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公开(公告)号：US10125632B2
公开(公告)日：2018-11-13
申请号：US14887988
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Matthew Peter Scoffone , Jason Edward Albert , Michael Robert Berry , Mitchell Allan Merrill
Abstract: Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.
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公开(公告)号：US20170159479A1
公开(公告)日：2017-06-08
申请号：US14963019
申请日：2015-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate , Jason Edward Albert
CPC classification number: F01D11/006 , F01D25/246 , F04D29/083 , F05D2240/57 , F05D2250/61
Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two components. The seal assembly may include an upstream corner shim and a downstream corner shim, where one of the upstream corner shim or the downstream corner shim includes a pressure actuation feature configured to block a flow of gas between the two components.
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公开(公告)号：US10267171B2
公开(公告)日：2019-04-23
申请号：US14962979
申请日：2015-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate , Jason Edward Albert
Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly disposed between the two components. The seal assembly may include an upstream corner shim, a downstream corner shim, and/or one or more intersegment seals that are configured to block a flow of fluid between the two components.
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公开(公告)号：US10094231B2
公开(公告)日：2018-10-09
申请号：US14963034
申请日：2015-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate , Jason Edward Albert , Christopher Edward Wolfe
Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two components. The seal assembly may include a first intersegment seal, a second intersegment seal, and a rope seal that are configured to block a flow of gas between the two components.
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公开(公告)号：US20170107853A1
公开(公告)日：2017-04-20
申请号：US14918005
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Matthew Peter Scoffone , Jason Edward Albert , Michael Robert Berry , Mitchell Allan Merrill
CPC classification number: F01D25/14 , F01D9/02 , F01D9/065 , F01D25/12 , F02C7/18 , F05D2240/10 , F05D2240/128 , F05D2260/202 , F05D2260/232 , Y02T50/676
Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.
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Patent Agency Ranking
公开(公告)号：US20190024519A1
公开(公告)日：2019-01-24
申请号：US15657558
申请日：2017-07-24
Applicant: General Electric Company
Inventor： Jason Edward Albert
Abstract: The present disclosure is directed to a turbomachine airfoil including an exterior wall having a trailing edge. The exterior wall defines a radially-extending cooling cavity and one or more trailing edge cooling passages extending through the exterior wall. Each trailing edge cooling passage includes an inlet in fluid communication with the cooling cavity and a first portion in fluid communication with the inlet. Each trailing edge cooling passage also includes a second portion in fluid communication with the first portion. The second portion includes a first outlet defined by the exterior wall at the trailing edge. Each trailing edge cooling passage further includes a third portion in fluid communication with the first portion. The third portion includes a second outlet defined by the exterior wall at the trailing edge. The second and third portions are separated by a rib extending upstream from the trailing edge.
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公开(公告)号：US10132195B2
公开(公告)日：2018-11-20
申请号：US14918005
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Matthew Peter Scoffone , Jason Edward Albert , Michael Robert Berry , Mitchell Allan Merrill
Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.
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公开(公告)号：US20170107850A1
公开(公告)日：2017-04-20
申请号：US14887988
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Matthew Peter Scoffone , Jason Edward Albert , Michael Robert Berry , Mitchell Allan Merrill
CPC classification number: F01D25/12 , F01D5/189 , F01D9/02 , F01D9/06 , F01D25/08 , F05D2240/128 , F05D2260/20 , F05D2260/232
Abstract: Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.
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公开(公告)号：US10247024B2
公开(公告)日：2019-04-02
申请号：US14963019
申请日：2015-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bodhayan Dev , Neelesh Nandkumar Sarawate , Jason Edward Albert
Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two components. The seal assembly may include an upstream corner shim and a downstream corner shim, where one of the upstream corner shim or the downstream corner shim includes a pressure actuation feature configured to block a flow of gas between the two components.
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公开(公告)号：US09970299B2
公开(公告)日：2018-05-15
申请号：US14855490
申请日：2015-09-16
Applicant: General Electric Company
Inventor： Matthew Peter Scoffone , Jason Edward Albert , Mitchell Merrill
CPC classification number: F01D5/08 , F02C6/08 , F02C7/12 , F05D2210/44 , F05D2240/127
Abstract: The present application provides a purge flow delivery system that may be used with a gas turbine engine. The purge flow delivery system may include a mixing chamber with a first sidewall, a second sidewall, and a cover plate, a first inlet tube positioned about the first sidewall, the first inlet tube configured to deliver a first fluid to the mixing chamber, a second inlet tube positioned about the second sidewall, the second inlet tube configured to deliver a second fluid to the mixing chamber, and a baffle plate attached to the cover plate and positioned to direct the first fluid at a first angle and the second fluid at a second angle.
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