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公开(公告)号：US10428659B2
公开(公告)日：2019-10-01
申请号：US14976041
申请日：2015-12-21
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Matthew A. Devore , Dominic J. Mongillo , Ryan Alan Waite
Abstract: A flowpath component for a gas turbine engine includes a leading edge, a trailing edge connected to the leading edge via a first surface and a second surface, an impingement cavity internal to the flowpath component, the impingement cavity being aligned with one of the leading edge and the trailing edge, a cooling passage extending at least partially through the flowpath component, and a plurality of crossover holes connecting the cooling passage to the impingement cavity. At least one of the crossover holes is aligned normal to an expected direction of fluid flow through the cooling passage and is unaligned with an axial line drawn perpendicular to a stacking line of the flowpath component.
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公开(公告)号：US10018062B2
公开(公告)日：2018-07-10
申请号：US14790589
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： Ryan Alan Waite , Jeffrey Michael Jacques , Benjamin F. Hagan
CPC classification number: F01D9/065 , F01D9/02 , F01D9/06 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2260/20 , F16L9/006 , Y02T50/675
Abstract: What is described is a transfer tube for use with an airfoil of a gas turbine engine coupled to a platform. The transfer tube includes a main body having a first end defining an inlet configured to receive a flow of fluid and a second end defining an outlet for the flow of fluid, the main body having a curved section. The transfer tube also includes a first mating face coupled to the first end of the main body. The transfer tube also includes a second mating face coupled to the second end of the main body. At least one of the first mating face or the second mating face is configured to be coupled to a platform body of the outer diameter platform.
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公开(公告)号：US09845694B2
公开(公告)日：2017-12-19
申请号：US14693359
申请日：2015-04-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Lane Thornton
CPC classification number: F01D9/065 , F01D5/147 , F01D5/186 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/125 , F05D2240/307 , F05D2240/81 , F05D2250/75 , Y02T50/676
Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.
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公开(公告)号：US20160326890A1
公开(公告)日：2016-11-10
申请号：US14707928
申请日：2015-05-08
Applicant: United Technologies Corporation
Inventor： BENJAMIN F. HAGAN , Ryan Alan Waite , Dominic J. Mongillo
CPC classification number: F01D5/189 , F01D5/147 , F01D5/18 , F01D9/065 , F01D25/005 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2230/50 , F05D2230/60 , F05D2260/20 , Y02T50/676
Abstract: A flow splitting baffle for separating a main cooling flow through an inner channel of a component includes a tubular structure defining a tubular cavity and having a longitudinal axis. The flow splitting baffle also includes an inner ring coupled to the tubular structure and extending away from the tubular structure along a plane that is perpendicular to the longitudinal axis. The flow splitting baffle also includes an outer ring parallel to the plane, positioned a first distance from the tubular structure, extending away from the tubular structure and positioned a second distance from the inner ring. The flow splitting baffle also includes a strut perpendicular to the plane, extending from the inner ring to the outer ring and coupled to the inner ring and the outer ring.
Abstract translation: 用于分离通过部件的内部通道的主冷却流的分流挡板包括限定管状空腔并具有纵向轴线的管状结构。 分流挡板还包括联接到管状结构并且沿垂直于纵向轴线的平面远离管状结构延伸的内环。 分流挡板还包括平行于该平面的外环，其与该管状结构隔开第一距离，远离该管状结构延伸并与该内环隔开第二距离。 分流挡板还包括垂直于平面的支柱，从内环延伸到外环并且联接到内环和外环。
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公开(公告)号：US20160312632A1
公开(公告)日：2016-10-27
申请号：US14693359
申请日：2015-04-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Lane Thornton
IPC: F01D9/06
CPC classification number: F01D9/065 , F01D5/147 , F01D5/186 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/125 , F05D2240/307 , F05D2240/81 , F05D2250/75 , Y02T50/676
Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的组件包括除了别的以外的包括径向端部的翼型件，在径向端部处具有出口的第一通道和在径向处具有入口的第二通道 结束。 组件还包括具有至少一个转动腔的盖，该转动腔构造成将从第一通道的出口排出的流体引导到第二通道的入口中。
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Patent Agency Ranking
公开(公告)号：US10316751B2
公开(公告)日：2019-06-11
申请号：US14837398
申请日：2015-08-27
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Ryan Alan Waite
Abstract: a gas turbine engine structure includes a body radially spanning an inner portion and an outer portion. The structure body includes a first passage interior to the structure body. The first passage includes a first opening on one of a radially outward edge and a radially inward edge of the structure, and a second opening on the other of the radially outward edge and the radially inward edge of the structure. A second passage is also included interior to the structure. The second passage is approximately aligned with the first passage, and is disposed between the first passage and one of the first surface and the second surface of the structure. The second passage insulates the first passage from heat transfer through one of the first surface and the second surface.
