Patent ID: 7534085
Filing Date: 2009-05-19
Classification: F01D,Y02T

Abstract:
1. A gas turbine engine comprising: a fan section, a compressor section, a combustor section and a turbine section spaced along an axis; said turbine section including at least one rotor disk including a plurality of disk slots, a plurality of turbine blades, each received within a corresponding one of said plurality of disk slots, and a cooling air supply for supplying cooling air along an axial length of said gas turbine engine and into said disk slots, said cooling air entering said disk slots at a position radially inwardly of a radial inner end of said turbine blades, and said turbine blades having air supply openings for receiving the cooling air delivered into said disk slots, and delivering said air radially outwardly along a length of said turbine blades; and cooling air flowing through said disk slot from an inlet end toward an exit end, and a first cross-sectional area of said disk slot adjacent said inlet end being greater than a second cross-sectional area at a location downstream of said inlet end, and the difference in cross-sectional area of said disk slot adjacent said inlet end and the location downstream of said inlet end being achieved by changing a contour of said disk slot.