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。

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

IPC分类号： F02C7/18 ,  F02C6/08

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。