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公开(公告)号：US10041357B2
公开(公告)日：2018-08-07
申请号：US14600048
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Dominic J. Mongillo, Jr.
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D5/225 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F05D2260/22141
Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots.
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公开(公告)号：US09957820B2
公开(公告)日：2018-05-01
申请号：US14728723
申请日：2015-06-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite
CPC classification number: F01D9/02 , F01D5/188 , F01D5/189 , F01D9/023 , F05D2220/32 , F05D2240/121 , F05D2240/15 , Y02T50/676
Abstract: A heat shield is provided for use in an inner cavity of a gas turbine engine component. The heat shield comprises a heat shield body comprising opposed side portions defining an inner channel. An inner section of a side portion of the opposed side portions is inwardly sloped such that a cross-section of the heat shield body is smaller in an inner body portion relative to a cross-section of an outer body portion thereof. An aperture is disposed through the side portion in a selected radial position. A vane assembly including the heat shield is also provided.
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公开(公告)号：US09926789B2
公开(公告)日：2018-03-27
申请号：US14707928
申请日：2015-05-08
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Dominic J. Mongillo
CPC classification number: F01D5/189 , F01D5/147 , F01D5/18 , F01D9/065 , F01D25/005 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2230/50 , F05D2230/60 , F05D2260/20 , Y02T50/676
Abstract: A flow splitting baffle for separating a main cooling flow through an inner channel of a component includes a tubular structure defining a tubular cavity and having a longitudinal axis. The flow splitting baffle also includes an inner ring coupled to the tubular structure and extending away from the tubular structure along a plane that is perpendicular to the longitudinal axis. The flow splitting baffle also includes an outer ring parallel to the plane, positioned a first distance from the tubular structure, extending away from the tubular structure and positioned a second distance from the inner ring. The flow splitting baffle also includes a strut perpendicular to the plane, extending from the inner ring to the outer ring and coupled to the inner ring and the outer ring.
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公开(公告)号：US20160258300A1
公开(公告)日：2016-09-08
申请号：US14639165
申请日：2015-03-05
Applicant: United Technologies Corporation
Inventor： Ryan Alan Waite , Benjamin F. Hagan
CPC classification number: F01D5/188 , F01D5/185 , F01D5/186 , F01D5/187 , F01D9/065 , F01D25/12 , F05D2250/185 , Y02T50/676
Abstract: A flow path component for a gas powered turbine including a flow path component body having cross sectional profile having a leading edge and a trailing edge, the leading edge being connected to the trailing edge by a first side and being connected to the trailing edge by a second side opposite the first side, a serpentine cooling passage including a plurality of segments, each of the segments being generally radially aligned, wherein a first subset of the segments disposed along one of the first side and the second side of the cross sectional profile, and a second subset of the segments spans the flow path component body from the first side to the second side, and a cavity internal to the flow path component body, wherein the cavity is at least partially shielded from one of the first side and the second side by at least one of the plurality of segments.
Abstract translation: 一种用于燃气动力涡轮机的流路部件，其包括具有前缘和后缘的横截面轮廓的流路部件主体，前缘通过第一侧连接到后缘，并且通过一个 第二侧相对于第一侧，蛇形冷却通道包括多个段，每个段大致径向对准，其中沿着横截面轮廓的第一侧和第二侧中的一个设置的段的第一子集， 并且所述段的第二子集跨越从第一侧到第二侧的流动路径部件主体，以及在流路部件主体内部的空腔，其中所述空腔至少部分地与第一侧和第二侧之一 通过所述多个片段中的至少一个片段。
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