公开(公告)号：US09062556B2

公开(公告)日：2015-06-23

申请号：US13630402

申请日：2012-09-28

Applicant: Pratt & Whitney Canada Corp.

Inventor： Michael Leslie Clyde Papple ,  Daniel Lecuyer ,  Patrick Peloquin

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/186 ,  F01D5/141 ,  F01D5/187 ,  F05D2250/74

Abstract: 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.

公开(公告)号：US09121289B2

公开(公告)日：2015-09-01

申请号：US13630310

申请日：2012-09-28

Applicant: Pratt & Whitney Canada Corp.

Inventor： Ghislain Plante ,  Rene Paquet ,  Patrick Peloquin

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/186 ,  F01D5/141 ,  F01D5/187 ,  F05D2250/74

Abstract: 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.

Abstract translation: 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。