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公开(公告)号：US20180038236A1
公开(公告)日：2018-02-08
申请号：US15783741
申请日：2017-10-13
Applicant: United Technologies Corporation
Inventor： Jaime G. Ghigliotty , Matthew A. Devore
CPC classification number: F01D9/041 , F01D5/189 , F05D2220/32 , F05D2230/13 , F05D2230/14 , F05D2240/126 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/22141 , F05D2300/177 , Y02T50/676
Abstract: A method of flowing cooling fluid through a stator vane in a gas turbine engine includes the step of providing an airfoil that has an exterior wall that provides a cooling cavity. The exterior surface has an interior surface that has multiple pin fins that extend therefrom. A baffle is arranged in the cooling cavity and supported by the pin fins. A perimeter cavity is provided between the baffle and the exterior wall. The pin fins are arranged in the perimeter cavity. Cooling fluid flows through a region in the perimeter cavity. The pin fins are arranged in the region having a low Reynolds number and through which the cooling fluid
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公开(公告)号：US20170204731A1
公开(公告)日：2017-07-20
申请号：US14997992
申请日：2016-01-18
Applicant: United Technologies Corporation
Inventor： Matthew A. Devore , Eleanor D. Kaufman
CPC classification number: F01D5/189 , F01D9/02 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2260/2212
Abstract: A baffle insert for a component of a gas turbine engine is provided. The baffle insert having: a first fluid conduit having a first interior cavity extending therethrough; a second fluid conduit having a second interior cavity extending therethrough; and a member located between the first fluid conduit and the second fluid conduit, wherein the member fluidly couples the first interior cavity to an exterior of the second fluid conduit, and wherein the member fluidly couples the second interior cavity to an exterior of the first fluid conduit and wherein the first interior cavity is isolated from the second interior cavity.
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公开(公告)号：US09551228B2
公开(公告)日：2017-01-24
申请号：US13737200
申请日：2013-01-09
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , San Quach , Matthew A. Devore
CPC classification number: F01D5/187 , B22C9/10 , B22C9/103 , F01D5/186 , F05D2260/201 , F05D2260/202 , F05D2260/205 , Y10T29/49337
Abstract: An airfoil includes leading and trailing edges, a first exterior wall extending from the leading edge to the trailing edge and having inner and outer surfaces, a second exterior wall extending from the leading edge to the trailing edge generally opposite the first exterior wall and having inner and outer surfaces, and cavities within the airfoil. A first cavity extends along the inner surface of the first exterior wall and a first inner wall and has an upstream end and a downstream end, and a feed cavity is located between the first inner wall and the second exterior wall.
Abstract translation: 机翼包括前缘和后缘，从前缘延伸到后缘并具有内表面和外表面的第一外壁，从前缘延伸到后缘的第二外壁，大体与第一外壁相对，并且具有内 和外表面以及翼型内的空腔。 第一腔沿着第一外壁的内表面延伸并且具有第一内壁，并且具有上游端和下游端，并且进料腔位于第一内壁和第二外壁之间。
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公开(公告)号：US20160186576A1
公开(公告)日：2016-06-30
申请号：US14627587
申请日：2015-02-20
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Scott D. Lewis , Matthew A. Devore
CPC classification number: F01D5/186 , F01D9/041 , F01D25/12 , F05D2220/30 , F05D2230/12 , F05D2230/13 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A cooling hole for a component includes a meter section and a diffuser section. The diffuser section has a footprint region defined by five sides, a first side of the five sides extending along substantially an entire height of the diffuser section and second and third sides of the five sides meeting in an obtuse angle opposite the first side. A component having the cooling hole and a method of forming the cooling hole are also disclosed.
Abstract translation: 用于组件的冷却孔包括仪表部分和扩散器部分。 扩散器部分具有由五个侧面限定的覆盖区域，五个侧面的第一侧沿着扩散器部分的大致整个高度延伸，五边的第二和第三侧以与第一侧相对的钝角相交。 还公开了具有冷却孔的部件和形成冷却孔的方法。
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Patent Agency Ranking
65.发明申请GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS 审中-公开气体涡轮发动机空气动力学几何和制造过程的方法公开(公告)号：US20160032732A1
公开(公告)日：2016-02-04
申请号：US14841324
申请日：2015-08-31
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, JR. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
CPC classification number: F01D5/187 , B22C9/10 , B22C9/101 , B22C9/24 , B22F3/1055 , B22F5/10 , B33Y10/00 , B33Y80/00 , C22C28/00 , F05D2220/32 , F05D2230/21 , F05D2230/31 , F05D2260/20 , F05D2300/131 , Y02P10/292 , Y02P10/295
Abstract: An airfoil for a gas turbine engine includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness. The second thickness is less than 0.060 inch (1.52 mm).
