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公开(公告)号：US11473437B2
公开(公告)日：2022-10-18
申请号：US16576933
申请日：2019-09-20
Applicant: General Electric Company
Inventor： Mark Broomer , Tyler Frederick Hooper , Jason Michael Ulberg
Abstract: In one aspect, a sealing assembly for a turbine of a gas turbine engine includes a first turbine component having a first surface and a second surface positioned aft of the first surface. The first turbine component, in turn, defines a slot positioned between the first surface and the second surface. Furthermore, the sealing assembly includes a second turbine component positioned aft of the first turbine component such that the first component and the second component define a gap therebetween. Additionally, the sealing assembly includes a seal configured to seal the gap defined between the first turbine component and the second turbine component. The seal includes a first portion positioned within the slot such that the first portion exerts a sealing force on the second surface of the first component. Moreover, the seal further includes a second portion that exerts a sealing force on the second component.
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Patent Agency Ranking
公开(公告)号：US10030538B2
公开(公告)日：2018-07-24
申请号：US14933025
申请日：2015-11-05
Applicant: General Electric Company
Inventor： Wilhelm Ramon Hernandez , Daniel Edward Demers , Tyler Frederick Hooper , Victor Hugo Silva Correia , Troy Todd Dennis
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.
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公开(公告)号：US11674403B2
公开(公告)日：2023-06-13
申请号：US17215539
申请日：2021-03-29
Applicant: General Electric Company
Inventor： Michael Elia Hayek , Tyler Frederick Hooper , Megan Lynn Williams , Jonathan David Baldiga
CPC classification number: F01D11/025 , F01D9/04 , F01D11/005 , F01D11/08 , F01D25/246 , F05D2220/32 , F05D2230/60 , F05D2240/11
Abstract: A shroud assembly including a shroud support and an annular shroud is provided. The shroud assembly includes one or more pins for securing the annular shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. A gas turbine engine having a compressor section, a combustion section, a turbine section and a shroud assembly is also provided. The shroud assembly includes one or more pins for securing the continuous shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. Methods for assembling a shroud assembly structure in a gas turbine engine are also provided.
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公开(公告)号：US20220307383A1
公开(公告)日：2022-09-29
申请号：US17215539
申请日：2021-03-29
Applicant: General Electric Company
Inventor： Michael Elia Hayek , Tyler Frederick Hooper , Megan Lynn Williams , Jonathan David Baldiga
Abstract: A shroud assembly including a shroud support and an annular shroud is provided. The shroud assembly includes one or more pins for securing the annular shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. A gas turbine engine having a compressor section, a combustion section, a turbine section and a shroud assembly is also provided. The shroud assembly includes one or more pins for securing the continuous shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. Methods for assembling a shroud assembly structure in a gas turbine engine are also provided.
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公开(公告)号：US20170198602A1
公开(公告)日：2017-07-13
申请号：US14992432
申请日：2016-01-11
Applicant: General Electric Company
Inventor： Wilhelm Ramon Hernandez , Daniel Edward Demers , Tyler Frederick Hooper , Victor Hugo Silva Correia
CPC classification number: F01D25/12 , F01D5/189 , F01D9/041 , F01D11/005 , F05D2220/32 , F05D2240/11 , F05D2240/128 , F05D2240/81 , F05D2260/201 , Y02T50/671 , Y02T50/676
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine within a nozzle segment comprising an outer and inner band and at least one vane extending between the outer and inner band. The outer band includes a forward and aft cavity. The apparatus comprises a forward impingement baffle located within the forward cavity comprising a forward cooling chamber and an aft impingement baffle located within the aft cavity comprising an aft cooling chamber. Cooling air introduced into the forward cooling air chamber passes through impingement holes of the forward impingement baffle into a forward impingement chamber then passes through an aperture to the aft cooling air chamber, and then passes through the impingement holes of the aft impingement baffle into an aft impingement chamber.
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公开(公告)号：US20170130604A1
公开(公告)日：2017-05-11
申请号：US14933025
申请日：2015-11-05
Applicant: General Electric Company
Inventor： Wilhelm Ramon Hernandez , Daniel Edward Demers , Tyler Frederick Hooper , Victor Hugo Silva Correia , Troy Todd Dennis
CPC classification number: F01D25/12 , F01D5/081 , F01D9/041 , F01D9/065 , F05D2220/32 , F05D2240/125 , F05D2240/128 , F05D2250/52 , F05D2250/71 , F05D2260/14 , F05D2260/201 , F05D2260/22141 , Y02T50/676
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.
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