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公开(公告)号：US09726043B2
公开(公告)日：2017-08-08
申请号：US13327349
申请日：2011-12-15
CPC分类号： F01D25/246 , F01D5/284 , F01D11/08 , F01D11/12 , F01D11/24 , F05D2240/11 , F05D2250/41 , F05D2260/38 , Y02T50/672
摘要： A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.
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公开(公告)号：US20130156556A1
公开(公告)日：2013-06-20
申请号：US13402616
申请日：2012-02-22
申请人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty , Joshua Brian Jamison
发明人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty , Joshua Brian Jamison
IPC分类号： F04D29/42
CPC分类号： F01D25/246 , F01D5/284 , F01D11/08 , F01D11/24 , F05D2240/11 , F05D2250/41 , F05D2250/61 , F05D2250/712 , F05D2260/38 , F05D2300/6033
摘要： A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.
摘要翻译： 一种用于燃气涡轮发动机的护罩段，所述护罩段由复合材料构成，所述复合材料包括嵌入基质中的增强纤维，并且具有由相对的前壁和后壁限定的横截面形状，以及相对的内壁和外壁，所述壁延伸 在相对的第一和第二端面之间，其中所述内壁限定弓形的内部流路表面; 并且其中复合圆角设置在第一和第二壁之间的接合处，所述复合圆角包括第一和第二部分，所述第二部分具有延伸到所述第一壁中的凹曲率。
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公开(公告)号：US09175579B2
公开(公告)日：2015-11-03
申请号：US13402616
申请日：2012-02-22
申请人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty , Joshua Brian Jamison
发明人： Michael John Franks , Jason David Shapiro , Samuel Ross Rulli , Roger Lee Doughty , Joshua Brian Jamison
CPC分类号： F01D25/246 , F01D5/284 , F01D11/08 , F01D11/24 , F05D2240/11 , F05D2250/41 , F05D2250/61 , F05D2250/712 , F05D2260/38 , F05D2300/6033
摘要： A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.
摘要翻译： 一种用于燃气涡轮发动机的护罩段，所述护罩段由复合材料构成，所述复合材料包括嵌入基质中的增强纤维，并且具有由相对的前壁和后壁限定的横截面形状，以及相对的内壁和外壁，所述壁延伸 在相对的第一和第二端面之间，其中所述内壁限定弓形的内部流路表面; 并且其中复合圆角设置在第一和第二壁之间的接合处，所述复合圆角包括第一和第二部分，所述第二部分具有延伸到所述第一壁中的凹曲率。
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公开(公告)号：US20130156550A1
公开(公告)日：2013-06-20
申请号：US13327349
申请日：2011-12-15
IPC分类号： F04D29/40
CPC分类号： F01D25/246 , F01D5/284 , F01D11/08 , F01D11/12 , F01D11/24 , F05D2240/11 , F05D2250/41 , F05D2260/38 , Y02T50/672
摘要： A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.
摘要翻译： 用于燃气涡轮发动机的护罩装置包括：环形金属吊架; 设置在所述衣架内的护罩区段，包括低延展性材料并且具有由相对的前壁和后壁限定的横截面形状，以及相对的内壁和外壁，所述壁在相对的第一和第二端面之间延伸， 壁定义了弧形内流道表面; 以及保持器，其机械地联接到所述衣架，其接合所述护罩区段，以将所述护罩区段保持在所述衣架上，同时允许所述护罩区段在径向方向上移动。
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公开(公告)号：US07946801B2
公开(公告)日：2011-05-24
申请号：US11965402
申请日：2007-12-27
申请人： Jason David Shapiro , David Allen Flodman , Samuel Ross Rulli , Samir Dimitri Sayegh , Norman Clement Brackett
发明人： Jason David Shapiro , David Allen Flodman , Samuel Ross Rulli , Samir Dimitri Sayegh , Norman Clement Brackett
IPC分类号： F01D5/08
CPC分类号： F02C7/18 , F01D5/08 , F01D9/041 , F01D9/06 , F01D11/001 , F01D11/08 , F01D25/12 , F01D25/246 , F05D2220/3213 , F05D2240/11 , F05D2260/201 , Y02T50/676
摘要： A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle having: (i) spaced-apart arcuate inner and outer bands; and (ii) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the vane disposed in a primary flowpath of the engine; (b) a supporting structure coupled to the outer band such that an outer band cavity is defined between the outer band and the stationary structure; (c) a first conduit passing through the outer band cavity and communicating with the interior of the vane, the first conduit coupled to a first source of cooling air within the engine; and (d) a second conduit communicating with the outer band cavity, the second conduit coupled to a second source of cooling air within the engine.
摘要翻译： 用于燃气涡轮发动机的冷却装置包括：（a）涡轮喷嘴，其具有：（i）间隔开的弓形内部和外部带; 和（ii）在所述内带和外带之间延伸的中空翼型涡轮叶片，所述叶片设置在所述发动机的主流路中; （b）耦合到所述外带的支撑结构，使得在所述外带和所述固定结构之间限定外带空腔; （c）通过所述外带空腔并与所述叶片内部连通的第一管道，所述第一管道联接到所述发动机内的第一冷却空气源; 和（d）与外带空腔连通的第二导管，第二导管连接到发动机内的第二冷却空气源。
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公开(公告)号：US20100281879A1
公开(公告)日：2010-11-11
申请号：US11965402
申请日：2007-12-27
申请人： Jason David Shapiro , David Allen Flodman , Samuel Ross Rulli , Samir Dimitri Sayegh , Norman Clement Brackett
发明人： Jason David Shapiro , David Allen Flodman , Samuel Ross Rulli , Samir Dimitri Sayegh , Norman Clement Brackett
CPC分类号： F02C7/18 , F01D5/08 , F01D9/041 , F01D9/06 , F01D11/001 , F01D11/08 , F01D25/12 , F01D25/246 , F05D2220/3213 , F05D2240/11 , F05D2260/201 , Y02T50/676
摘要： A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle having: (i) spaced-apart arcuate inner and outer bands; and (ii) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the vane disposed in a primary flowpath of the engine; (b) a supporting structure coupled to the outer band such that an outer band cavity is defined between the outer band and the stationary structure; (c) a first conduit passing through the outer band cavity and communicating with the interior of the vane, the first conduit coupled to a first source of cooling air within the engine; and (d) a second conduit communicating with the outer band cavity, the second conduit coupled to a second source of cooling air within the engine.
