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公开(公告)号：US10352567B2
公开(公告)日：2019-07-16
申请号：US14879793
申请日：2015-10-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Liangyu Wang , Anthony John Dean , Keith Robert McManus , Kapil Kumar Singh , Suhui Li , Sravan Kumar Dheeraj Kapilavai , Mathew Paul Thariyan , Owen Graham
Abstract: The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air through the premixer, and the centerbody is configured to inject fuel into the flow of air. Additionally, the centerbody includes an airfoil shape that reduces and/or substantially eliminates recirculation pockets to prevent autoignition and/or flame holding in a combustion chamber. Accordingly, the turbine system may produce fewer NOx emissions.
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公开(公告)号：US20230324048A1
公开(公告)日：2023-10-12
申请号：US18085781
申请日：2022-12-21
Applicant: General Electric Company
Inventor： Owen Graham , Sharath Nagaraja , Nicholas Magina , Fei Han , Kwanwoo Kim
CPC classification number: F23R3/26 , F23R3/002 , F23R3/04 , F23R3/10 , F23R3/28 , F02C7/18 , F05D2240/35
Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
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公开(公告)号：US20210302020A1
公开(公告)日：2021-09-30
申请号：US17138048
申请日：2020-12-30
Applicant: General Electric Company
Inventor： Owen Graham , Kwanwoo Kim , Nicholas Magina , Sharath Nagaraja , Fei Han
Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
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公开(公告)号：US20180274780A1
公开(公告)日：2018-09-27
申请号：US15468172
申请日：2017-03-24
Applicant: General Electric Company
Inventor： Kwanwoo Kim , Owen Graham , Clayton Stuart Cooper
IPC: F23M20/00
CPC classification number: F23R3/10 , F05D2240/35 , F05D2260/964 , F23R3/002 , F23R2900/00014
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an annular bulkhead adjacent to a diffuser cavity; a deflector downstream of the bulkhead and adjacent to a combustion chamber; a bulkhead support coupled to an upstream side of the deflector; a first walled enclosure coupled to the bulkhead support; and a second walled enclosure coupled to the first walled enclosure. The deflector and the bulkhead support together define a bulkhead conduit therethrough to the combustion chamber. The first walled enclosure defines a first cavity and a hot side orifice. The hot side orifice is adjacent to and in fluid communication with the bulkhead conduit. The second walled enclosure defines a second cavity and a second opening adjacent to a diffuser cavity.
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公开(公告)号：US20170102147A1
公开(公告)日：2017-04-13
申请号：US14879793
申请日：2015-10-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Liangyu Wang , Anthony John Dean , Keith Robert McManus , Kapil Kumar Singh , Suhui Li , Sravan Kumar Dheeraj Kapilavai , Mathew Paul Thariyan , Owen Graham
CPC classification number: F23R3/14 , F02C3/04 , F02C7/222 , F05D2220/32 , F05D2260/14 , F23C2900/07001 , F23D11/107 , F23D11/383 , F23D2900/14021 , F23R3/286 , F23R3/30 , Y02T50/675
Abstract: The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air through the premixer, and the centerbody is configured to inject fuel into the flow of air. Additionally, the centerbody includes an airfoil shape that reduces and/or substantially eliminates recirculation pockets to prevent autoignition and/or flame holding in a combustion chamber. Accordingly, the turbine system may produce fewer NOx emissions.
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Patent Agency Ranking
公开(公告)号：US11536457B2
公开(公告)日：2022-12-27
申请号：US17138048
申请日：2020-12-30
Applicant: General Electric Company
Inventor： Owen Graham , Kwanwoo Kim , Nicholas Magina , Sharath Nagaraja , Fei Han
Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
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公开(公告)号：US10724739B2
公开(公告)日：2020-07-28
申请号：US15468172
申请日：2017-03-24
Applicant: General Electric Company
Inventor： Kwanwoo Kim , Owen Graham , Clayton Stuart Cooper
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes an annular bulkhead adjacent to a diffuser cavity; a deflector downstream of the bulkhead and adjacent to a combustion chamber; a bulkhead support coupled to an upstream side of the deflector; a first walled enclosure coupled to the bulkhead support; and a second walled enclosure coupled to the first walled enclosure. The deflector and the bulkhead support together define a bulkhead conduit therethrough to the combustion chamber. The first walled enclosure defines a first cavity and a hot side orifice. The hot side orifice is adjacent to and in fluid communication with the bulkhead conduit. The second walled enclosure defines a second cavity and a second opening adjacent to a diffuser cavity.
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公开(公告)号：US10941939B2
公开(公告)日：2021-03-09
申请号：US15714118
申请日：2017-09-25
Applicant: General Electric Company
Inventor： Owen Graham , Kwanwoo Kim , Nicholas Magina , Sharath Nagaraja , Fei Han
Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
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公开(公告)号：US10513984B2
公开(公告)日：2019-12-24
申请号：US14834467
申请日：2015-08-25
Applicant: General Electric Company
Inventor： Kwanwoo Kim , Fei Han , Owen Graham
IPC: F02C7/045 , F02C7/24 , F01D25/04 , F02C3/14 , F23R3/04 , F01D9/02 , F02C3/04 , F02C7/04 , F02C9/18 , F23R3/42
Abstract: In one aspect the present subject matter is directed to a system for suppressing acoustic noise within a combustion section of a gas turbine. The system includes at least one static structure disposed forward of a combustion chamber defined within the combustion section. The static structure at least partially defines a diffuser cavity upstream of the combustion chamber. A baffle plate is coupled to the static structure. The baffle plate and the static structure at least partially define an air plenum within the combustion section forward of the combustion chamber. The baffle plate includes an aperture that provides for fluid communication between the diffuser cavity and the air plenum. The at least one static structure and the baffle plate define a Helmholtz resonator within the combustion section.
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公开(公告)号：US20190093891A1
公开(公告)日：2019-03-28
申请号：US15714118
申请日：2017-09-25
Applicant: General Electric Company
Inventor： Owen Graham , Kwanwoo Kim , Nicholas Magina , Sharath Nagaraja , Fei Han
Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
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