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公开(公告)号：US10208628B2
公开(公告)日：2019-02-19
申请号：US15085625
申请日：2016-03-30
发明人： Shakeel Nasir , John Schugardt , Nick Nolcheff , John Meier , Yogendra Yogi Sheoran , Shezan Kanjiyani , Daniel Aukland
摘要： A turbine engine incorporating a fine particle separation means includes a radial compressor that rotates about a longitudinal axis, a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc the redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the outer annular wall at a position downstream axially along the flow path from the arc.
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公开(公告)号：US20150275763A1
公开(公告)日：2015-10-01
申请号：US14227924
申请日：2014-03-27
发明人： Shezan Kanjiyani , John Gintert , Rajiv Rana , Lorenzo Crosatti , Bradley Reed Tucker , Ed Zurmehly
CPC分类号： F02C7/18 , F01D5/187 , F01D11/08 , F01D25/12 , F01D25/14 , F02C3/10 , F05D2240/81 , F05D2260/201 , F05D2260/205 , Y02T50/673 , Y02T50/676
摘要： A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.
摘要翻译： 涡轮部分包括具有内径端壁，外径端壁和定子叶片的定子组件; 涡轮转子组件，其包括延伸到主流气流路径中的转子叶片; 壳体，其包括环绕所述转子叶片并且至少部分地限定所述主流热气体流动路径的环形护罩; 第一挡板，布置成限定具有定子组件的外径端壁的第一腔; 第二挡板 以及第三挡板，其布置成限定具有第二挡板的第二空腔和具有护罩的第三空腔。 第一腔体流体地联接到第二腔体，而第二腔室流体耦合到第三空腔，使得冷却空气从第一空腔流到第二空腔，并从第二腔体流到第三空腔。
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3.发明申请公开(公告)号：US20140169957A1
公开(公告)日：2014-06-19
申请号：US13719566
申请日：2012-12-19
CPC分类号： F01D1/04 , B23P11/00 , F01D9/041 , F01D9/042 , F05D2230/60 , F05D2260/941 , Y02T50/671 , Y10T29/49245
摘要： Embodiments of a turbine nozzle are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring and a slip joint ring, which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots therein. A plurality of vanes is fixedly coupled to the support ring and extends radially therefrom into the plurality of slots. A plurality of radial slip joints is formed between the plurality of vanes and the plurality slots. Each slip joint extends around a different one of the plurality of vanes to permit relative radial movement between the plurality of vanes and the slip joint ring during operation of the turbine nozzle.
摘要翻译： 提供涡轮喷嘴的实施例，如制造涡轮喷嘴的方法的实施例。 在一个实施例中，涡轮喷嘴包括支撑环和滑动接头环，其与支撑环基本上同心并且与其径向间隔开。 滑接环在其中具有多个狭槽。 多个叶片固定地联接到支撑环并且从其径向延伸到多个狭槽中。 在多个叶片和多个槽之间形成多个径向滑动接头。 每个滑动接头围绕多个叶片中的不同的叶片延伸，以允许在涡轮喷嘴的操作期间在多个叶片和滑动接头环之间的相对径向移动。
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公开(公告)号：US09970307B2
公开(公告)日：2018-05-15
申请号：US14219622
申请日：2014-03-19
CPC分类号： F01D11/005 , B23K1/0018 , B23K2101/001 , B23P15/04 , F01D5/28 , F01D9/041 , F01D9/042 , F01D11/00 , F01D17/162 , F05D2300/182 , Y02T50/673 , Y10T29/49321
摘要： Embodiments of a turbine nozzle having slip joints impregnated by an oxidation-resistant sealing material are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the method includes providing a support ring, a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, and a plurality of vanes fixedly coupled to the support ring. The plurality of vanes extends radially from the support ring into a plurality of circumferentially-spaced slots provided in the slip joint ring to form a plurality of slip joints therewith. The plurality of slip joints are impregnated with a silicon-modified aluminide sealing material. The silicon-modified aluminide sealing material impedes gas flow into the radial slip joints during operation of the turbine nozzle, while also fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring along the plurality of slip joints.
