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公开(公告)号：US09874111B2
公开(公告)日：2018-01-23
申请号：US14477964
申请日：2014-09-05
Applicant: United Technologies Corporation
Inventor： Michael S. Stevens , Ken F. Blaney
CPC classification number: F01D25/243 , F01D9/041 , F01D25/08 , F01D25/246 , Y02T50/671
Abstract: A gas turbine engine includes a tangential on-board injector (TOBI) fluidly connected to a compressor section. A diffuser case structurally supports a combustor section and the tangential on-board injector via at least one low thermal mass joint.
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公开(公告)号：US20170107841A1
公开(公告)日：2017-04-20
申请号：US14885278
申请日：2015-10-16
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov , Paul M. Lutjen , Kevin J. Ryan , Ken F. Blaney
CPC classification number: F01D11/08 , F01D11/02 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2250/314 , F05D2260/20 , F16J15/44 , Y02T50/675
Abstract: According to various embodiments, disclosed is a blade outer air seal assembly for a turbine engine comprising a main body portion that extends generally axially, with respect to a central axis of the turbine engine, from a leading edge portion of the main body to a trailing edge portion of the main body, wherein the leading edge portion includes a leading edge wall having a undercut profile along at least a portion of the leading edge wall, wherein the main body portion comprises cooling passages comprising a leading edge cooling passage adjacent to the leading edge wall, having a leading edge periphery on a side of the leading edge cooling passage adjacent to the leading edge wall, which generally conforms to the undercut profile of the leading edge wall.
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43.发明申请SELF-PUMPING FUEL INJECTOR FOR A GAS TURBINE ENGINE AND METHOD OF OPERATION 审中-公开用于燃气涡轮发动机的自吸式燃料喷射器和操作方法公开(公告)号：US20160327274A1
公开(公告)日：2016-11-10
申请号：US15105381
申请日：2014-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ken F. Blaney , Stephen K. Kramer
CPC classification number: F23R3/28 , F02C3/04 , F02C7/22 , F02C7/236 , F05D2250/25 , F05D2260/85 , F23D11/26 , F23K5/04 , F23K5/142
Abstract: A self-pumping fuel injector includes a pump and a motor for, in-part, delivering fuel to a combustor at higher fuel pressures during start-up and ramping-up conditions. Each pump may include a stationary flow interuptor that intermittently and variably supplies fuel to a rotating spindle that, in-turn, expels the fuel into a nozzle of the injector for improve fuel spray distributions.
Abstract translation: 自抽式燃料喷射器包括泵和电动机，其部分地在启动和升高状态期间以更高的燃料压力向燃烧器输送燃料。 每个泵可以包括固定的流动中继器，其间歇地且可变地向旋转的主轴供应燃料，这反过来将燃料排出到喷射器的喷嘴中，以改善燃料喷雾分布。
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公开(公告)号：US20150300195A1
公开(公告)日：2015-10-22
申请号：US14789232
申请日：2015-07-01
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Shawn J. Gregg , Thurman Carlo Dabbs , Ken F. Blaney , Russell E. Keene , Bruce E. Chick
CPC classification number: F01D11/08 , F01D1/02 , F01D11/24 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2260/20 , F05D2260/201 , F05D2260/205 , F05D2260/2212 , F05D2260/2214
Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.
Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封件包括壁，前钩和后钩。 该壁在前钩和后钩之间延伸，其适于将叶片外部空气密封件安装到燃气涡轮发动机的壳体上。 壁包括沿壁的至少一部分延伸的芯通道。 芯通道径向和轴向地延伸穿过后钩的一部分，以沿着后钩的后缘与一个或多个孔连通。
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公开(公告)号：US20140083099A1
公开(公告)日：2014-03-27
申请号：US13623888
申请日：2012-09-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ken F. Blaney , Neil L. Tatman
CPC classification number: F01D9/042 , F01D9/04 , F01D11/005 , F01D25/24 , Y10T29/49826
Abstract: A compressor case assembly according to an exemplary embodiment of this disclosure, among other possible things, includes a case. A plurality of vane stages circumscribe an interior of the case. Each of the plurality of vane stages include a vane guide and at least one window for inserting a respective at least one vane there through. The at least one window is axially aligned with each of the vane guides The at least one window extends from an outer surface of the case into each of the vane guides.
Abstract translation: 根据本公开的示例性实施例的压缩机壳体组件以及其他可能的事情包括壳体。 多个叶片台围绕壳体的内部。 多个叶片级中的每一个包括叶片引导件和用于在其中插入相应的至少一个叶片的至少一个窗口。 至少一个窗口与每个叶片引导件轴向对齐。至少一个窗口从壳体的外表面延伸到每个叶片引导件中。
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Patent Agency Ranking
公开(公告)号：US11073037B2
公开(公告)日：2021-07-27
申请号：US16516920
申请日：2019-07-19
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark
IPC: F01D11/08
Abstract: A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a support structure via a carrier. At least one of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. The first and second walls extend at an angle less than 90° from the base portion. The carrier has a flat portion that extends from the first wall to the second wall.
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公开(公告)号：US11073036B2
公开(公告)日：2021-07-27
申请号：US16429694
申请日：2019-06-03
Applicant: United Technologies Corporation
Inventor： Matthew James Bennison , Paul M. Lutjen , Ken F. Blaney
Abstract: A gas turbine engine component includes a main body. A cooling passage is within the main body. The cooling passage is defined by a first wall opposite a second wall. The cooling passage has an inlet on the second wall. A protrusion is formed on the first wall arranged across from the inlet.
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公开(公告)号：US10961866B2
公开(公告)日：2021-03-30
申请号：US16042066
申请日：2018-07-23
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark
Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a central chamber within the attachment block, and communicates with cooling holes through a radially inner face of the attachment block to direct cooling air at the central web of the blade outer air seal. A blade outer air seal is also disclosed.
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公开(公告)号：US10920600B2
公开(公告)日：2021-02-16
申请号：US16122553
申请日：2018-09-05
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Paul M. Lutjen , Thomas E. Clark
IPC: F01D11/08
Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The blade outer air seal has a lip at an axial end engaged with the support structure. A seal structure has a seal portion and a wear liner portion joined by a radially extending portion. The seal portion is radially outward of the lip and the wear liner is radially inward of the lip.
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公开(公告)号：US10648407B2
公开(公告)日：2020-05-12
申请号：US16122431
申请日：2018-09-05
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark
Abstract: A turbine section for a gas turbine engine includes a turbine blade that extends radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is mounted in a support structure and is arranged radially outward of the outer tip. A flow guide is arranged between the support structure and the blade outer air seal and defines a passage between the flow guide and the blade outer air seal. The passage is configured to communicate air in a generally axial direction.
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