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公开(公告)号：US11846209B2
公开(公告)日：2023-12-19
申请号：US17963029
申请日：2022-10-10
Applicant: General Electric Company
Inventor： Christophe Jude Day , Kenneth Edward Seitzer , Michael Alan Hile , Thomas Alan Wall , Carol Anne Venn , Anthony Paul Greenwood
CPC classification number: F01D9/06 , F01D5/082 , F01D25/32 , F02C7/18 , F02C9/18 , F05D2210/40 , F05D2220/323 , F05D2230/22 , F05D2230/30 , F05D2230/51 , F05D2230/60 , F05D2240/12 , F05D2250/25 , F05D2260/14 , F05D2260/20 , F05D2260/209 , F05D2260/601 , F05D2260/607 , Y02T50/60
Abstract: An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.
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公开(公告)号：US11815020B2
公开(公告)日：2023-11-14
申请号：US17813745
申请日：2022-07-20
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Gabriel Naccache , Christopher Gover , Alexander Smith , Alain Martel , Matthieu Boudreau
CPC classification number: F02C7/12 , F01D5/081 , F01D5/082 , F02C7/22 , F05D2220/32 , F05D2240/35 , F05D2240/55
Abstract: A tangential on-board injector (TOBI), comprising: a body defining an annular passageway to receive cooling air, the TOBI defining a plurality of discharge nozzles; a rotating component mounted for rotation relative to the body about an axis of rotation; a seal extending between the body and the rotating component; a plurality of vanes circumferentially distributed about the axis of rotation and located downstream of the plurality of discharge nozzles relative to a flow of the cooling air circulating toward the seal from the plurality of discharge nozzles and upstream of the seal; and flow passages defined between the plurality of vanes, a flow passage of the flow passages extending along a passage axis, the passage axis having a tangential component at an outlet of the flow passage that is different than a tangential component of an exit flow axis of a nozzle of the plurality of discharge nozzles.
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公开(公告)号：US11719116B2
公开(公告)日：2023-08-08
申请号：US17827205
申请日：2022-05-27
Inventor： Shogo Iwai , Takahiro Ono
IPC: F01D11/24 , F01D5/08 , F02C7/18 , F16K31/00 , G05D23/02 , F01D5/18 , F01D25/12 , F02C9/20 , F16K25/00
CPC classification number: F01D11/24 , F01D5/081 , F02C7/18 , F16K31/002 , G05D23/025 , F01D5/082 , F01D5/084 , F01D5/187 , F01D25/12 , F02C9/20 , F16K25/005 , G05D23/02 , G05D23/022 , G05D23/024 , Y10T137/7737
Abstract: There are provided a throttle mechanism and the like that are capable of easily changing a cross-sectional area of a flow path according to an operating state. The throttle mechanism in an embodiment is a throttle mechanism that controls a flow rate of a fluid flowing through a flow path, and is configured to make a cross-sectional area of the flow path change autonomously according to temperature.
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公开(公告)号：US11668195B2
公开(公告)日：2023-06-06
申请号：US17149762
申请日：2021-01-15
Applicant: DOOSAN ENERBILITY CO., LTD.
Inventor： Herbert Brandl , Willy H. Hofmann , Joerg Krueckels , Ulrich Rathmann , Seok Beom Kim
CPC classification number: F01D5/082 , F01D5/081 , F01D5/143 , F01D5/145 , F01D5/186 , F01D5/187 , F05D2240/81 , F05D2250/192 , F05D2260/20 , F05D2260/201 , F05D2260/202 , F05D2260/205
Abstract: The present technique presents a gas turbine blade for re-using cooling air, a turbomachine assembly having the blade, and a gas turbine having the turbomachine assembly. The blade includes a platform and an airfoil extending from the platform. The airfoil includes a pressure surface, a suction surface, a leading edge and a trailing edge. The platform includes a pressure side, a suction side, a leading-edge side and a trailing-edge side, disposed towards the pressure surface, the suction surface, the leading edge and the trailing edge of the airfoil, respectively. The suction side of the platform includes a part of the upper surface and a suction-side lateral surface of the platform. At least a part of an edge between the suction-side lateral surface and the upper surface of the platform comprises a chamfer part.