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公开(公告)号：US09885245B2
公开(公告)日：2018-02-06
申请号：US14283104
申请日：2014-05-20
CPC分类号： F01D9/02 , F01D9/04 , F01D9/042 , F01D9/065 , F01D25/12 , F01D25/246 , F05D2220/32 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： Turbine nozzles and cooling systems for cooling slip joints therein are provided. The turbine nozzle has an endwall, a vane coupled to the endwall, a slip joint, and a plurality of airfoil quenching holes that cooperate with a plurality of endwall cooling holes. The vane comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall and an end portion. The slip joint is between the end portion and the endwall. The airfoil quenching holes are defined through the pressure sidewall in the end portion. The endwall cooling holes are defined through the endwall along the pressure sidewall and in proximity to the leading edge. The airfoil quenching holes and endwall cooling holes are disposed adjacent the slip joint.
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公开(公告)号：US09611748B2
公开(公告)日：2017-04-04
申请号：US14099218
申请日：2013-12-06
CPC分类号： F01D9/042 , B22C9/04 , B22C9/22 , F01D9/041 , F01D25/26 , F05D2230/21 , F05D2300/50212
摘要： Stationary airfoils configured to form an improved slip joint in bi-cast turbine engine components and the turbine engine components including the same are provided. The stationary airfoil for a bi-cast turbine engine component comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. An end portion is shaped with a pair of opposing flanges to form a slip joint with a shroud ring in the bi-cast turbine engine component and to define an interlocking feature. The slip joint permits radial movement of the stationary airfoil relative to the shroud ring due to thermal differential expansion and contraction.
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公开(公告)号：US09657642B2
公开(公告)日：2017-05-23
申请号：US14227924
申请日：2014-03-27
发明人： Shezan Kanjiyani , John Gintert , Rajiv Rana , Lorenzo Crosatti , Bradley Reed Tucker , Ed Zurmehly
CPC分类号： F02C7/18 , F01D5/187 , F01D11/08 , F01D25/12 , F01D25/14 , F02C3/10 , F05D2240/81 , F05D2260/201 , F05D2260/205 , Y02T50/673 , Y02T50/676
摘要： A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.
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公开(公告)号：US20150337680A1
公开(公告)日：2015-11-26
申请号：US14283104
申请日：2014-05-20
CPC分类号： F01D9/02 , F01D9/04 , F01D9/042 , F01D9/065 , F01D25/12 , F01D25/246 , F05D2220/32 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： Turbine nozzles and cooling systems for cooling slip joints therein are provided. The turbine nozzle has an endwall, a vane coupled to the endwall, a slip joint, and a plurality of airfoil quenching holes that cooperate with a plurality of endwall cooling holes. The vane comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall and an end portion. The slip joint is between the end portion and the endwall. The airfoil quenching holes are defined through the pressure sidewall in the end portion. The endwall cooling holes are defined through the endwall along the pressure sidewall and in proximity to the leading edge. The airfoil quenching holes and endwall cooling holes are disposed adjacent the slip joint.
