公开(公告)号：US10082043B2

公开(公告)日：2018-09-25

申请号：US14750094

申请日：2015-06-25

申请人： Pratt & Whitney Canada Corp.

发明人： Guy Lefebvre ,  Rene Paquet

IPC分类号： F02K1/48 ,  F01D25/30 ,  F02K1/38 ,  B01F3/02 ,  F01D25/00

CPC分类号： F01D25/30 ,  B01F3/026 ,  F01D25/005 ,  F02K1/386 ,  F02K1/48 ,  F05D2220/32 ,  F05D2240/40 ,  F05D2260/30 ,  F05D2260/96 ,  F05D2300/6033 ,  Y02T50/672

摘要： A multi-lobe exhaust mixer has an annular body composed of a plurality of circumferentially adjacent lobe segments. The lobe segments may be made of a ceramic matrix composite material to reduce the weight of the mixer and ensure proper behavior when exposed to high thermal gradients. Each lobe segment may have partial lobes at circumferentially opposed ends thereof and at least one complete lobe therebetween. The partial lobes of the circumferentially adjacent lobe segments combining to conjointly form complete lobes at the junction between the circumferentially adjacent lobe segments. The partial lobes may be nested into each other to dampen vibrations.

公开(公告)号：US09845696B2

公开(公告)日：2017-12-19

申请号：US14570139

申请日：2014-12-15

申请人： Pratt & Whitney Canada Corp.

发明人： Guy Lefebvre ,  Rene Paquet

IPC分类号： F01D11/00 ,  F01D11/08 ,  F01D25/12

CPC分类号： F01D11/005

摘要： A shroud sealing arrangement for a gas turbine engine, which comprises a static shroud assembly mounted to an engine case and having a platform surrounding a rotatable airfoil array. The platform has an inner side and an outer side and extends from a leading edge to a trailing edge. A shroud support structure mounts the shroud platform to the case. A circumferential groove is defined on the outer side of the shroud platform proximal to one of the leading edge and the trailing edge. A sealing ring is set in the groove and adapted to seal cooling air from escaping directly to the gas path.

公开(公告)号：US09121289B2

公开(公告)日：2015-09-01

申请号：US13630310

申请日：2012-09-28

申请人： Pratt & Whitney Canada Corp.

发明人： Ghislain Plante ,  Rene Paquet ,  Patrick Peloquin

IPC分类号： F01D5/18 ,  F01D5/14

CPC分类号： F01D5/186 ,  F01D5/141 ,  F01D5/187 ,  F05D2250/74

摘要： A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one row of holes selected from the group consisting of a first row, a second row, a third row and a fourth row, with the first, second, third and fourth rows of holes respectively including the holes numbered PA-1 to PA-10, PB-1 to PB-3, HA-1 to HA-9, and SA-1 to SA-8 located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.

摘要翻译： 一种用于燃气涡轮发动机的涡轮机叶片，其具有由围绕至少一个外壳的周边壁限定的翼型部分，所述周边壁具有限定在其中的多个冷却孔，并且在所述至少一个外壳和气体的气体路径之间提供流体连通 涡轮发动机。 多个冷却孔包括从由第一排，第二排，第三排和第四排组成的组中选择的至少一排孔，第一排，第二排，第三排和第四排孔分别包括孔 编号为PA-1至PA-10，PB-1至PB-3，HA-1至HA-9和SA-1至SA-8，其中心轴延伸穿过相应的点1和点2， 根据表3中列出的X，Y，Z笛卡尔坐标值的标称位置。

公开(公告)号：US10533444B2

公开(公告)日：2020-01-14

申请号：US15814926

申请日：2017-11-16

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Guy Lefebvre ,  Rene Paquet

IPC分类号： F01D11/00

摘要： A shroud sealing arrangement for a gas turbine engine, which comprises a static shroud assembly mounted to an engine case and having a platform surrounding a rotatable airfoil array. The platform has an inner side and an outer side and extends from a leading edge to a trailing edge. A shroud support structure mounts the shroud platform to the case. A circumferential groove is defined on the outer side of the shroud platform proximal to one of the leading edge and the trailing edge. A sealing ring is set in the groove and adapted to seal cooling air from escaping directly to the gas path.

公开(公告)号：US09689276B2

公开(公告)日：2017-06-27

申请号：US14335289

申请日：2014-07-18

申请人： Pratt & Whitney Canada Corp.

发明人： Guy Lefebvre ,  Rene Paquet

IPC分类号： F01D25/12 ,  F01D11/24 ,  F01D25/14

CPC分类号： F01D25/12 ,  F01D11/24 ,  F01D25/14 ,  F01D25/246 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/205

摘要： A gas turbine engine includes an annular casing and a plurality of shroud segments forming an annular shroud. The annular shroud forms with the annular casing an annular cavity therebetween. The annular cavity includes an inlet and an outlet. An annular ring assembly is disposed in the annular cavity between the casing and the shroud and cooperating therewith to provide a first annular chamber and a second annular chamber. The annular ring assembly and a first portion of the shroud form the first annular chamber. The annular ring assembly and a second portion of the shroud form the second annular chamber. The annular ring assembly forms an intermediate annular chamber disposed between the first annular chamber and the second annular chamber. A flow path for coolant air is sequentially defined through the inlet, the first annular chamber, the intermediate annular chamber, the second annular chamber and the outlet.

公开(公告)号：US08561415B2

公开(公告)日：2013-10-22

申请号：US13782140

申请日：2013-03-01

申请人： Pratt & Whitney Canada Corp.

发明人： Mike Fontaine ,  Rene Paquet ,  Jean Fournier

IPC分类号： F02C7/20

CPC分类号： F01D25/24 ,  F01D25/162

摘要： A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.

摘要翻译： 具有工作流体流动的燃气涡轮发动机壳体包括限定用于引导工作流体流动的环形管道的内外壳部分和定位在环形管道内并在内壳部分和外壳部分之间延伸的多个支柱。 支柱通过沿着相应支柱的周边线的第一焊接并且具有圆角型的第二焊接在选定的位置焊接到内外壳部分，用于将每个支柱的一部分附加到相应的内壳和外壳 部分。