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公开(公告)号：US20170363212A1
公开(公告)日：2017-12-21
申请号：US15183309
申请日：2016-06-15
Applicant: General Electric Company
IPC: F16J15/447
CPC classification number: F16J15/444
Abstract: A sealing element apparatus for a rotating seal includes an array of cells defining an annular sealing surface, where the cells are divided into a plurality of layers extending parallel to the sealing surface.
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公开(公告)号：US10316681B2
公开(公告)日：2019-06-11
申请号：US15168581
申请日：2016-05-31
Applicant: General Electric Company
Inventor： Jagata Laxmi Narasimharao , Thomas Ory Moniz , Mohamed Musthafa Thoppil , Bhaskar Nanda Mondal , Atanu Saha
Abstract: A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembly further includes a plurality of seals in series, at least one seal of the plurality of seals is coupled between a static support member and a respective rotor stage such that a plurality of turbine cavities in series are defined within the wheelspace. Each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheel space.
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公开(公告)号：US10451084B2
公开(公告)日：2019-10-22
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
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：US11359646B2
公开(公告)日：2022-06-14
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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Patent Agency Ranking
公开(公告)号：US20180030986A1
公开(公告)日：2018-02-01
申请号：US15221962
申请日：2016-07-28
Applicant: General Electric Company
Inventor： Arnab Sen , Mohamed Musthafa Thoppil , Nathan Evan McCurdy Gibson
Abstract: A turbine engine with a stator having axially spaced first and second structural elements along with a rotor and a face seal between the rotor and the stator including a non-rotating gas bearing face coupled to the first and second structural elements, and a rotating gas bearing face coupled to the rotor and confronting the non-rotating gas bearing surface. Introducing airflow to one or multiple parts of the seal.
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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
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：US10823184B2
公开(公告)日：2020-11-03
申请号：US15221962
申请日：2016-07-28
Applicant: General Electric Company
Inventor： Arnab Sen , Mohamed Musthafa Thoppil , Nathan Evan McCurdy Gibson
IPC: F01D11/02 , F04D27/00 , F01D11/04 , F16J15/34 , F01D5/02 , F01D9/02 , F01D11/00 , F01D25/10 , F04D29/056 , F04D29/32 , F04D29/54
Abstract: A turbine engine with a stator having axially spaced first and second structural elements along with a rotor and a face seal between the rotor and the stator including a non-rotating gas bearing face coupled to the first and second structural elements, and a rotating gas bearing face coupled to the rotor and confronting the non-rotating gas bearing surface. Introducing airflow to one or multiple parts of the seal.
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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：US20170342851A1
公开(公告)日：2017-11-30
申请号：US15168581
申请日：2016-05-31
Applicant: General Electric Company
Inventor： Jagata Laxmi Narasimharao , Thomas Ory Moniz , Mohamed Musthafa Thoppil , Bhaskar Nanda Mondal , Atanu Saha
CPC classification number: F01D11/04 , F01D3/00 , F01D5/082 , F01D5/085 , F01D5/12 , F01D11/001 , F01D11/02 , F01D25/12 , F02C7/28 , F05D2220/32 , F05D2230/60 , F05D2240/55 , Y02T50/673 , Y02T50/676
Abstract: A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembly further includes a plurality of seals in series, at least one seal of the plurality of seals is coupled between a static support member and a respective rotor stage such that a plurality of turbine cavities in series are defined within the wheelspace. Each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheel space.
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