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公开(公告)号：US20160160668A1
公开(公告)日：2016-06-09
申请号：US14930764
申请日：2015-11-03
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Dave J. Hyland , Timothy Dale
CPC classification number: F01D9/04 , F01D9/065 , F01D25/162 , F01D25/24 , F01D25/243 , F02C3/13 , F02C3/14 , F02C6/08 , F02C9/18 , F05D2220/32 , F05D2230/60 , F05D2240/128 , F05D2240/35
Abstract: An inner diffuser case for a gas turbine engine may include a pre-diffuser including a plurality of struts. At least one of the struts may include an aperture therethrough. A cone may have a downstream end coupled to the pre-diffuser downstream of, and proximate to, the aperture. A skirt may have a forward end coupled to the pre-diffuser downstream of, and proximate to, the aperture. The forward end of the skirt may be axially aligned with the downstream end of the cone.
Abstract translation: 用于燃气涡轮发动机的内部扩散器壳体可以包括包括多个支柱的预扩散器。 支柱中的至少一个可以包括穿过其中的孔。 锥体可以具有连接到孔的预扩散器下游并且靠近孔的下游端。 裙部可以具有连接到孔的预扩散器下游并且靠近孔的前端。 裙部的前端可以与锥体的下游端轴向对准。
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公开(公告)号：US10753222B2
公开(公告)日：2020-08-25
申请号：US15700264
申请日：2017-09-11
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Joseph F. Englehart , Christopher Carter Venable , Michael G. McCaffrey
Abstract: A gas turbine engine sealing system includes a case including forward and aft hooks. The aft hook arranged radially outward of the forward hook. A blade outer air seal has a J-hook that receives the aft hook and includes an end received by the forward hook.
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公开(公告)号：US20190078514A1
公开(公告)日：2019-03-14
申请号：US15700328
申请日：2017-09-11
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Joseph F. Englehart , Graham Ryan Philbrick , Henry K. Webster , Richard Seleski , ChaiDee Woods Brown , Michael G. McCaffrey
Abstract: A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.
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公开(公告)号：US10041364B2
公开(公告)日：2018-08-07
申请号：US14930764
申请日：2015-11-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan Jeffery Eastwood , Dave J. Hyland , Timothy Dale
IPC: F01D1/00 , F01D9/04 , F01D9/06 , F01D25/24 , F02C3/13 , F02C6/08 , F01D25/16 , F02C3/14 , F02C9/18
Abstract: An inner diffuser case for a gas turbine engine may include a pre-diffuser including a plurality of struts. At least one of the struts may include an aperture therethrough. A cone may have a downstream end coupled to the pre-diffuser downstream of, and proximate to, the aperture. A skirt may have a forward end coupled to the pre-diffuser downstream of, and proximate to, the aperture. The forward end of the skirt may be axially aligned with the downstream end of the cone.
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公开(公告)号：US20170254538A1
公开(公告)日：2017-09-07
申请号：US15062440
申请日：2016-03-07
Applicant: United Technologies Corporation
Inventor： John S. Tu , James B. Hoke , David Kwoka , Jonathan Jeffery Eastwood
CPC classification number: F23R3/002 , F05D2240/15 , F05D2260/201 , F23M5/00 , F23M5/04 , F23M5/08 , F23M5/085 , F23R3/005 , F23R3/04 , F23R3/06 , F23R2900/00005 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044
Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.
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Patent Agency Ranking
公开(公告)号：US20160186994A1
公开(公告)日：2016-06-30
申请号：US14912175
申请日：2014-08-06
Applicant: UNITED TECHNOLOGIES CORPORATION
CPC classification number: F23M5/085 , F23R3/002 , F23R3/06 , F23R3/60 , F23R2900/03044 , Y02T50/675
Abstract: A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end. A spacing surface is spaced from the boss, and is at an outer position that is inward of the outer end of the boss. The spacing surface spaces the panel from the outer shell. A trough is intermediate the boss and the spacing surface. The trough extends to an outer end which is inward of the outer position of the spacing surface. A gas turbine engine is also disclosed.
Abstract translation: 用于燃气涡轮发动机的燃烧器具有燃烧器外壳。 面板具有面向热的燃烧产物的内表面和围绕特征的凸台，凸台延伸到外端。 间隔表面与凸台间隔开，并且处于位于凸台的外端内侧的外部位置。 间隔表面将面板与外壳隔开。 槽位于凸台和间隔表面之间。 槽延伸到位于间隔表面的外部位置内侧的外端。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US11143032B2
公开(公告)日：2021-10-12
申请号：US16173644
申请日：2018-10-29
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Christopher M. Juh
Abstract: A power turbine rotor locking assembly including a rotor shaft. The assembly also includes an aft rotor stage surrounding the rotor shaft. The assembly further includes a locknut torqued to the rotor shaft. The assembly yet further includes a plurality of torque resistance features located on an aft side of the aft rotor stage. The assembly also includes a tooling fixture having a plurality of corresponding torque resistance features, the corresponding torque resistance features selectively engageable with the torque resistance features of the aft rotor stage to resist circumferential movement during assembly and disassembly of the locknut with the rotor shaft.
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公开(公告)号：US11047575B2
公开(公告)日：2021-06-29
申请号：US16383999
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Jon E. Sobanski , Steven D. Porter
Abstract: A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area. The combustor includes: a shell having a kink; and a kinked heat shield panel in facing spaced relationship with the shell, the kinked heat shield panel including a kink located proximate the kink in the shell, wherein the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface.
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公开(公告)号：US10914187B2
公开(公告)日：2021-02-09
申请号：US15700288
申请日：2017-09-11
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Joseph F. Englehart , Graham Ryan Philbrick , ChaiDee Woods Brown
Abstract: An active clearance control manifold assembly includes multiple arcuate manifold segments each having multiple circumferential channels axially spaced apart from one another. The circumferential channels include cooling holes facing radially inward. A tube at least partially circumscribes and fluidly interconnects the manifold segments.
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公开(公告)号：US20200326072A1
公开(公告)日：2020-10-15
申请号：US16383999
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Jon E. Sobanski , Steven D. Porter
IPC: F23R3/06
Abstract: A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area. The combustor includes: a shell having a kink; and a kinked heat shield panel in facing spaced relationship with the shell, the kinked heat shield panel including a kink located proximate the kink in the shell, wherein the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface.
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