公开(公告)号：US20100281879A1

公开(公告)日：2010-11-11

申请号：US11965402

申请日：2007-12-27

Applicant: Jason David Shapiro ,  David Allen Flodman ,  Samuel Ross Rulli ,  Samir Dimitri Sayegh ,  Norman Clement Brackett

Inventor： Jason David Shapiro ,  David Allen Flodman ,  Samuel Ross Rulli ,  Samir Dimitri Sayegh ,  Norman Clement Brackett

IPC: F02C7/18 ,  F02C6/08

CPC classification number: F02C7/18 ,  F01D5/08 ,  F01D9/041 ,  F01D9/06 ,  F01D11/001 ,  F01D11/08 ,  F01D25/12 ,  F01D25/246 ,  F05D2220/3213 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

Abstract: 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.

Abstract translation: 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：US07008183B2

公开(公告)日：2006-03-07

申请号：US10746092

申请日：2003-12-26

Applicant: Samir Dimitri Sayegh ,  Glen William Royal ,  Massimo Rufo

Inventor： Samir Dimitri Sayegh ,  Glen William Royal ,  Massimo Rufo

IPC: F01D9/02

CPC classification number: F01D9/04 ,  F01D25/12 ,  F05D2260/201 ,  Y02T50/67 ,  Y02T50/676

Abstract: An impingement baffle includes a perforate plate having a pattern of impingement holes. An imperforate deflector is spaced from the plate and is smaller than the plate for deflecting inlet air around the deflector to the holes. The baffle is disposed between a turbine shroud and supporting hanger, and the deflector is disposed between the hanger and the baffle.

Abstract translation: 冲击挡板包括具有冲击孔图案的穿孔板。 无孔导流板与板间隔开并且小于板，用于将导流器周围的入口空气偏转到孔。 挡板设置在涡轮机护罩和支撑悬架之间，并且偏转器设置在悬挂器和挡板之间。

公开(公告)号：US07946801B2

公开(公告)日：2011-05-24

申请号：US11965402

申请日：2007-12-27

Applicant: Jason David Shapiro ,  David Allen Flodman ,  Samuel Ross Rulli ,  Samir Dimitri Sayegh ,  Norman Clement Brackett

Inventor： Jason David Shapiro ,  David Allen Flodman ,  Samuel Ross Rulli ,  Samir Dimitri Sayegh ,  Norman Clement Brackett

IPC: F01D5/08

CPC classification number: F02C7/18 ,  F01D5/08 ,  F01D9/041 ,  F01D9/06 ,  F01D11/001 ,  F01D11/08 ,  F01D25/12 ,  F01D25/246 ,  F05D2220/3213 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

Abstract: 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.

Abstract translation: 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。