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Patent Agency Ranking
公开(公告)号：US10823416B2
公开(公告)日：2020-11-03
申请号：US15673882
申请日：2017-08-10
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Daniel Kirtley , Duane Douglas Thomsen , Neeraj Kumar Mishra , Adam Robert Kahn
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a bulkhead wall extended generally along a radial direction relative to a combustor centerline and a mixer disposed concentric to the nozzle centerline. The bulkhead wall defines one or more openings therethrough adjacent to a combustion chamber. Each of the openings defines a nozzle centerline extended along a lengthwise direction. The mixer comprises a retaining wall extended along a radial direction relative to the nozzle centerline and coupled to the upstream side of the bulkhead wall. The mixer further comprises an annular shroud extended at least partially through the one or more openings of the bulkhead wall. The mixer defines a cooling passage through the retaining wall and the annular shroud. The cooling passage defines an inlet opening through the retaining wall and an outlet opening through the annular shroud.
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公开(公告)号：US20190049113A1
公开(公告)日：2019-02-14
申请号：US15673882
申请日：2017-08-10
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Daniel Kirtley , Duane Douglas Thomsen , Neeraj Kumar Mishra , Adam Robert Kahn
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a bulkhead wall extended generally along a radial direction relative to a combustor centerline and a mixer disposed concentric to the nozzle centerline. The bulkhead wall defines one or more openings therethrough adjacent to a combustion chamber. Each of the openings defines a nozzle centerline extended along a lengthwise direction. The mixer comprises a retaining wall extended along a radial direction relative to the nozzle centerline and coupled to the upstream side of the bulkhead wall. The mixer further comprises an annular shroud extended at least partially through the one or more openings of the bulkhead wall. The mixer defines a cooling passage through the retaining wall and the annular shroud. The cooling passage defines an inlet opening through the retaining wall and an outlet opening through the annular shroud.
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公开(公告)号：US09976746B2
公开(公告)日：2018-05-22
申请号：US14842872
申请日：2015-09-02
Applicant: General Electric Company
Inventor： Nicholas John Bloom , Daniel Kirtley , Adam Robert Kahn
CPC classification number: F23R3/60 , F02C3/04 , F05D2220/32 , F05D2240/90 , F05D2260/941 , F23M2900/05002 , F23R3/002 , F23R3/007 , F23R3/10 , F23R2900/00017
Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. Additionally, a heat shield is provided. The heat shield includes an end also received within the slot defined by the annular dome. A mounting assembly attaches the forward end of the liner and the end of the heat shield to the annular dome, such that the forward end of the liner and the end of the heat shield are co-mounted within the slot defined by the annular dome.
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公开(公告)号：US10113486B2
公开(公告)日：2018-10-30
申请号：US14876543
申请日：2015-10-06
Applicant: General Electric Company
Inventor： John Herman Mueller , Andrew Bradley Gebbia , Adam Robert Kahn
Abstract: A method of transferring a fluid flow from a static component to a rotor of a gas turbine engine and a modulated flow transfer system are provided. The modulated flow transfer system includes an annular inducer configured to accelerate the fluid flow in a substantially circumferential direction in a direction of rotation of the rotor. The system further includes a first fluid flow supply including a compressor bleed connection, a feed manifold formed of bendable tubing, and a feed header extending between the compressor bleed connection and the feed manifold. The feed header includes a modulating valve configured to control an amount of fluid flow into the feed manifold. The system also includes a flow supply tube that extends between the feed manifold and the inducer and is couplable to at least one of the plurality of first fluid flow inlet openings through a sliding piston seal.
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公开(公告)号：US20170096945A1
公开(公告)日：2017-04-06
申请号：US14876543
申请日：2015-10-06
Applicant: General Electric Company
Inventor： John Herman Mueller , Andrew Bradley Gebbia , Adam Robert Kahn
CPC classification number: F02C9/18 , F01D5/02 , F01D5/082 , F01D5/088 , F02C3/04 , F02C7/12 , F02C7/125 , F02C7/18 , F02K3/04 , F04D29/321 , F04D29/325 , F05D2220/36 , F05D2230/642 , F05D2240/129 , F05D2240/35 , F05D2240/58 , F05D2250/322 , F05D2260/16 , F05D2260/607 , Y02T50/671 , Y02T50/676
Abstract: A method of transferring a fluid flow from a static component to a rotor of a gas turbine engine and a modulated flow transfer system are provided. The modulated flow transfer system includes an annular inducer configured to accelerate the fluid flow in a substantially circumferential direction in a direction of rotation of the rotor. The system further includes a first fluid flow supply including a compressor bleed connection, a feed manifold formed of bendable tubing, and a feed header extending between the compressor bleed connection and the feed manifold. The feed header includes a modulating valve configured to control an amount of fluid flow into the feed manifold. The system also includes a flow supply tube that extends between the feed manifold and the inducer and is couplable to at least one of the plurality of first fluid flow inlet openings through a sliding piston seal.
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