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1.发明授权公开(公告)号：US10801344B2
公开(公告)日：2020-10-13
申请号：US15845727
申请日：2017-12-18
摘要： An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. A skin core cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The skin core cooling passage is divided by a wall into two discrete first and second skin core cooling passages each supplied with cooling fluid from opposing sides.
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公开(公告)号：US10689988B2
公开(公告)日：2020-06-23
申请号：US14683408
申请日：2015-04-10
摘要： A component for a gas turbine engine includes a root with a neck that extends into a fir tree with at least one tooth, the root includes a feed passage in communication with a multiple of cooling passages that extend through the neck and fir tree.
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公开(公告)号：US10670273B2
公开(公告)日：2020-06-02
申请号：US15698967
申请日：2017-09-08
发明人： Tracy A Propheter-Hinckley , Benjamin D Bellows , Brandon W Spangler , David J Hyland , Dennis M Moura , Dustin W Davis , Mark F Zelesky , Ricardo Trindade , Steven Bruce Gautschi , Trevor Rudy
摘要： A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.
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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
摘要： 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：US20190203602A1
公开(公告)日：2019-07-04
申请号：US15856182
申请日：2017-12-28
发明人： Shawn M. McMahon , Christopher Whitfield , Nicholas M. LoRicco , Steven Bruce Gautschi , Vincent E. Simms , Justin M. Aniello , Thomas Allwood , Richard M. Salzillo , Jeffery Scott Hembree, SR.
CPC分类号： F01D5/186 , F01D9/041 , F01D9/065 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/202
摘要： A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.
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公开(公告)号：US10190420B2
公开(公告)日：2019-01-29
申请号：US14618912
申请日：2015-02-10
摘要： An airfoil according to an example of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a reference plane extending in a spanwise direction along a surface of the internal wall, a first cavity and a second cavity separated by the internal wall, and a plurality of crossover passages within the internal wall and connecting the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The passage axis of each of the plurality of crossover passages is arranged at a radial angle relative to a localized region of the reference plane such that the radial angle of at least some of the plurality of crossover passages differs in the spanwise direction.
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公开(公告)号：US20190017390A1
公开(公告)日：2019-01-17
申请号：US15997943
申请日：2018-06-05
摘要： A method of manufacturing a component for a gas turbine engine according to an exemplary aspect of the present disclosure includes forming the component with a first manufacturing technique to include a first cavity and a second cavity, and a microcircuit in fluid communication with the first cavity, the component including an outer wall and a ribbed portion or a bulged portion extending from the outer wall. The exemplary method includes forming a plunged hole with a second manufacturing technique different from the first manufacturing technique to intersect at least a portion of the microcircuit and extend into the ribbed portion or the bulged portion.
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公开(公告)号：US20180281051A1
公开(公告)日：2018-10-04
申请号：US15960857
申请日：2018-04-24
发明人： Lane Thornton , San Quach , Steven Bruce Gautschi
摘要： In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.
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公开(公告)号：US20160251980A1
公开(公告)日：2016-09-01
申请号：US15028468
申请日：2014-10-17
CPC分类号： F01D25/12 , F01D5/02 , F01D5/12 , F01D9/041 , F01D11/001 , F01D11/04 , F01D17/14 , F01D17/162 , F02C3/04 , F05D2220/32 , F05D2240/35 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2260/20
摘要： A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine.
摘要翻译： 公开了一种用于燃气涡轮发动机的涡轮叶片组件，并且包括可围绕横向于发动机纵向轴线的第一轴线旋转的翼型件。 翼型件包括端壁和设置在端壁上的至少一个突出部，其构造成阻止流过端壁与燃气涡轮发动机的静态结构之间的间隙。
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公开(公告)号：US09284845B2
公开(公告)日：2016-03-15
申请号：US14250166
申请日：2014-04-10
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil comprises pressure and suction surfaces extending from a root section to a tip section of the airfoil. The airfoil also comprises a leading edge and trailing edge defining a chord length therebetween. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall, the tip shelf wall being spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate less than 85% of the chord length measured from the trailing edge.
摘要翻译： 翼型件包括从根部延伸到翼型的尖端部分的压力和吸力表面。 翼型件还包括在其间限定弦长的前缘和后缘。 沿着压力表面和尖端搁板壁之间的尖端部分形成尖端搁板，顶部搁板壁在压力表面和吸力表面之间分开。 沿尖端搁架壁和从抽吸面延伸的尖叫尖端壁之间的尖端部分形成一个尖叫口袋。 尖端架从从前缘测量的绳索长度的10％范围内延伸到从后缘测量的弦长的10％以内。 尖叫口袋从前缘测量的弦长的10％范围内延伸，以终止从后缘测得的弦长的85％以下。
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