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公开(公告)号：US20140090391A1
公开(公告)日：2014-04-03
申请号：US14039913
申请日：2013-09-27
Applicant: United Technologies Corporation
Inventor： Steven W. Burd
IPC: F23R3/28
Abstract: A combustor for a gas turbine engine includes an forward fuel injection system in communication with a combustion chamber and a downstream fuel injection system that communicates with the combustion chamber downstream of the forward fuel injection system.
Abstract translation: 用于燃气涡轮发动机的燃烧器包括与燃烧室连通的前向燃料喷射系统和与前向燃料喷射系统下游的燃烧室连通的下游燃料喷射系统。
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公开(公告)号：US11143030B2
公开(公告)日：2021-10-12
申请号：US13725229
申请日：2012-12-21
Applicant: United Technologies Corporation
Inventor： Steven W. Burd , Alan C. Barron
Abstract: A method of coating a component having a multiple of cooling holes includes removing at least a portion of a prior coating; directing a gas through at least one of the multiple of cooling holes; and applying a coat layer while directing the gas through at least one of the
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公开(公告)号：US10935235B2
公开(公告)日：2021-03-02
申请号：US15348568
申请日：2016-11-10
Applicant: United Technologies Corporation
Inventor： Steven W. Burd
IPC: F23R3/42 , F23R3/06 , F23R3/50 , F23M5/02 , F23R3/60 , F23M5/04 , F23R3/00 , F01D9/02 , F23M5/08
Abstract: A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a forward section and an aft section that defines an angle therebetween in the axial profile between the forward section and the aft section.
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公开(公告)号：US10746403B2
公开(公告)日：2020-08-18
申请号：US14939619
申请日：2015-11-12
Applicant: United Technologies Corporation
Inventor： John S. Tu , Steven W. Burd
Abstract: A wall assembly that may be for a combustor of a gas turbine engine includes a liner having a hot face that defines a combustion chamber, an opposite cold face, and a plurality of effusion holes. A shell of the assembly is spaced outward from the cold face and includes a plurality of impingement holes each having a centerline orientated substantially normal to the cold face. A plurality of cooling member arrays of the liner each include a first plurality of members that may be pins projecting outward from the cold face to conduct heat out of the liner. Each array is spaced between adjacent effusion holes and is symmetrically orientated about the respective centerline.
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公开(公告)号：US10704424B2
公开(公告)日：2020-07-07
申请号：US15029525
申请日：2014-09-04
Applicant: United Technologies Corporation
Inventor： Steven W. Burd , Christopher R. Brdar , Derk S. Philippona
Abstract: A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.
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Patent Agency Ranking
公开(公告)号：US10337455B2
公开(公告)日：2019-07-02
申请号：US15105117
申请日：2014-12-12
Applicant: United Technologies Corporation
Inventor： Steven W. Burd
Abstract: The present disclosure relates generally to a system for fan nacelle inlet flow control in a gas turbine engine, the nacelle comprising a nacelle inlet cowl including an inlet lip disposed at a leading edge of the nacelle inlet cowl, an inner surface extending aft from the inlet lip, and an outer surface extending aft from the inlet lip and positioned radially outward of the inner surface; and at least one flow control passage extending through the nacelle inlet cowl, each of the at least one flow control passage including a flow control passage inlet, disposed on the inlet lip, and a flow control passage outlet; wherein air may flow into the flow control passage inlet, through the flow control passage, and exits the flow control passage outlet.
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17.发明授权Assemblies with brazed joints and methods of fabricating assemblies with brazed joints 有权钎焊接头组件和钎焊接头制造组件的方法公开(公告)号：US09511452B2
公开(公告)日：2016-12-06
申请号：US14616842
申请日：2015-02-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher M. Pater , Steven W. Burd , Derk S. Philippona , Robert J. Sayers
CPC classification number: B23K31/02 , B23K1/00 , B23K1/0018 , B23K1/20 , B23K3/08 , B23K33/00 , B23K2101/001
Abstract: An assembly may comprise a first part including a first surface, and a second part including a second surface and a bottom edge having sloped regions and at least one well between the sloped regions. The assembly may further comprise a brazed joint joining the first surface to the second surface. The at least one well may be configured to collect excess braze material from the brazed joint.
