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公开(公告)号：US20190226500A1
公开(公告)日：2019-07-25
申请号：US16367673
申请日：2019-03-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： JinQuan Xu , Frederic Tisdall Tenney
Abstract: A stage of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a row of flow directing components circumferentially disposed about a centerline axis and at least one flow directing component of the row having at least one design characteristic that is dissimilar from a corresponding design characteristic of at least one other flow directing component of the row.
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公开(公告)号：US10302100B2
公开(公告)日：2019-05-28
申请号：US14767602
申请日：2014-02-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： JinQuan Xu , Frederic Tisdall Tenney
Abstract: A stage of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a row of flow directing components circumferentially disposed about a centerline axis and at least one flow directing component of the row having at least one design characteristic that is dissimilar from a corresponding design characteristic of at least one other flow directing component of the row.
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公开(公告)号：US20180304345A1
公开(公告)日：2018-10-25
申请号：US16017114
申请日：2018-06-25
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Mark F. Zelesky , JinQuan Xu , Joel H. Wagner
IPC: B22C9/10 , F01D5/18 , F01D9/04 , F01D25/12 , B29C64/153 , B22C1/00 , B22C1/18 , B22F5/00 , B22D29/00 , B22F3/105 , B28B7/34 , B28B1/00 , B22F5/04 , B33Y80/00 , B33Y10/00
CPC classification number: B22C9/10 , B22C1/00 , B22C1/181 , B22C9/106 , B22D29/002 , B22F3/1055 , B22F5/009 , B22F5/04 , B28B1/001 , B28B7/346 , B29C64/153 , B33Y10/00 , B33Y80/00 , F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/21 , F05D2240/12 , F05D2240/30 , F05D2300/13 , F05D2300/16 , Y02P10/292 , Y02P10/295
Abstract: A method of preparing a casting article for manufacturing a gas turbine engine part according to an exemplary aspect of the present disclosure includes communicating a powdered material to an additive manufacturing system, the powdered material including at least one of a silica material, an alumina material, and a refractory metal material. The method includes using the additive manufacturing system to manufacture a casting article layer by layer, the casting article including a plurality of circuit forming portions, at least one of the circuit forming portions including an interior channel that establishes a hollow opening through the circuit forming portion.
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公开(公告)号：US20180135741A1
公开(公告)日：2018-05-17
申请号：US15350754
申请日：2016-11-14
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
CPC classification number: F16H57/0443 , B64D37/22 , F01D25/20 , F01M11/067 , F16H57/045 , F16N17/00 , F16N19/00 , F16N2210/09
Abstract: Aspects of the disclosure are directed to a system comprising: a tank that stores a fluid, and a conduit that includes a first end and a second end, where the conduit is configured to convey at least a portion of the fluid stored in the tank from the second end of the conduit to the first end of the conduit, where a first end region of the conduit coinciding with the second end of the conduit has a first end region density and the fluid has a fluid density, where the first end region density is greater than or equal to the fluid density such that the first end region of the conduit remains immersed in the fluid stored in the tank when the fluid in the tank is under negative gravity conditions.
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公开(公告)号：US09909673B2
公开(公告)日：2018-03-06
申请号：US14724413
申请日：2015-05-28
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
Abstract: A fluid supply system for providing a turbomachine fluid to a component of a gas turbine engine is disclosed. The fluid supply system includes a fluid container, a moveable barrier, and an airbag. The moveable barrier fluidly divides the fluid container into a first portion and a second portion. The moveable barrier is moveable between a flow-permitting position and a flow-restricting position. The turbomachine fluid experiences a circulating flow between the component and the second portion of fluid container when the moveable barrier is in the flow-permitting position. The circulating flow is at least partially impeded by the moveable barrier when the moveable barrier is in the flow-restricting position. The airbag is positioned within the first portion of the fluid container. The airbag is selectively operable to move the moveable barrier from the flow-permitting position to the flow-restricting position.
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Patent Agency Ranking
公开(公告)号：US09869186B2
公开(公告)日：2018-01-16
申请号：US15243220
申请日：2016-08-22
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
IPC: F01D5/18 , F02C3/04 , F04D29/58 , F04D29/54 , F04D29/32 , F04D29/52 , F01D9/04 , F01D25/24 , F01D25/30 , F01D25/12 , F23R3/00
CPC classification number: F01D5/187 , F01D5/186 , F01D9/041 , F01D9/065 , F01D25/12 , F01D25/24 , F01D25/30 , F02C3/04 , F04D29/324 , F04D29/522 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/70 , F05D2250/71 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676
Abstract: A component for a gas turbine engine including a gas path wall having a first surface and a second surface. A cooling hole extends through the gas path wall from an inlet in the first surface through a transition to an outlet in the second surface. Cusps are formed on the transition.
