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：US10533749B2

公开(公告)日：2020-01-14

申请号：US14923594

申请日：2015-10-27

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sri Sreekanth ,  Si-Man Lao ,  Michael Leslie Clyde Papple

IPC: F02C1/00 ,  F23R3/16

Abstract: A turbine component includes a structure having hot and cold surfaces opposite each other; and a plurality of cooling holes extending between the cold and hot surfaces, each of the cooling holes including at least one projection or recess element to form part of a fluid path surface with enhanced in-hole heat convection.