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公开(公告)号:US11346282B2
公开(公告)日:2022-05-31
申请号:US16251492
申请日:2019-01-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Ramons A. Reba , Bruce L. Morin , Daniel L. Gysling , Carson A. Roy Thill , Jose R. Paulino , JinQuan Xu , Stephen A. Morford
Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.
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公开(公告)号:US10746033B2
公开(公告)日:2020-08-18
申请号:US15982396
申请日:2018-05-17
Applicant: United Technologies Corporation
Inventor: Brandon W. Spangler , Jose R. Paulino
Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform includes a radially outer surface that is attached to the radially inner end of the airfoil. A radially inner side of the platform includes a forward surface and an aft surface. A pocket is recessed into at least one of the forward surface and the aft surface. A cover plate covers the pocket and a seal is attached to the cover plate.
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公开(公告)号:US10428953B2
公开(公告)日:2019-10-01
申请号:US15053613
申请日:2016-02-25
Applicant: United Technologies Corporation
Inventor: Paul M. Lutjen , Jose R. Paulino
IPC: F16J15/3288 , F01D11/00 , F01D11/08 , F04D29/08 , F16J15/328
Abstract: Aspects of the disclosure are directed to a brush seal assembly, comprising a compressible core, at least one wire wound around the core, and a backing plate that is substantially ‘c’ shaped or ‘u’ shaped that at least partially encases the at least one wire. Aspects of the disclosure are directed to a method comprising separating compressible cores with a spacer, winding wires around the cores and the spacer, and forming substantially ‘c’ shaped or ‘u’ shaped backings about the wires to obtain a package of brush seal assemblies.
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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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15.
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:US20160040548A1
公开(公告)日:2016-02-11
申请号:US14812668
申请日:2015-07-29
Applicant: United Technologies Corporation
Inventor: Jose R. Paulino , Christopher W. Strock
CPC classification number: C23C4/12 , F01D11/122 , F05D2230/90 , F05D2240/11 , F05D2300/20
Abstract: A gas turbine engine article includes a substrate and a bond coating that covers at least a portion of the substrate with a step formed in at least one of the substrate and the bond coating. A thermally insulating topcoat is disposed on the bond coating. The thermally insulating topcoat includes a first topcoat portion separated by at least one fault that extends through the thermally insulating topcoat from a second topcoat portion.
Abstract translation: 一种燃气涡轮发动机制品包括基材和粘合涂层,其覆盖基材的至少一部分,所述台阶形成在基材和粘结涂层中的至少一个中。 绝缘面漆设在接合涂层上。 绝热顶涂层包括由至少一个断层隔开的第一顶涂层部分,其从第二顶涂层部分延伸穿过绝热顶涂层。
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公开(公告)号:US11384841B2
公开(公告)日:2022-07-12
申请号:US16706183
申请日:2019-12-06
Applicant: United Technologies Corporation
Inventor: Jose R. Paulino , Neil L. Tatman , Paul J. Burgess
IPC: F16J15/3288
Abstract: A seal joint assembly is provided that includes a stationary seal carrier, a stationary seal land and a brush seal. The stationary seal land includes a seal land surface. The brush seal is mounted to the stationary seal carrier. The brush seal includes a first set of bristles and a second set of bristles. The first set of bristles includes a first bristle that contacts the seal land surface. The second set of bristles includes a second bristle that contacts the seal land surface. The second bristle crosses the first bristle.
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公开(公告)号:US20200232390A1
公开(公告)日:2020-07-23
申请号:US16251492
申请日:2019-01-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Ramons A. Reba , Bruce L. Morin , Daniel L. Gysling , Carson A. Roy Thill , Jose R. Paulino , JinQuan Xu , Stephen A. Morford
Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.
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公开(公告)号:US20190195080A1
公开(公告)日:2019-06-27
申请号:US16289784
申请日:2019-03-01
Applicant: United Technologies Corporation
Inventor: Jose R. Paulino , Christopher W. Strock
CPC classification number: F01D11/08 , B33Y10/00 , B33Y80/00 , C23C4/02 , F05D2220/32 , F05D2240/55 , F05D2300/502
Abstract: A gas turbine engine article includes a substrate that has at least one step, and the step includes an undercut. A thermally insulating topcoat is disposed on the substrate. The thermally insulating topcoat includes at least one fault that extends from the step.
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公开(公告)号:US10167957B2
公开(公告)日:2019-01-01
申请号:US15169197
申请日:2016-05-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Timothy M. Davis , Terence P. Tyler, Jr. , Jose R. Paulino , Paul M. Lutjen
Abstract: A metal gasket bellows seal includes a first ply comprised of a first material having a first yield strength. The metal gasket bellows seal also includes a second ply positioned adjacent to the first ply and comprised of a second material having a second yield strength that is less than the first yield strength.
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