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公开(公告)号：US20170363004A1
公开(公告)日：2017-12-21
申请号：US15187149
申请日：2016-06-20
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
CPC classification number: F02C7/12 , F02C7/14 , F02C7/222 , F02C7/224 , F05D2220/32 , F05D2240/35 , F05D2260/208 , F23D11/36 , F23D2214/00 , F23R3/283 , F23R3/30 , F23R3/346 , F23R3/42 , F28D15/02 , F28D15/04 , F28D2021/0024 , F28D2021/0026
Abstract: Fuel injectors for gas turbine engines are provided herein. The fuel injectors include a nozzle configured to dispense fuel into a combustor of a gas turbine engine, a fuel conduit fluidly connecting a fuel source to the nozzle, and a heat pipe having a vaporization section and a condensation section, wherein the vaporization section is in thermal communication with the nozzle and the condensation section is in thermal communication with a cooling source of the gas turbine engine.
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公开(公告)号：US09718127B2
公开(公告)日：2017-08-01
申请号：US15228585
申请日：2016-08-04
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
IPC: B22D23/06 , B22C7/02 , B22D27/04 , B33Y10/00 , B33Y40/00 , B28B1/00 , B33Y70/00 , B33Y80/00 , F01D25/00 , B22F3/105 , B22F5/04 , B22F7/06 , B23K15/00 , B23K26/00 , B23K26/342 , B22D19/10 , B22F5/00 , B23P6/00 , C30B11/00 , C30B21/02 , C22C19/03 , C22C19/07 , C30B29/52 , C22C38/00 , F01D5/00 , F01D5/14 , F01D5/18 , F01D5/28 , F01D5/30 , F01D5/34 , B22C9/24 , B23K101/00 , B23K103/18 , B23K103/00 , B23P15/02 , B22F3/24
CPC classification number: B22D27/045 , B22C9/24 , B22D19/10 , B22F3/1055 , B22F5/007 , B22F5/04 , B22F7/06 , B22F2003/248 , B22F2998/10 , B23K15/0086 , B23K15/0093 , B23K26/0006 , B23K26/342 , B23K2101/001 , B23K2103/18 , B23K2103/52 , B23P6/007 , B23P15/02 , B28B1/001 , B33Y10/00 , B33Y40/00 , B33Y70/00 , B33Y80/00 , C22C19/03 , C22C19/07 , C22C38/00 , C30B11/00 , C30B11/002 , C30B11/003 , C30B21/02 , C30B29/52 , F01D5/005 , F01D5/14 , F01D5/18 , F01D5/186 , F01D5/187 , F01D5/284 , F01D5/3084 , F01D5/34 , F01D25/005 , F05D2220/32 , F05D2230/21 , F05D2230/31 , F05D2230/50 , F05D2240/10 , F05D2240/24 , F05D2300/10 , F05D2300/175 , F05D2300/20 , F05D2300/21 , F05D2300/22 , F05D2300/222 , F05D2300/6033 , F05D2300/607 , F05D2300/609 , Y02P10/292 , Y02P10/295
Abstract: A method of manufacturing a component includes additively manufacturing a crucible; directionally solidifying a metal material within the crucible; and removing the crucible to reveal the component. A component for a gas turbine engine includes a directionally solidified metal material component, the directionally solidified metal material component having been additively manufactured of a metal material concurrently with a core, the metal material having been remelted and directionally solidified.
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公开(公告)号：US20170081958A1
公开(公告)日：2017-03-23
申请号：US14942025
申请日：2015-11-16
Applicant: United Technologies Corporation
Inventor： JinQuan Xu , Scott D. Lewis
CPC classification number: F01D5/186 , F01D5/187 , F01D9/065 , F05D2220/32 , F05D2250/25 , F05D2250/314 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. The plurality of crossover passages are arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity.
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公开(公告)号：US09598967B2
公开(公告)日：2017-03-21
申请号：US13718181
申请日：2012-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： JinQuan Xu
CPC classification number: F01D5/30 , F01D5/143 , F01D5/145 , F01D5/282 , F01D5/284 , F01D5/3084 , F01D5/3092 , F05D2240/80 , F05D2300/603 , Y02T50/672 , Y02T50/673 , Y10T29/49316
Abstract: An airfoil member and platform assembly for a gas turbine engine is provided. The platform to which the airfoil member is anchored is made of a composite material and includes an endwall defining a contoured region for improved aerodynamics. The contoured region influences the flow of gases through the flow passages between the airfoil members, thereby reducing endwall losses due to horseshoe vortexing. The composite material may be woven ceramic matrix composite fibers infiltrated with a ceramic matrix material or woven organic matrix composite fibers infiltrated with an organic matrix material.
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