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TURBINE AIRFOIL COOLING SYSTEM WITH CHORDWISE EXTENDING SQUEALER TIP COOLING CHANNEL

United States Patent Application

20170370232
A1
View the Complete Application at the US Patent & Trademark Office
An internal cooling system (10) for an airfoil (12) in a turbine engine (14) whereby the cooling system (10) includes a chordwise extending tip cooling channel (16) radially inward of a squealer tip (18) and formed at least in part by an inner wall (20) with a nonlinear outer surface (22) is disclosed. The nonlinear outer surface (22) of the inner wall (20) of the chordwise extending tip cooling channel (16) may be formed from pressure and suction side sections (24, 26) that intersect at a point (74) that is closer to the inner surface (30) of an outer wall (32) forming at least a portion of the squealer tip (18) than other aspects of the pressure side section (24) and the suction side section (26). The configurations of the pressure and suction side sections (24, 26) reduces the flow cross-sectional area, which accelerates the cooling fluid flow in a chordwise direction within the chordwise extending tip cooling channel (16) and directs cooling fluid toward the pressure and suction side outer walls (34, 36) for improved cooling efficiency.
Lee, Ching-Pang (Cincinnati, OH)
15/ 544,112
January 22, 2015
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT [0001] Development of this invention was supported in part by the United States Department of Energy, Advanced Turbine Development Program, Contract No. DE-FC26-05NT42644. Accordingly, the United States Government may have certain rights in this invention.