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公开(公告)号：US10794206B2
公开(公告)日：2020-10-06
申请号：US16122525
申请日：2018-09-05
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark
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. A flow guide has a plurality of flow guide segments arranged between the blade outer air seal and the support structure. An intersegment seal is at a circumferential end of at least one of the flow guide segments.
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公开(公告)号：US20200094447A1
公开(公告)日：2020-03-26
申请号：US16139141
申请日：2018-09-24
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark
Abstract: A mandrel for a molding process that includes a first portion that has a first portion outer surface, a first portion inner surface, a first portion first end, and a first portion second end. A thickness of the first portion first end is greater than the first portion second end. A second portion has a second portion outer surface, a second portion inner surface, a second portion first end, and a second portion second end. A thickness of the second portion first end is smaller than the second portion second end. The first portion inner surface engages the second portion inner surface to form a mandrel that has a constant cross-section.
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公开(公告)号：US10557367B2
公开(公告)日：2020-02-11
申请号：US15105220
申请日：2014-12-19
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Richard K. Hayford , Christopher M. Jarochym
Abstract: An example active clearance control system for a gas turbine engine includes an actuator, and a case wall portion defining an aperture configured to receive the actuator. The actuator is configured to move an air seal segment, and the actuator is insertable to an installed position within the aperture through a radially outer side of the case wall portion.
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公开(公告)号：US10443851B2
公开(公告)日：2019-10-15
申请号：US15105381
申请日：2014-12-19
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Stephen K. Kramer
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.
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公开(公告)号：US10352184B2
公开(公告)日：2019-07-16
申请号：US15339581
申请日：2016-10-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jose R. Paulino , Ken F. Blaney , Terence P. Tyler, Jr. , Daniel S. Rogers , Anthony B. Swift , Thomas E. Clark
Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.
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Patent Agency Ranking
公开(公告)号：US10145257B2
公开(公告)日：2018-12-04
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
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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公开(公告)号：US10100667B2
公开(公告)日：2018-10-16
申请号：US14997315
申请日：2016-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony B. Swift , Paul M. Lutjen , Neil L. Tatman , Dominic J. Mongillo, Jr. , Matthew A. Devore , Ken F. Blaney
Abstract: A gas turbine engine component is provided. The gas turbine engine component comprises a main body and a leading edge cooling passage defined within the main body. The main body has a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The leading edge cooling passage comprises an axial flow cooling passage defined within the main body and adjacent to the leading edge wall and has a leading edge periphery that generally conforms to the elongated transition portion of the leading edge wall.
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公开(公告)号：US09879551B2
公开(公告)日：2018-01-30
申请号：US14698284
申请日：2015-04-28
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Richard K. Hayford
CPC classification number: F01D5/26 , F01D5/16 , F01D5/18 , F01D25/06 , F05D2220/32 , F05D2230/211 , F05D2260/96 , F05D2300/1606 , F05D2300/1614 , Y10T29/49341
Abstract: An airfoil includes an airfoil structure defining a damping network that includes a first cavity, a second cavity, a flow passage connecting the first and second cavities. The airfoil further includes a damping material configured to flow through the damping network. A method of forming an airfoil includes forming an airfoil body having a damping network that includes a first cavity, a second cavity, and a flow passage connecting the first and second cavities. The method further includes adding a damping material configured to flow through the damping network.
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公开(公告)号：US20170051624A1
公开(公告)日：2017-02-23
申请号：US15118521
申请日：2015-02-12
Applicant: United Technologies Corporation
Inventor： Dmitriy A. Romanov , Jose R. Paulino , Ken F. Blaney
IPC: F01D11/08
CPC classification number: F01D11/08 , B22C9/10 , B22C9/24 , F01D11/24 , F05D2230/211 , F05D2240/11 , F05D2260/204 , F05D2260/22141 , F05D2300/13 , Y02T50/676
Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets.
Abstract translation: 根据本公开的示例性方面的叶片外部空气密封件尤其包括围绕叶片阵列周向分布的主体。 主体具有多个凹槽，其可以例如改善涡轮机的空气动力学效率。 翅片在多个凹槽的第一凹槽和第二凹槽之间。 翅片从主体径向延伸并且终止于提供一个或多个冷却出口的径向内部翅片面。
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公开(公告)号：US20160201467A1
公开(公告)日：2016-07-14
申请号：US14596152
申请日：2015-01-13
Applicant: United Technologies Corporation
Inventor： Peter J. Milligan , Paul M. Lutjen , Ken F. Blaney , Thurman C. Dabbs , Kevin J. Ryan
CPC classification number: F01D11/24 , F05D2240/11 , F05D2250/74 , Y02T50/673
Abstract: A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 1 herein, wherein the Cartesian coordinates are provided with respect to a point P which is at the center of an arc W and co-planer with a machined surface V. A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 2 herein, wherein the Cartesian coordinates are provided with respect to a point P′ which is at the center of an arc W′ and co-planer with a machined surface V′.
Abstract translation: 用于涡轮机的叶片外部空气密封件（BOAS）可以包括BOAS主体，其包括基本上符合本文表1所示的一组笛卡尔坐标定义的多个冷却孔，其中笛卡尔坐标相对于 点P位于圆弧W的中心并具有加工表面V的共同平面机。用于涡轮机的叶片外部空气密封（BOAS）可以包括BOAS主体，其包括基本上符合设定的多个冷却孔 的笛卡尔坐标，其中相对于位于弧W'中心的点P'提供笛卡尔坐标，并且具有加工表面V'的共刨床。
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