摘要翻译： 用于燃气涡轮发动机的冷却装置包括：（a）涡轮喷嘴，其具有：（i）间隔开的弓形内部和外部带; 和（ii）在所述内带和外带之间延伸的中空翼型涡轮叶片，所述叶片设置在所述发动机的主流路中; （b）耦合到所述外带的支撑结构，使得在所述外带和所述固定结构之间限定外带空腔; （c）通过所述外带空腔并与所述叶片内部连通的第一管道，所述第一管道联接到所述发动机内的第一冷却空气源; 和（d）与外带空腔连通的第二导管，第二导管连接到发动机内的第二冷却空气源。
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公开(公告)号：US20110189009A1
公开(公告)日：2011-08-04
申请号：US12696566
申请日：2010-01-29
申请人： Jason David Shapiro , Roger Lee Doughty , Aaron Dziech , Victor Correia , Elias Lampes , Robert Carella , Brian Corsetti
发明人： Jason David Shapiro , Roger Lee Doughty , Aaron Dziech , Victor Correia , Elias Lampes , Robert Carella , Brian Corsetti
CPC分类号： F01D25/246 , F01D11/12
摘要： A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member; (b) a turbine shroud disposed in the support member, the shroud being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring mounted between the support member and the shroud and arranged to resiliently urge the shroud to a concentric position within the structural member.
摘要翻译： 为具有中心轴线的燃气涡轮发动机提供涡轮机护罩装置。 该装置包括：（a）环形支撑构件; （b）设置在所述支撑构件中的涡轮机罩，所述护罩是包括低延性材料并具有相对的流路和后表面以及相对的前后端的连续环; 和（c）弹簧，其安装在所述支撑构件和所述护罩之间并且布置成将所述护罩弹性地推动到所述结构构件内的同心位置。
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公开(公告)号：US08079807B2
公开(公告)日：2011-12-20
申请号：US12696566
申请日：2010-01-29
申请人： Jason David Shapiro , Roger Lee Doughty , Aaron Dziech , Victor Correia , Elias Lampes , Robert Carella , Brian Corsetti
发明人： Jason David Shapiro , Roger Lee Doughty , Aaron Dziech , Victor Correia , Elias Lampes , Robert Carella , Brian Corsetti
CPC分类号： F01D25/246 , F01D11/12
摘要： A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member; (b) a turbine shroud disposed in the support member, the shroud being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring mounted between the support member and the shroud and arranged to resiliently urge the shroud to a concentric position within the structural member.
摘要翻译： 为具有中心轴线的燃气涡轮发动机提供涡轮机护罩装置。 该装置包括：（a）环形支撑构件; （b）设置在所述支撑构件中的涡轮机罩，所述护罩是包括低延性材料并具有相对的流路和后表面以及相对的前后端的连续环; 和（c）弹簧，其安装在所述支撑构件和所述护罩之间并且布置成将所述护罩弹性地推动到所述结构构件内的同心位置。
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公开(公告)号：US08172522B2
公开(公告)日：2012-05-08
申请号：US12058980
申请日：2008-03-31
IPC分类号： F01D25/28
CPC分类号： F01D9/042 , F01D25/246 , F04D29/526 , F04D29/644 , F05D2260/94 , F05D2260/941
摘要： A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.
摘要翻译： 描述了一种在涡轮发动机定子组件中支撑可移除静态部件的方法和系统。 该方法包括以下步骤：将位于第一静态部件上的第一位置的定子吊架与位于第一静态结构上的柱接合，由此支柱支撑第一静态部件的重量的至少一部分， 位于所述第一静态部件上的第二位置，所述第二静止部件位于与所述第一位置周向隔开的位置处，所述第二静止部件位于所述第二静止部件上的所述定子衣架上，并且使位于所述第一静止部件上的第三位置的钩与第二静止部件 结构，由此第二静态结构支撑第一静态部件的重量的至少一部分。
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公开(公告)号：US20090246012A1
公开(公告)日：2009-10-01
申请号：US12058972
申请日：2008-03-31
CPC分类号： F01D9/042
摘要： A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.
摘要翻译： 描述了提供对用于燃气涡轮发动机的定子叶片的支撑的反应安装系统，其包括位于第一位置处的外带上的定子悬挂器和位于与第一位置周向隔开的第二位置的定子止动器。 描述了一种用于燃气涡轮发动机的定子组件，该定子组件包括具有翼型的定子叶片，位于翼型件的径向外端的外带，位于轴向邻近外带的护罩，衣架悬挂器包括 柱，其中所述柱的至少一部分在所述外带的一部分上沿轴向方向延伸;以及反应安装系统，位于所述外带上，其中所述反作用安装系统与所述柱接合以为所述定子叶片提供支撑。
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