Abstract translation: 组件可以包括包括第一表面的第一部分和包括具有倾斜区域的第二表面和底部边缘以及在倾斜区域之间的至少一个井的第二部分。 组件还可以包括将第一表面连接到第二表面的钎焊接头。 所述至少一个孔可以构造成从钎焊接头收集多余的钎焊材料。
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公开(公告)号：US20160237950A1
公开(公告)日：2016-08-18
申请号：US15025374
申请日：2014-08-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven W. Burd
CPC classification number: F02K1/822 , B32B3/00 , B32B3/10 , B32B3/26 , B32B2255/00 , B32B2307/30 , B32B2605/00 , B32B2605/18 , F01D5/18 , F01D5/186 , F01D9/02 , F01D25/12 , F01D25/30 , F05D2220/32 , F05D2230/90 , F05D2250/90 , F05D2260/20 , F23M2900/05004 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03041 , Y02T50/671 , Y02T50/676 , Y02T50/6765
Abstract: A component is provided for a gas turbine engine includes a substrate with an aperture. The component also includes a backside coating on a backside of the substrate and at least partially onto an inner boundary of the aperture, where the backside coating forms a passage with the aperture. A method of forming a shaped aperture in a component of a gas turbine engine is provided. The method includes applying a backside coating on a backside of a substrate and at least partially onto an inner boundary of an aperture. The backside coating forms a passage with the aperture including a convergent section, a divergent section and a throat therebetween.
Abstract translation: 提供了一种用于燃气涡轮发动机的部件，其包括具有孔的基板。 所述部件还包括在所述基板的背面上并且至少部分地位于所述孔的内边界上的背面涂层，其中所述背面涂层与所述孔形成通道。 提供了一种在燃气涡轮发动机的部件中形成成形孔的方法。 该方法包括将背面涂层施加在基底的背面并且至少部分地施加到孔的内边界上。 后侧涂层形成通道，其中孔口包括会聚部分，发散部分和喉部之间。
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公开(公告)号：US20160209033A1
公开(公告)日：2016-07-21
申请号：US14601037
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Steven W. Burd
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R3/06 , F23R3/50 , F23R2900/00005 , F23R2900/00018 , Y02T50/675
Abstract: Aspects of the disclosure are directed to a liner associated with a combustor of an aircraft engine, comprising: a thermal barrier coating, and a base metal, wherein the thermal barrier coating comprises a contoured surface on a flowpath side proximate to an exit of a hole formed by the thermal barrier coating and the base metal.
Abstract translation: 本公开的方面涉及与飞机发动机的燃烧器相关联的衬套，其包括：热障涂层和基底金属，其中所述热障涂层包括靠近孔的出口的流路侧上的轮廓表面 由热障涂层和贱金属形成。
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公开(公告)号：US09376985B2
公开(公告)日：2016-06-28
申请号：US13717203
申请日：2012-12-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven W. Burd
CPC classification number: F02G3/00 , F23R3/14 , F23R3/28 , F23R3/286 , Y02T50/675 , Y10T137/2087
Abstract: A swirler includes an inner shroud positioned radially inside an outer shroud. At least one of the outer shroud and inner shroud has a major diameter and a minor diameter, the major diameter being greater than the minor diameter, the major and minor diameters defining an ovate shape. The swirler further includes a plurality of vanes extending between the inner and outer shrouds.
Abstract translation: 旋流器包括位于外护罩径向内侧的内护罩。 外护罩和内护罩中的至少一个具有大直径和小直径，主直径大于小直径，主直径和次直径限定卵形。 旋流器还包括在内护罩和外护罩之间延伸的多个叶片。
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