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公开(公告)号：US20190242407A1
公开(公告)日：2019-08-08
申请号：US15890866
申请日：2018-02-07
Applicant: United Technologies Corporation
CPC classification number: F04D29/584 , F01D5/082 , F01D5/085 , F01D25/125 , F02C3/04 , F04D19/02 , F04D29/102 , F05D2220/323 , F05D2240/20 , F05D2260/205
Abstract: A high pressure compressor rotor stack includes a bore basket that includes a bore basket internal passage. A first plurality of rotor stages at least partially defines a forward rotor bore with a forward hub structure and the bore basket. A second plurality of rotor stages at least partially defines an aft rotor bore with an aft hub structure and the bore basket.
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公开(公告)号：US09896939B2
公开(公告)日：2018-02-20
申请号：US14656230
申请日：2015-03-12
Applicant: United Technologies Corporation
Inventor： Alberto A. Mateo , Anthony P. Cherolis
CPC classification number: F01D5/08 , F01D5/081 , F01D5/082 , F01D5/085 , F01D5/087 , F01D5/088 , F01D9/02 , F01D25/08 , F01D25/12 , F01D25/162 , F02C7/18 , F05D2220/32 , F05D2260/14 , F05D2260/202 , F05D2260/209 , F05D2260/2212 , F05D2270/3062 , Y02T50/676
Abstract: A swirler tube is disclosed. A swirler is provided comprising a flange defining a first surface, a tube extending away from the first surface, a flow surface defined by a flange inner surface and a tube inner surface, the flange inner surface having an inlet diameter, and a metering feature disposed on the flow surface, wherein the metering feature is integral to the tube, the metering feature have a metering feature diameter that is less than the inlet diameter.
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公开(公告)号：US09879603B2
公开(公告)日：2018-01-30
申请号：US14458593
申请日：2014-08-13
Applicant: ROLLS-ROYCE PLC
Inventor： Alan Robert Maguire , Timothy John Scanlon , Colin Young
IPC: F02C7/18 , F01D5/08 , F02C6/08 , F01D5/04 , F01D9/06 , F01D25/08 , F02C7/12 , F01D25/12 , F02C3/00
CPC classification number: F02C7/18 , F01D5/046 , F01D5/08 , F01D5/081 , F01D5/082 , F01D9/06 , F01D25/08 , F01D25/12 , F02C3/00 , F02C6/08 , F02C7/12 , F05D2220/32 , F05D2260/20 , F05D2260/205 , Y02T50/676
Abstract: This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.
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公开(公告)号：US09879543B2
公开(公告)日：2018-01-30
申请号：US12502727
申请日：2009-07-14
Applicant: James W. Norris , James D. Hill
Inventor： James W. Norris , James D. Hill
CPC classification number: F01D5/18 , F01D5/082 , F01D5/181 , F01D5/187 , F01D5/3007 , F05D2260/202 , F05D2260/205 , F05D2260/207 , F05D2260/22141
Abstract: A cooling system for cooling a fluid reaction apparatus of a gas turbine engine includes a vapor cooling subsystem and a film cooling subsystem. The vapor cooling subsystem has a vaporization section and a condenser section for cooling a portion of the fluid reaction apparatus. The condenser section is cooled by a fluid. The film cooling subsystem is configured for cooling a portion of the fluid reaction apparatus by discharging fluid out of openings defined in the fluid reaction apparatus. At least a portion of the fluid used to cool the condenser section of the vapor cooling subsystem is discharged out of the openings of the film cooling subsystem.
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公开(公告)号：US20170370224A1
公开(公告)日：2017-12-28
申请号：US15190494
申请日：2016-06-23
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Julian Partyka , Raymond S. Hummel
CPC classification number: F01D5/027 , F01D5/026 , F01D5/066 , F01D5/082 , F01D11/006 , F02C3/04 , F02C7/28 , F05D2220/32 , F05D2240/55 , F05D2260/4031
Abstract: A rotor disc assembly includes a rotor disc and a minidisc. The rotor disc has a first extension member, a first finger, and a second finger. The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion and a second portion that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger that radially extends from a minidisc body and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove.
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公开(公告)号：US09816963B2
公开(公告)日：2017-11-14
申请号：US14141873
申请日：2013-12-27
Inventor： Daniel K. Vetters , Simon Mizzi , Michael J. Agg
CPC classification number: G01N29/022 , F01D5/082 , F02C7/18 , F04D19/02 , F04D29/053 , F04D29/584 , F05D2240/12 , F05D2250/232 , G01N2291/0423 , Y02T50/671 , Y02T50/673 , Y02T50/676 , Y10T29/49229
Abstract: A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.
