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公开(公告)号：US12286932B1
公开(公告)日：2025-04-29
申请号：US18441736
申请日：2024-02-14
Applicant: General Electric Company
Inventor： Hejie Li , Hiranya Nath , Habeeb Kunnummal Manat , Shai Birmaher , Craig Alan Gonyou , Anquan Wang , Michael A. Benjamin
Abstract: A combustor of a turbine engine has a combustion chamber for combusting fuel and air, generating heat. A fuel nozzle-mixer assembly mixes and injects fuel and air into the combustion chamber for combustion. The assembly has a heat shield at an aft end for shielding the assembly from the heat. A centerbody outer shell defines a cooling air flow cavity. A cooling air flow gap is defined between the centerbody outer shell and the heat shield. The centerbody outer shell has cooling air exit holes between the cooling air flow cavity and the cooling air flow gap, the air passing through the cooling air exit holes and into the cooling air flow gap. The cooling air exits the cooling air flow gap at a cooling air exit angle, the cooling air exit angle having a non-zero axially aft component, displacing the combustion downstream, to protect the assembly.
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公开(公告)号：US12270542B2
公开(公告)日：2025-04-08
申请号：US17187040
申请日：2021-02-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Anquan Wang , Eric John Ruggiero
Abstract: An apparatus, system, and method of reducing film cooling scrubbing in a combustor are provided. The apparatus includes a combustor liner that includes a field of a plurality of sparsely-spaced film holes that extend through the combustor liner wherein the field includes a boundary. The combustor liner also includes a patch of relatively more densely-spaced shield holes that extend through the combustor liner at specific predetermined locations within the boundary of the field.
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公开(公告)号：US20190162117A1
公开(公告)日：2019-05-30
申请号：US15823732
申请日：2017-11-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Anquan Wang , Hojjat Nasr , Craig Alan Gonyou , Michael Anthony Benjamin
Abstract: A combustor assembly for a turbine engine and method for cooling a portion of the combustor assembly, the combustor assembly comprising a combustor liner defining a combustion chamber with an inlet and an outlet, a fuel dome located in the inlet and having a wall adjacent at least a portion of the combustor liner, and a deflector overlying and spaced from at least a portion of the wall.
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公开(公告)号：US20200224539A1
公开(公告)日：2020-07-16
申请号：US16249285
申请日：2019-01-16
Applicant: General Electric Company
Inventor： Anquan Wang , Ryan Christopher Jones , Paul Christopher Schilling , Craig Alan Gonyou
IPC: F01D5/18
Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.
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公开(公告)号：US10197474B2
公开(公告)日：2019-02-05
申请号：US15586734
申请日：2017-05-04
Applicant: General Electric Company
Inventor： Anquan Wang , Guanghua Wang , James Peter DeLancey
Abstract: A system for use in inspecting a component having flow openings defined therein. The system includes a fluid injector in flow communication with the component, wherein the fluid injector provides fluid to the component such that the fluid is discharged from the flow openings. A sensing sheet is coupled to or positioned proximate to the component such that the fluid discharged from the flow openings is received at the sensing sheet, wherein the sensing sheet is formed from pressure-sensitive material. A light source emits light towards the sensing sheet such that the pressure-sensitive material is excited to an energy level. The system further includes an imaging device that captures images of a change in color of the pressure-sensitive material as a function of a pressure of the fluid received at the sensing sheet, wherein the change in color represents a pressure distribution across the sensing sheet based on a flow profile of the fluid discharged from the flow openings.
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Patent Agency Ranking
公开(公告)号：US20180321113A1
公开(公告)日：2018-11-08
申请号：US15586734
申请日：2017-05-04
Applicant: General Electric Company
Inventor： Anquan Wang , Guanghua Wang , James Peter DeLancey
CPC classification number: G01M15/14 , F01D5/186 , F01D9/02 , F01D21/003 , F05D2220/32 , F05D2260/202 , F05D2260/83 , F23R3/002 , F23R2900/00019 , F23R2900/03042
Abstract: A system for use in inspecting a component having flow openings defined therein. The system includes a fluid injector in flow communication with the component, wherein the fluid injector provides fluid to the component such that the fluid is discharged from the flow openings. A sensing sheet is coupled to or positioned proximate to the component such that the fluid discharged from the flow openings is received at the sensing sheet, wherein the sensing sheet is formed from pressure-sensitive material. A light source emits light towards the sensing sheet such that the pressure-sensitive material is excited to an energy level. The system further includes an imaging device that captures images of a change in color of the pressure-sensitive material as a function of a pressure of the fluid received at the sensing sheet, wherein the change in color represents a pressure distribution across the sensing sheet based on a flow profile of the fluid discharged from the flow openings.
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公开(公告)号：US20180266687A1
公开(公告)日：2018-09-20
申请号：US15460924
申请日：2017-03-16
Applicant: General Electric Company
Inventor： Anquan Wang , Eric John Ruggiero
CPC classification number: F23R3/002 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
Abstract: An apparatus, system, and method of reducing film cooling scrubbing in a combustor are provided. The apparatus includes a combustor liner that includes a field of a plurality of sparsely-spaced film holes that extend through the combustor liner wherein the field includes a boundary. The combustor liner also includes a patch of relatively more densely-spaced shield holes that extend through the combustor liner at specific predetermined locations within the boundary of the field.
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公开(公告)号：US20170198911A1
公开(公告)日：2017-07-13
申请号：US14993366
申请日：2016-01-12
Applicant: General Electric Company
Inventor： Anquan Wang , Wilbur Douglas Scheidt , Jeffrey Lehmkuhl
Abstract: An engine component is generally provided for a gas turbine engine generating hot combustion gas flow. In one embodiment, the engine the engine component includes a substrate having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The passage defines a diffusion section having a pair of side passage walls extending to the outlet on the hot surface, with each of the side passage walls within the diffusion section having a surface roughness (Ra) of about 4 mils to about 7 mils. Methods are also provided for forming a film hole in a CMC substrate.
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公开(公告)号：US20250093032A1
公开(公告)日：2025-03-20
申请号：US18469187
申请日：2023-09-18
Applicant: GENERAL ELECTRIC COMPANY , GE Marmara Technology Center Muhendislik Hizmetleri Ltd , GE Aerospace Poland sp. z o.o.
Inventor： Emrah Deniz , Fatih Yasar , Katarzyna Anna Mikolajczyk , Michael T. Bucaro , Ahmet Kacar , Anquan Wang , Hejie Li , Craig Alan Gonyou , Aaron C. Brady
Abstract: A gas turbine engine comprises a compressor section, a combustion section, and a turbine section in a serial flow arrangement and enshrouded by a casing, the combustion section comprising: an annular combustion chamber defined by at least a dome wall and an annular liner; a plurality of combustor cups circumferentially arranged on the dome wall; a fuel supply connected to the casing; and a fuel nozzle passing through the casing and having a nozzle tube and a distribution manifold fluidly coupling the nozzle tube to at least two combustor cups of the plurality of combustor cups; wherein the fuel nozzle is fixed to the at least two combustor cups.
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公开(公告)号：US11873734B2
公开(公告)日：2024-01-16
申请号：US17068235
申请日：2020-10-12
Applicant: General Electric Company
Inventor： Anquan Wang , Ryan Christopher Jones , Paul Christopher Schilling , Craig Alan Gonyou
IPC: F01D5/18
CPC classification number: F01D5/186
Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.
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