公开(公告)号：PL367009A1

公开(公告)日：2004-10-18

申请号：PL36700904

申请日：2004-04-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  PALUMBO MICHAEL A

IPC: F01D5/18 ,  F02C7/12

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided includes a plenum (80) longitudinally located within the leading edge (46) of the airfoils. Within the plenum (80) are positioned a plurality of turbulence promoters (86) to provide enhanced heat transfer within the leading edge. Also, the cooling design includes a plurality of inlets (72,76) to receive cooling air from an internal cavity (36) of the airfoil as well as a plurality of outlets (64,66) located within a trench (52) on the exterior surface of the leading edge (46) through which the cooling air exits to film cool the leading edge.

公开(公告)号：SG125938A1

公开(公告)日：2006-10-30

申请号：SG200401289

申请日：2004-03-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  PALUMBO MICHAEL A

IPC: F01D5/00 ,  F01D5/18

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes a plenum (80) longitudinally located within the leading edge (46) of the airfoils. Within the plenum (80) are positioned a plurality of turbulence promoters (86) to provide enhanced heat transfer within the leading edge (46). Also, the cooling design includes a plurality of inlets (72,76) to receive cooling air from an internal cavity (36) of the airfoil as well as a plurality of outlets (64,66) located within a trench on the exterior surface of the leading edge (46) through which the cooling air exists to film cool the leading edge.

公开(公告)号：CA2462986A1

公开(公告)日：2004-10-07

申请号：CA2462986

申请日：2004-04-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PALUMBO MICHAEL A ,  CUNHA J FRANK

IPC: F01D5/18 ,  F01D25/12

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes a plenum longitudinally located within the leading edge of the airfoils. Within the plenum are positioned a plurality of turbulence promoters to provide enhanced heat transfer within the leading edge. Also, the cooling design includes a plurality of inlets to receive cooling air from an internal cavity of the airfoil as well as a plurality of outlets located within a trench on the exterior surface of the leading edge through which the cooling air exits to film cool the leading edge.