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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：US20170002662A1
公开(公告)日：2017-01-05
申请号：US14789356
申请日：2015-07-01
Applicant: United Technologies Corporation
Inventor： Ryan Alan Waite , Matthew A. Devore , Benjamin F. Hagan
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D9/065 , F05D2250/313 , F05D2250/75 , F05D2260/20 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes a body that extends in a radial direction that provides an exterior airfoil surface. The body includes pressure and suction side walls that extend from a leading edge to a trailing edge in a chord-wise direction. A core cooling passage is provided between the pressure and suction side walls and extends in the radial direction. A skin passage is arranged in one of the pressure and suction side walls between the core cooling passage and the exterior airfoil surface. The skin passage includes a first passageway that extends in the radial direction. The first passageway turns to a second passageway that extends in the chord-wise direction to terminate at an exit arranged near the trailing edge.
Abstract translation: 用于燃气涡轮发动机的翼型件包括沿径向延伸的主体，其提供外部翼型表面。 主体包括压力和吸力侧壁，其沿着弦向方向从前缘延伸到后缘。 核心冷却通道设置在压力侧和吸力侧壁之间，并沿径向方向延伸。 皮芯通道设置在芯冷却通道和外部翼型件表面之间的压力和吸力侧壁之一中。 皮肤通道包括沿径向方向延伸的第一通道。 第一通道转向第二通道，该第二通道沿顺时针方向延伸以终止在靠近后缘的出口处。
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公开(公告)号：US20160265372A1
公开(公告)日：2016-09-15
申请号：US14641470
申请日：2015-03-09
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ky H. Vu , Jeffrey J. DeGray , Ryan Alan Waite , Gina Cavallo , Thomas P. Dziuba
CPC classification number: F01D9/041 , F01D5/02 , F01D5/186 , F01D5/189 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2230/21 , F05D2230/642 , F05D2240/126 , F05D2240/80 , F05D2260/20 , F05D2260/30 , Y02T50/676
Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.
Abstract translation: 燃气涡轮发动机部件组件包括相对于发动机中心轴线与第一部件周向间隔开的第一部件和第二部件。 第一挡板与第一部件相关联。 第二挡板与第二部件相关联。 第一和第二挡板中的每一个包括至少一个径向挡板。 在第一和第二挡板之间形成间隙以限定冷却空气入口。 第一盖板与第一挡板相关联以覆盖间隙的第一部分。 第二盖板与第二挡板相关联以覆盖间隙的第二部分。 第一和第二盖板彼此分开，并且包括至少一个盖板径向突片，其与相关联的至少一个挡板径向突片配合，以防止第一和第二挡板与第一和第二盖板之间的泄漏间隙。
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Patent Agency Ranking
16.发明申请GAS TURBINE ENGINE AIRFOIL COOLING CONFIGURATION WITH PRESSURE GRADIENT SEPARATORS 审中-公开气体涡轮发动机空气冷却配置与压力梯级分离器公开(公告)号：US20160251968A1
公开(公告)日：2016-09-01
申请号：US14632485
申请日：2015-02-26
Applicant: United Technologies Corporation
Inventor： San Quach , Ryan Alan Waite , Christopher King , Steven Bruce Gautschi
CPC classification number: F01D5/187 , F01D5/147 , F01D9/041 , F01D11/08 , F01D25/30 , F05D2220/32 , F05D2240/122 , F05D2240/127 , F05D2240/304 , F05D2240/307 , F05D2240/35 , F05D2240/55 , F05D2260/221 , F05D2260/2212 , F05D2260/2214 , F23R3/002 , Y02T50/673 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.
Abstract translation: 用于燃气涡轮发动机的翼型件包括翼型件，其包括在前缘和后缘处连接的间隔开的压力和抽吸侧壁，以提供从平台向尖端沿径向延伸的外部翼型件表面。 在后缘附近的压力侧和吸力侧壁之间设置空腔。 空腔包括由相对于彼此成角度布置的第一和第二出射区域界定的内部区域。 第一出口区域和第二出口区域分别相对于彼此在低压区域和高压区域中。 分别在第一和第二出口区域设置第一和第二基座组。 第二基座组具有各自终止的第一和第二基座。 第二基座的端部延伸超过第一基座的端部。
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公开(公告)号：US10385699B2
公开(公告)日：2019-08-20
申请号：US14632485
申请日：2015-02-26
Applicant: United Technologies Corporation
Inventor： San Quach , Ryan Alan Waite , Christopher King , Steven Bruce Gautschi
Abstract: An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.
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公开(公告)号：US10208602B2
公开(公告)日：2019-02-19
申请号：US14697329
申请日：2015-04-27
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Ryan Alan Waite , Peter Balawajder , Benjamin F. Hagan
Abstract: A film cooled component may comprise a cooling chamber and a first ligament centered about a first axis. The first ligament may be in fluid communication with the cooling chamber. A first meter may be disposed at an end of the first ligament. A first diffuser may extend from the first meter to a surface of the film cooled component. The first diffuser may comprise a first tapered sidewall oriented at an angle of between 5 degrees to 15 degrees relative to the first axis. The first diffuser may further comprise a first non-tapered sidewall oriented at an angle less than 5 degrees relative to the first axis.
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公开(公告)号：US20180355731A1
公开(公告)日：2018-12-13
申请号：US16049987
申请日：2018-07-31
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. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.
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公开(公告)号：US20180066532A1
公开(公告)日：2018-03-08
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
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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