Abstract translation: 用于燃气涡轮发动机的翼型包括具有通过间隔开的压力和吸力侧连接的前缘和后缘的主体，以提供由周壁限定的外部翼面。 内壁布置在周边壁的内部和附近，以在其间提供冷却通道。 具有第一和第二部分的冷却通道是锥形的并且分别具有第一和第二厚度。 第一厚度大于第二厚度。 第二厚度小于0.060英寸（1.52毫米）。
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公开(公告)号：US20160010465A1
公开(公告)日：2016-01-14
申请号：US14633677
申请日：2015-02-27
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Dominic J. Mongillo, JR. , Matthew A. Devore
CPC classification number: F01D5/187 , F01D5/08 , F01D5/186 , F01D5/188 , F01D9/041 , F01D17/16 , F05D2220/32 , F05D2220/3212 , F05D2240/12 , F05D2240/303 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: An example gas turbine engine component includes an airfoil having a leading edge area, a first circuit to cool a first section of the leading edge area, and a second circuit to cool a second section of the leading edge area. The first circuit separate and distinct from the second circuit within the airfoil.
Abstract translation: 示例性燃气涡轮发动机部件包括具有前缘区域的翼型件，用于冷却前缘区域的第一部分的第一电路和用于冷却前缘区域的第二部分的第二电路。 第一回路与翼型内的第二回路分开且不同。
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公开(公告)号：US20160010463A1
公开(公告)日：2016-01-14
申请号：US14767768
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： San Quach , Matthew A. Devore
CPC classification number: F01D5/186 , F01D5/187 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/30 , F05D2240/35 , F05D2260/202 , Y02T50/671 , Y02T50/673 , 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. A stagnation line is located on the pressure side wall aft of the leading edge. A cooling passage is provided between the pressure and suction side walls. Forward-facing cooling holes are provided adjacent to the stagnation line on the pressure side wall and oriented toward the leading edge.
Abstract translation: 用于燃气涡轮发动机的翼型件包括在前缘和后缘处彼此连接的压力和吸力侧壁。 停滞线位于前缘的压力侧壁后方。 在压力侧和吸力侧壁之间设有冷却通道。 靠近压力侧壁上的停滞线设置面向前的冷却孔并朝向前缘定向。
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公开(公告)号：US20160003071A1
公开(公告)日：2016-01-07
申请号：US14708830
申请日：2015-05-11
Applicant: United Technologies Corporation
Inventor： Jaime G. Ghigliotty , Matthew A. Devore
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D5/189 , F05D2220/32 , F05D2230/13 , F05D2230/14 , F05D2240/126 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/22141 , F05D2300/177 , Y02T50/676
Abstract: A stator vane for a gas turbine engine includes an airfoil that has an exterior wall that provides a cooling cavity. The exterior surface has an interior surface that has multiple pin fins extending therefrom. A baffle is arranged in the cooling cavity and is supported by the pin fins.
Abstract translation: 用于燃气涡轮发动机的定子叶片包括具有提供冷却腔的外壁的翼型件。 外表面具有从其延伸的多个销翅片的内表面。 挡板布置在冷却腔中并由销翅片支撑。
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公开(公告)号：US20150322801A1
公开(公告)日：2015-11-12
申请号：US14687974
申请日：2015-04-16
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Matthew A. Devore
CPC classification number: F01D5/18 , F01D5/186 , F01D5/187 , F01D9/02 , F01D25/12 , F01D25/24 , F05D2220/32 , F05D2260/202 , Y02T50/676
Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a first cooling hole with a first cooling passage arranged at a first angle relative to a chordwise axis and a second cooling hole with a second cooling passage arranged at a second different angle relative to the chordwise axis. A radial projection of the first cooling passage intersects a radial projection of the second cooling passage.
Abstract translation: 根据本公开的示例性方面的翼型件包括第一冷却孔，第一冷却孔具有相对于弦向轴线以第一角度布置的第一冷却通道和第二冷却孔，第二冷却通道布置在第二冷却通道的第二冷却通道 不同的角度相对于和弦轴。 第一冷却通道的径向突起与第二冷却通道的径向突出部相交。
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