkateswararao Gurram , Josiah Warren Joiner , Wojciech Sak
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.
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公开(公告)号：US20140271142A1
公开(公告)日：2014-09-18
申请号：US13827762
申请日：2013-03-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joseph C. Albers , Monty Lee Shelton , Robert Proctor , Richard Russo, JR.
IPC: 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 turbine shroud assembly comprises a honeycomb rub strip, a metallic backsheet disposed along an upper edge of said honeycomb seal structure, a shroud frame having a first rail and a second rail disposed at lateral edges of said metallic backsheet, a first support and a second support connected to the first rail and the second rail, a spline extending axially in the first rail and the second rail along laterally outer surfaces of the first rail and the second rail and, a spline seal having a first edge and a second opposite edge, the first edge disposed in each of the spline grooves and the second opposite edge being capable of positioning in an adjacent shroud assembly.
Abstract translation: 涡轮机罩组件包括蜂窝状擦拭条，沿着所述蜂窝密封结构的上边缘设置的金属底片，具有设置在所述金属底片的侧边缘处的第一轨道和第二轨道的护罩框架，第一支撑件和第二支撑件 连接到第一轨道和第二轨道的支撑件，沿第一轨道和第二轨道的横向外表面在第一轨道和第二轨道中轴向延伸的花键，以及具有第一边缘和第二相对边缘的花键密封件， 设置在每个花键槽中的第一边缘和第二相对边缘能够定位在相邻的护罩组件中。
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公开(公告)号：US20140140833A1
公开(公告)日：2014-05-22
申请号：US13683813
申请日：2012-11-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joseph Charles Albers , Robert Proctor , Monty Lee Shelton , Richard Russo, JR.
CPC classification number: F01D25/28 , F01D5/12 , F01D5/225 , F01D11/122 , F01D11/127
Abstract: A turbine shroud apparatus for a gas turbine engine having a centerline axis includes: a shroud segment having: an arcuate body extending axially between forward and aft ends and laterally between opposed end faces, wherein each of the end faces includes seal slots formed therein; and an arcuate stationary seal member mounted to the body; a turbine vane disposed axially aft of the shroud segment; and a casing surrounding the shroud segment and the turbine vane; wherein the turbine vane is mounted to the case so as to bear against the stationary seal member, compressing it and forcing the shroud segment radially outward against the casing.
Abstract translation: 一种具有中心轴线的燃气涡轮发动机的涡轮机护罩装置，包括：护罩段，其具有：在前端和后端之间轴向延伸并且在相对的端面之间横向延伸的弧形体，其中每个端面包括形成在其中的密封槽; 以及安装在所述主体上的弧形固定密封构件; 设置在所述护罩段的轴向后方的涡轮叶片; 以及围绕所述护罩段和所述涡轮叶片的壳体; 其中所述涡轮叶片安装到所述壳体上以便抵靠所述固定密封构件，将所述涡轮叶片压缩并迫使所述护罩段径向向外抵靠所述壳体。
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公开(公告)号：US10654577B2
公开(公告)日：2020-05-19
申请号：US15439122
申请日：2017-02-22
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Thomas Ory Moniz , Monty Lee Shelton , Joel Francis Kirk , Jeffrey Donald Clements
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a low pressure (LP) turbine defining an outer flowpath. The outer flowpath defines a first outer flowpath radius at an upstream-most end of the LP turbine, a last outer flowpath radius disposed at a downstream-most end of the LP turbine, a middle outer flowpath radius disposed therebetween along the longitudinal direction. The middle outer flowpath radius is greater than the last outer flowpath radius.
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Patent Agency Ranking
公开(公告)号：US20180328177A1
公开(公告)日：2018-11-15
申请号：US15590363
申请日：2017-05-09
Applicant: General Electric Company
Inventor： Alan Glenn Turner , Monty Lee Shelton , Anand Roday , Aigbedion Akwara
CPC classification number: F01D5/084 , F01D25/12 , F02C7/28 , F05D2220/3216 , F05D2240/55
Abstract: A gas turbine engine includes a compressor section having a high pressure compressor, the high pressure compressor including an aft-most compressor stage. The gas turbine engine also includes a combustion section having a stage of discharge nozzles, the stage of discharge nozzles located downstream of the aft-most compressor stage and upstream of a diffuser cavity. The gas turbine engine also includes a high pressure spool drivingly coupled to the high pressure compressor, the high pressure spool forming in part a compressor discharge pressure seal and including a forward spool section. The forward spool section extends between the compressor discharge pressure seal and the aft-most compressor stage, the forward spool section defining an airflow cavity for providing a cooling airflow from the diffuser cavity to the aft-most compressor stage.
