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公开(公告)号：US20150016954A1
公开(公告)日：2015-01-15
申请号：US14504719
申请日：2014-10-02
Applicant: United Technologies Corporation
Inventor： Anne-Marie B. Thibodeau , Bruce E. Chick , Thurman Carlo Dabbs , James N. Knapp , Dmitriy A. Romanov , Russell E. Keene , Jeffrey Vincent Anastas
CPC classification number: F01D25/246 , F01D11/08 , F01D11/125 , F05D2240/11 , F05D2260/202
Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.
Abstract translation: 叶片外部空气密封支撑组件包括构造成支撑叶片外部空气密封件的主支撑构件。 主支撑构件在前缘部分和后缘部分之间大致轴向地延伸。 前缘部分构造成可滑动地容纳在由叶片外部空气密封件建立的凹槽内。 支撑翼片从主支撑构件朝向叶片外部空气密封件径向向内延伸。 所述支撑突出部构造成接触所述叶片外部空气密封件的延伸部以限制所述叶片外部空气密封件的相对轴向运动。 角撑板跨越支撑片和主支撑件之间。
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公开(公告)号：US20170292393A1
公开(公告)日：2017-10-12
申请号：US15094603
申请日：2016-04-08
Applicant: United Technologies Corporation
Inventor： Jeffrey Vincent Anastas , Michael S. Stevens
CPC classification number: F01D9/048 , F01D5/082 , F01D9/041 , F05D2220/32 , F05D2230/20 , F05D2240/126 , F05D2240/128 , F05D2260/20
Abstract: A TOBI for a gas turbine engine having a TOBI body, a first TOBI airfoil having a radially extending portion extending from a leading edge and an axially extending portion extending toward a trailing edge, and a second TOBI airfoil circumferentially adjacent to the first TOBI airfoil, the second TOBI airfoil having a radially extending portion extending from a leading edge and an axially extending portion extending toward a trailing edge. An entrance is defined between the leading edges of the adjacent TOBI airfoils and an exit is defined between the trailing edges of the TOBI airfoils, wherein airflow entering the entrance enters in a radial direction relative to the TOBI body and airflow exiting the exit exits in a circumferential direction relative to the TOBI body.
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公开(公告)号：US11459905B2
公开(公告)日：2022-10-04
申请号：US16665500
申请日：2019-10-28
Applicant: United Technologies Corporation
Inventor： Michael S. Stevens , Jeffrey Vincent Anastas
IPC: B23P15/00 , B28B1/00 , B33Y10/00 , B33Y40/20 , B22F5/00 , F01D11/00 , F01D11/12 , B22F10/20 , B33Y80/00
Abstract: A method of making a component includes creating a computer file defining the component in layers, the component including: a body including a sealing portion; and an abradable seal extending from the sealing portion; and building the component using an additive manufacturing process that builds the component on a layer-by-layer basis such that the abradable seal is integral to the body.
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Patent Agency Ranking
公开(公告)号：US20160208926A1
公开(公告)日：2016-07-21
申请号：US15022838
申请日：2014-07-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Timothy M. Davis , Jeffrey Vincent Anastas
CPC classification number: F16J15/3496 , F01D9/02 , F01D11/001 , F01D11/003 , F01D11/08 , F01D11/12 , F01D11/122 , F01D11/125 , F01D11/127 , F01D11/22 , F02C7/28 , F05D2220/32 , F05D2240/55 , F05D2250/283 , F16J15/3464 , F16J15/444
Abstract: A seal assembly includes an annular carrier defining a radially inward face, and an opposed radially outward face defining a plurality of spline slots. The spline slots are configured and adapted to receive corresponding spline tabs to center the carrier in a surrounding structure. A honeycomb seal is mounted to the radially inward face of the carrier. The honeycomb seal is configured for sealing engagement with a knife-edge seal rotating relative to the honeycomb seal. The seal assembly has a relatively low coefficient of thermal expansion in comparison to the static component or the knife-edge seal. For example, a gas turbine engine can include a seal assembly as described above, wherein the carrier is mounted to a static component and a rotor mounted for rotation relative to the carrier, and wherein the rotor includes the knife edge seal component sealingly engaged to the honeycomb seal.
Abstract translation: 密封组件包括限定径向内表面的环形载体和限定多个花键槽的相对的径向向外的面。 花键槽被配置并适于接收相应的花键突片，以使载体在周围的结构中居中。 蜂窝密封件安装在载体的径向向内的表面上。 蜂窝状密封件构造成与相对于蜂窝密封件旋转的刀刃密封件密封接合。 与静态部件或刀刃密封件相比，密封组件具有相对低的热膨胀系数。 例如，燃气涡轮发动机可以包括如上所述的密封组件，其中载体被安装到静止部件和安装成相对于载体旋转的转子，并且其中转子包括密封地接合到 蜂窝密封。
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公开(公告)号：US20200063594A1
公开(公告)日：2020-02-27
申请号：US16665500
申请日：2019-10-28
Applicant: United Technologies Corporation
Inventor： Michael S. Stevens , Jeffrey Vincent Anastas
Abstract: A method of making a component includes creating a computer file defining the component in layers, the component including: a body including a sealing portion; and an abradable seal extending from the sealing portion; and building the component using an additive manufacturing process that builds the component on a layer-by-layer basis such that the abradable seal is integral to the body.
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公开(公告)号：US10077680B2
公开(公告)日：2018-09-18
申请号：US14504719
申请日：2014-10-02
Applicant: United Technologies Corporation
Inventor： Anne-Marie B. Thibodeau , Bruce E. Chick , Thurman Carlo Dabbs , James N. Knapp , Dmitriy A. Romanov , Russell E. Keene , Jeffrey Vincent Anastas
CPC classification number: F01D25/246 , F01D11/08 , F01D11/125 , F05D2240/11 , F05D2260/202
Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.
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公开(公告)号：US09957897B2
公开(公告)日：2018-05-01
申请号：US14662581
申请日：2015-03-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas E. Clark , Jeffrey Vincent Anastas
CPC classification number: F02C7/22 , F01D5/081 , F01D9/06 , F02C7/18 , F05D2220/32 , F05D2230/60 , F05D2240/10 , F05D2240/81 , F05D2260/30 , Y02T50/676
Abstract: A gimbal tube system for an onboard injector (OBI) includes a transfer tube having a first transfer tube end that can be mounted to an inner diameter of a stator platform and a second transfer tube end defining a transfer tube pivot connector. The system also includes a gimbal tube including a first gimbal tube end that defines a gimbal tube pivot connector that can movably mount to the transfer tube pivot connector such that the gimbal tube and the transfer tube can move relative to each other at a pivot joint defined between the transfer tube and the gimbal tube. The gimbal tube further includes a second gimbal tube end defining a nozzle that can be inserted into the OBI.
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公开(公告)号：US20170089213A1
公开(公告)日：2017-03-30
申请号：US14867850
申请日：2015-09-28
Applicant: United Technologies Corporation
Inventor： Michael S. Stevens , Jeffrey Vincent Anastas
CPC classification number: F01D11/122 , B22F3/1055 , B22F5/009 , B23P15/00 , B28B1/001 , B33Y10/00 , B33Y80/00 , F01D11/001 , F01D11/127 , F05D2230/22 , F05D2250/283 , Y02P10/295
Abstract: A method of making a component includes creating a computer file defining the component in layers, the component including: a body including a sealing portion; and an abradable seal extending from the sealing portion; and building the component using an additive manufacturing process that builds the component on a layer-by-layer basis such that the abradable seal is integral to the body.
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