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公开(公告)号：US10570744B2
公开(公告)日：2020-02-25
申请号：US15228543
申请日：2016-08-04
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
IPC: B22C9/10 , B22C9/22 , F01D5/18 , C22C19/03 , C22C19/07 , C22C38/00 , B22D25/02 , B22D29/00 , C30B21/02 , C30B11/00 , B22D19/10 , B22D27/04 , B22F3/105 , C30B29/52 , B22C9/02 , B22F5/00 , B22F5/04 , F01D5/14 , F01D5/28 , F01D5/30 , F01D5/34 , B23P6/00 , F01D5/00 , F02M35/10 , F02M21/02 , F04D29/046 , F04D29/056 , B33Y10/00 , B33Y80/00 , B22C9/24 , B22D21/00 , B22D23/06 , B23P15/02 , B22F3/24
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：US20200040982A1
公开(公告)日：2020-02-06
申请号：US16586134
申请日：2019-09-27
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
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：US20200024964A1
公开(公告)日：2020-01-23
申请号：US16239856
申请日：2019-01-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： JinQuan Xu
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface, an outer skin and a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin.
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公开(公告)号：US10458331B2
公开(公告)日：2019-10-29
申请号：US15187149
申请日：2016-06-20
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
IPC: F02C7/22 , F23R3/28 , F01D25/12 , F02C7/14 , F02C7/12 , F23R3/30 , F23R3/42 , F02C7/224 , F23R3/34 , F23D11/36 , F28D15/04 , F28D15/02
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：US20190277501A1
公开(公告)日：2019-09-12
申请号：US15914815
申请日：2018-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： JinQuan Xu
Abstract: A combustion liner for an engine includes a shell having an impingement slot disposed therethrough and a panel having an effusion cooling hole disposed therethrough, the effusion cooling hole offset from the impingement slot and configured to create an impingement floatwall film formed between the panel and a combustion chamber of the engine. A length of the impingement slot is longer than a width of the impingement slot, the length and width configured to create turbulent airflow within a flow channel and minimize particulate matter accumulation. In various embodiments, the length of the impingement slot is at least approximately five or ten times longer than the width.
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Patent Agency Ranking
公开(公告)号：US10307817B2
公开(公告)日：2019-06-04
申请号：US14870443
申请日：2015-09-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Mark F. Zelesky , JinQuan Xu , Joel H. Wagner
IPC: B22C9/10 , B22C9/24 , B22D29/00 , B22F3/105 , B29C67/00 , B22C1/00 , B22C9/02 , F01D5/18 , B22F5/00 , B22F5/04 , B33Y80/00 , B33Y10/00
Abstract: A casting article according to another exemplary aspect of the present disclosure includes, among other things, a circuit forming portion including an interior channel and an outer shell body that surrounds the interior channel. An engineered failure feature is formed in the outer shell body and is configured to increase compressibility of the casting article during a casting process.
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公开(公告)号：US20190085707A1
公开(公告)日：2019-03-21
申请号：US15710874
申请日：2017-09-21
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
CPC classification number: F01D5/186 , F01D5/284 , F01D5/288 , F01D11/08 , F05D2230/13 , F05D2230/90 , F05D2260/202 , F05D2300/20 , F05D2300/516 , F05D2300/6033 , F05D2300/611
Abstract: A gas turbine engine component has an engine component body and at least one hole formed within the engine component body and extends between a hole inlet and a hole outlet. The hole has a first portion with a first roughness and a second portion having a second roughness that is less than the first roughness. The first portion is upstream of the second portion. A gas turbine engine and a method of forming a cooling hole are also disclosed.
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公开(公告)号：US20180299126A1
公开(公告)日：2018-10-18
申请号：US15490089
申请日：2017-04-18
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
Abstract: A combustor section of a turbine engine includes a first liner panel including a first portion and a second portion defining a continuous uninterrupted surface. The second portion extends away from the first portion at an angle in cross-section greater than 180 degrees beginning at an inflection point. A combustor assembly for a turbine engine and a method of assembling a combustor for a turbine engine are also disclosed.
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公开(公告)号：US09879542B2
公开(公告)日：2018-01-30
申请号：US14652651
申请日：2013-02-12
Applicant: United Technologies Corporation
Inventor： JinQuan Xu
CPC classification number: F01D5/147 , F01D5/021 , F01D5/143 , F01D5/145 , F01D9/02 , F01D9/041 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/80 , Y02T50/673
Abstract: A gas turbine engine component includes an airfoil and a platform. The airfoil has a pressure side and an opposite suction side. The platform is connected to the airfoil and has a first curved edge adjacent the suction side and a second curved edge spaced from the pressure side such that more than half of the platform is located to the pressure side. The platform located to the pressure side has a non-axisymmetrical surface contouring.
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公开(公告)号：US20170370228A1
公开(公告)日：2017-12-28
申请号：US15696307
申请日：2017-09-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： JinQuan Xu , James Tilsley Auxier
Abstract: A gas turbine engine component has a component body configured to be positioned within a flow path of a gas turbine engine having an external pressure, and wherein the component body includes at least one internal cavity having an internal pressure. At least one inlet opening is formed in an outer surface of the component body to direct hot exhaust gas flow into the at least one internal cavity, and there is at least one outlet from the internal cavity. The internal pressure is less than an inlet external pressure at the inlet opening and the internal pressure is greater than an outlet external pressure at the outlet opening to controllably ingest hot exhaust gas via the inlet opening and expel the hot exhaust gas via the outlet opening to maintain a laminar boundary layer along the outer surface of the component body.
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