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公开(公告)号：US20180283203A1
公开(公告)日：2018-10-04
申请号：US15478321
申请日：2017-04-04
Applicant: General Electric Company
CPC classification number: F01D21/02 , F01D5/02 , F01D5/12 , F01D9/042 , F01D21/045 , F01D25/24 , F01D25/246 , F05D2220/323 , F05D2260/311 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine engine, system, and method of severing at least one blade of a row of blades spaced about a rotor during an over speed condition are provided. The gas turbine engine includes a shaft rotatable about an axis of the shaft, a rotor coupled to the shaft and having a radially outer surface, and one or more rows of blades spaced axially along the outer portion. Each row of blades includes a plurality of blades spaced circumferentially around the radially outer surface. A gas turbine engine casing at least partially surrounds the one or more rows of blades. One or more rows of stationary vanes are spaced axially along the casing. Each row of stationary vanes includes a plurality of stationary vanes extending radially between the shaft and the gas turbine engine casing. The stationary vanes are coupled to the gas turbine engine casing using a fuse element.
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公开(公告)号：US09238977B2
公开(公告)日：2016-01-19
申请号：US13683813
申请日：2012-11-21
Applicant: General Electric Company
Inventor： Joseph Charles Albers , Robert Proctor , Monty Lee Shelton , Richard Russo, Jr.
CPC classification number: F01D25/28 , F01D5/12 , F01D5/225 , F01D11/122 , F01D11/127
Abstract: A turbine shroud apparatus for a gas turbine engine having a centerline axis includes: a shroud segment having: an arcuate body extending axially between forward and aft ends and laterally between opposed end faces, wherein each of the end faces includes seal slots formed therein; and an arcuate stationary seal member mounted to the body; a turbine vane disposed axially aft of the shroud segment; and a casing surrounding the shroud segment and the turbine vane; wherein the turbine vane is mounted to the case so as to bear against the stationary seal member, compressing it and forcing the shroud segment radially outward against the casing.
Abstract translation: 一种具有中心轴线的燃气涡轮发动机的涡轮机护罩装置，包括：护罩段，其具有：在前端和后端之间轴向延伸并且在相对的端面之间横向延伸的弧形体，其中每个端面包括形成在其中的密封槽; 以及安装在所述主体上的弧形固定密封构件; 设置在所述护罩段的轴向后方的涡轮叶片; 以及围绕所述护罩段和所述涡轮叶片的壳体; 其中所述涡轮叶片安装到所述壳体上以便抵靠所述固定密封构件，将所述涡轮叶片压缩并迫使所述护罩段径向向外抵靠所述壳体。
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公开(公告)号：US20220280998A1
公开(公告)日：2022-09-08
申请号：US17473281
申请日：2021-09-13
Applicant: General Electric Company
Inventor： Paul Mathew , Mohandas Nayak , Sathisha Chikkabikkodu Hanum , Monty Lee Shelton
Abstract: An anti-fretting coating composition that is operationally stable at temperatures of 800° F. to 2650° F. is provided. The anti-fretting coating composition primarily includes cobalt and aluminum oxide and may also include other modifying phases that enhance the overall tribological performance. A component coated with the anti-fretting coating composition is also provided. The component includes a substrate having a first contact surface shaped to cooperate with a second contact surface of an abutting member in a manner which can develop wear between the first contact surface and the second contact surface. The first contact surface includes an anti-fretting coating thereon formed from the disclosed anti-fretting coating composition.
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公开(公告)号：US11199111B2
公开(公告)日：2021-12-14
申请号：US16901568
申请日：2020-06-15
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Christopher Charles Glynn , Corey Bourassa , Monty Lee Shelton , Robert Francis Manning , Victor Hugo Silva Correia
IPC: B01D39/00 , F01D25/32 , B01D46/24 , B01D45/12 , B01D46/42 , F01D25/12 , F01D9/06 , B01D45/08 , B01D45/16 , B01D50/00
Abstract: An assembly for removing particles from a fluid stream includes a first particle remover having a main flow outlet emitting a first reduced-particle stream and a scavenge flow outlet emitting a particle-laden stream, as well as a second particle remover fluidly coupled to the scavenge flow outlet and emitting a second reduced-particle stream.
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