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公开(公告)号：US20230035756A1
公开(公告)日：2023-02-02
申请号：US17386065
申请日：2021-07-27
Applicant: General Electric Company
Inventor： Mustafa Dindar , Bernard James Renggli , Andrew J. Hank , Daniel Robert Dwyer , Jeffrey S. Spruill
Abstract: A variable area exhaust nozzle defining an actual area ratio for a gas turbine engine that includes a shroud assembly having a fixed shroud and an adjustable cowl, an adjustable plug, a nozzle adjustment assembly, and a controller configured to receive data indicative of an operating speed of the gas turbine engine; determine a target area ratio based at least in part on received data indicative of the operating speed of the gas turbine engine; and operate the nozzle adjustment assembly to selectively adjust at least one of the adjustable cowl or the adjustable plug such that the actual area ratio is substantially equivalent to the target area ratio.
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公开(公告)号：US11555449B2
公开(公告)日：2023-01-17
申请号：US17088199
申请日：2020-11-03
Applicant: General Electric Company
Inventor： Mustafa Dindar , Joseph Donofrio , Richard David Cedar , David William Crall
Abstract: The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.
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公开(公告)号：US10974813B2
公开(公告)日：2021-04-13
申请号：US15864010
申请日：2018-01-08
Applicant: General Electric Company
Inventor： Mustafa Dindar
Abstract: An engine nacelle is provided for an aircraft. The engine nacelle comprises: an inlet for receiving an air flow to generate a thrust force for the aircraft; a lip portion positioned at the inlet and surrounding the inlet; and at least one strake provided on a surface of the engine nacelle.
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14.发明申请VARIABLE IMMERSION LOBE MIXER FOR TURBOFAN JET ENGINE EXHAUST AND METHOD OF FABRICATING THE SAME 有权涡轮喷气式发动机排气机的可变式倾斜式搅拌机及其制造方法公开(公告)号：US20150107225A1
公开(公告)日：2015-04-23
申请号：US14396800
申请日：2013-04-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Mustafa Dindar , Vaughn Ray Kunze
CPC classification number: F02K1/386 , B64D33/06 , B64D2033/045 , F02K1/38 , F02K1/46 , F02K1/48 , F02K1/827 , F05D2230/20 , F05D2230/60 , F05D2250/184 , F05D2250/61 , F05D2250/611 , F05D2250/70 , F05D2250/71 , F05D2260/96 , F05D2300/6033 , Y02T50/672 , Y10T29/49234
Abstract: A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that defines a plurality of core immersion lobes and a plurality of bypass immersion lobes between the forward end and the aft end. The plurality of bypass immersion lobes includes a first bypass immersion lobe and a second bypass immersion lobe. The first bypass immersion lobe has a first crown contour line extending from the forward end to the aft end of the mixer, and the second bypass immersion lobe has a second crown contour line extending from the forward end to the aft end of the mixer. The first crown contour line is different than the second crown contour line.
Abstract translation: 提供一种制造用于燃气轮机的混合器的方法。 该方法包括形成混合器的前端和后端，并且形成环形起伏的轮廓，其在前端和后端之间限定多个芯浸入波瓣和多个旁路浸没波瓣。 多个旁路浸没波瓣包括第一旁路浸没波瓣和第二旁路浸没波瓣。 第一旁路浸入波瓣具有从混合器的前端延伸到后端的第一冠轮廓线，并且第二旁路浸入波瓣具有从混合器的前端延伸到后端的第二冠轮廓线。 第一冠轮廓线与第二冠轮廓线不同。
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Patent Agency Ranking
公开(公告)号：US11898495B1
公开(公告)日：2024-02-13
申请号：US17946735
申请日：2022-09-16
Applicant: General Electric Company
Inventor： Mustafa Dindar , Scott Alan Schimmels
CPC classification number: F02C7/224 , F02C3/22 , F02K1/82 , F05D2260/213 , F05D2260/22141
Abstract: A fuel system for a gas turbine engine is provided. The gas turbine engine including an exhaust assembly. The exhaust assembly including a tail cone and defining a radial direction, a circumferential direction, an axial direction, a working gas flow path, and an outer bypass flow path, the fuel system including: a hydrogen fuel tank for holding a hydrogen fuel; a heat exchanger configured to be coupled to or integrated into the tail cone of the exhaust assembly, the heat exchanger including: a first axial flow path in flow communication with the hydrogen fuel tank; a second axial flow path in flow communication with a combustion section of the gas turbine engine; and a radial flow path.
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公开(公告)号：US11873768B1
公开(公告)日：2024-01-16
申请号：US17946766
申请日：2022-09-16
Applicant: General Electric Company
Inventor： Mustafa Dindar , Scott Alan Schimmels
CPC classification number: F02C9/40 , F02C3/22 , F02C7/224 , F02C9/28 , F05D2210/132 , F05D2220/32 , F05D2270/80
Abstract: A method of operating a fuel management unit for a fuel system. The method including: receiving data indicative of a state of an exhaust assembly using a sensor of the fuel system, the state of the exhaust assembly including a temperature of a working gas flow within the exhaust assembly; determining an amount of a hydrogen fuel in a liquid phase to provide to a hydrogen delivery assembly in response to receiving data indicative of the state of the exhaust assembly; and directing one or more components to provide the determined amount of the hydrogen fuel to the hydrogen delivery assembly.
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公开(公告)号：US11808161B2
公开(公告)日：2023-11-07
申请号：US17717387
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Jixian Yao , Kishore Ramakrishnan , Trevor Howard Wood , Mustafa Dindar
CPC classification number: F01D25/24 , B64C21/02 , B64C21/06 , F05D2220/323 , F05D2240/14 , F05D2260/60
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; and a nacelle that circumferentially surrounds the fan, the nacelle comprising an annular wall having an exterior surface and an interior surface, the exterior surface comprising a first exterior portion, and the interior surface comprising a first interior portion, wherein a first exterior portion is formed of a first structure defining an exterior surface porosity, and wherein a first interior portion is formed of a second structure defining an interior surface porosity.
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公开(公告)号：US20230323791A1
公开(公告)日：2023-10-12
申请号：US17717387
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Jixian Yao , Kishore Ramakrishnan , Trevor Howard Wood , Mustafa Dindar
CPC classification number: F01D25/24 , B64C21/06 , F05D2220/323 , F05D2240/14 , F05D2260/60
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; and a nacelle that circumferentially surrounds the fan, the nacelle comprising an annular wall having an exterior surface and an interior surface, the exterior surface comprising a first exterior portion, and the interior surface comprising a first interior portion, wherein a first exterior portion is formed of a first structure defining an exterior surface porosity, and wherein a first interior portion is formed of a second structure defining an interior surface porosity.
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公开(公告)号：US20210231054A1
公开(公告)日：2021-07-29
申请号：US17088199
申请日：2020-11-03
Applicant: General Electric Company
Inventor： Mustafa Dindar , Joseph Donofrio , Richard David Cedar , David William Crall
Abstract: The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.
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