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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：US20160326887A1
公开(公告)日：2016-11-10
申请号：US14707988
申请日：2015-05-08
Applicant: United Technologies Corporation
Inventor： Ryan A. Waite , Benjamin F. Hagan
CPC classification number: F01D5/187 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2230/50 , F05D2240/12 , F05D2260/202 , F05D2260/232 , Y02T50/673 , Y02T50/676
Abstract: A turbomachine component (e.g., a blade, vane, or any other suitable component) is defined at least partially in a radial direction and an axial direction orthogonal to the radial direction and includes a body defining an outer surface configured to be in thermal communication with a gas path flow in the axial direction. The component includes a thermal regulation channel system defined within the body which includes at least one radial channel configured to allow thermal regulation flow in the radial direction, and at least one axial channel configured to allow thermal regulation flow in the axial direction.
Abstract translation: 涡轮机组件（例如，叶片，叶片或任何其它合适的部件）至少部分地在与径向方向正交的径向方向和轴向方向上限定，并且包括限定外表面的主体，该外表面被配置为与 气路在轴向上流动。 该部件包括限定在主体内的热调节通道系统，该热调节通道系统包括至少一个径向通道，该径向通道构造成允许沿径向进行热调节流动，以及至少一个轴向通道，其构造成允许在轴向上的热调节流动。
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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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Patent Agency Ranking
公开(公告)号：US10738643B2
公开(公告)日：2020-08-11
申请号：US16164958
申请日：2018-10-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan , David Richard Griffin
Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.
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公开(公告)号：US10465543B2
公开(公告)日：2019-11-05
申请号：US15810279
申请日：2017-11-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Lane Thornton
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：US09957815B2
公开(公告)日：2018-05-01
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 includes a flow path component body having cross sectional profile having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a first side and by a second side opposite the first side. A serpentine cooling passage includes a plurality of segments, each of the segments being generally radially aligned. A first subset of the segments is 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. A cavity is positioned internal to the flow path component body. 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.
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公开(公告)号：US09810084B1
公开(公告)日：2017-11-07
申请号：US14615509
申请日：2015-02-06
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ryan Alan Waite , Steven Bruce Gautschi , Benjamin F. Hagan
CPC classification number: F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.
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公开(公告)号：US20170268371A1
公开(公告)日：2017-09-21
申请号：US15071439
申请日：2016-03-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan , David Richard Griffin
CPC classification number: F01D11/12 , F01D5/02 , F01D9/041 , F01D11/08 , F01D25/08 , F02C7/28 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2260/231 , F05D2260/30 , F05D2260/38 , F05D2260/52 , Y02T50/672
Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.
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