Patent ID: 7465154
Filing Date: 2008-12-16
Classification: F01D,F05D

Abstract:
1. A gas turbine engine component comprising: a component body extending from a leading edge toward a trailing edge, said component body having an airfoil shape with a pressure side and a suction side; a cooling channel formed within said component body, and an impingement tube received within said cooling channel, such that cooling fluid may be directed into said impingement tube for passing along a length of said component body and outwardly through impingement holes in said impingement tube, and against an inner wall of both said pressure side and said suction side, said cooling channel having pedestals spaced towards said trailing edge relative to said impingement tube; and supplemental pedestals formed on said inner wall of said suction side and extending toward said impingement tube at an end of said impingement tube spaced toward said trailing edge, and there being impingement holes in a pressure side portion of said impingement tube aligned with said supplemental pedestals, wherein said impingement tube has no impingement holes in a suction side portion of said impingement tube aligned with said supplemental pedestals.