摘要翻译： 提供了用于冷却滑动接头的涡轮喷嘴和冷却系统。 涡轮喷嘴具有端壁，联接到端壁的叶片，滑动接头以及与多个端壁冷却孔配合的多个翼型骤冷孔。 叶片包括通过压力侧壁和吸力侧壁和端部部分互连的前缘和后缘。 滑动接头位于端部和端壁之间。 翼型淬火孔通过端部中的压力侧壁限定。 端壁冷却孔沿着压力侧壁并且靠近前缘限定通过端壁。 翼片淬火孔和端壁冷却孔设置在滑动接头附近。
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9.发明申请GAS PATH COMPONENTS OF GAS TURBINE ENGINES AND METHODS FOR COOLING THE SAME USING POROUS MEDIUM COOLING SYSTEMS 有权气体涡轮发动机的气体路径成分及使用多孔介质冷却系统进行冷却的方法公开(公告)号：US20150322800A1
公开(公告)日：2015-11-12
申请号：US14275012
申请日：2014-05-12
CPC分类号： F01D5/189 , B22F3/1055 , B22F5/009 , B22F5/04 , B22F7/004 , F01D5/147 , F01D5/183 , F01D5/186 , F01D5/188 , F05D2260/202 , F05D2260/203 , Y02P10/295 , Y02T50/676 , Y10T29/49321
摘要： Gas path components of gas turbine engines and methods for cooling the same using porous medium cooling systems are provided. The gas path component comprises a wall at least partially defining a cooling plenum and a porous medium cooling system. The wall includes a wall surface comprising a gas path surface and an opposing wall surface proximate the cooling plenum. The porous medium cooling system is disposed between the cooling plenum and the opposing wall surface. The porous medium cooling system comprises a perforated baffle and a porous material layer disposed between and adjacent the perforated baffle and the opposing wall surface. The wall includes a plurality of openings in fluid communication with the cooling plenum via the porous medium cooling system.
摘要翻译： 提供燃气涡轮发动机的气路部件和使用多孔介质冷却系统对其进行冷却的方法。 气体路径部件包括至少部分限定冷却气室和多孔介质冷却系统的壁。 该壁包括壁表面，该壁表面包括靠近冷却气室的气体通道表面和相对的壁表面。 多孔介质冷却系统设置在冷却气室和相对的壁表面之间。 多孔介质冷却系统包括穿孔挡板和设置在穿孔挡板和相对的壁表面之间和之间的多孔材料层。 该壁包括多个通过多孔介质冷却系统与冷却气室流体连通的开口。
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10.发明申请TURBINE NOZZLES WITH SLIP JOINTS IMPREGNATED BY OXIDATION-RESISTANT SEALING MATERIAL AND METHODS FOR THE PRODUCTION THEREOF 有权具有耐氧化密封材料浸渍的滑动接头的涡轮喷嘴及其生产方法公开(公告)号：US20150267550A1
公开(公告)日：2015-09-24
申请号：US14219622
申请日：2014-03-19
CPC分类号： F01D11/005 , B23K1/0018 , B23K2101/001 , B23P15/04 , F01D5/28 , F01D9/041 , F01D9/042 , F01D11/00 , F01D17/162 , F05D2300/182 , Y02T50/673 , Y10T29/49321
摘要： Embodiments of a turbine nozzle having slip joints impregnated by an oxidation-resistant sealing material are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the method includes providing a support ring, a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, and a plurality of vanes fixedly coupled to the support ring. The plurality of vanes extends radially from the support ring into a plurality of circumferentially-spaced slots provided in the slip joint ring to form a plurality of slip joints therewith. The plurality of slip joints are impregnated with a silicon-modified aluminide sealing material. The silicon-modified aluminide sealing material impedes gas flow into the radial slip joints during operation of the turbine nozzle, while also fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring along the plurality of slip joints.
摘要翻译： 提供了具有由耐氧化密封材料浸渍的滑动接头的涡轮喷嘴的实施例，如制造涡轮喷嘴的方法的实施例。 在一个实施例中，该方法包括提供支撑环，与支撑环基本上同心且与其径向间隔开的滑动关节环以及固定地联接到支撑环的多个叶片。 多个叶片从支撑环径向地延伸到设置在滑动接合环中的多个周向间隔开的槽中，以与其形成多个滑动接头。 多个滑动接头用硅改性的铝化物密封材料浸渍。 硅改性的铝化物密封材料在涡轮喷嘴操作期间阻止气体流入径向滑动接头，同时还可以断裂以允许沿着多个滑动接头在多个叶片和滑动接头环之间的相对径向运动。
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