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TURBINE AIRFOIL COOLING SYSTEM WITH INTEGRATED AIRFOIL AND PLATFORM COOLING SYSTEM

United States Patent Application

20170370231
A1
View the Complete Application at the US Patent & Trademark Office
A cooling system (10) for a turbine airfoil (12) of a turbine engine having one or more mid-chord cooling channels (16) that extend through both the airfoil (32) and a platform (18) of the airfoil (12) to provide adequate cooling the platform (18) while cooling the airfoil (32) is disclosed. The mid-chord cooling channel (16) may be formed from an airfoil portion (20) extending generally spanwise within the airfoil (32) and a platform portion (22) extending into a platform (18) of the airfoil (12) with a larger cross-sectional area than a cross-sectional area of the airfoil portion (20). The mid-chord cooling channel (16) may also extend into the platform (18) of the airfoil (12) a distance laterally outside of a silhouette (60) of the airfoil (32) defined by the leading edge (24), trailing edge (26), pressure side (28) and suction side (30) of the airfoil (32). Thus, the mid-chord cooling channel (16) extends laterally into the platform (18) to provide adequate cooling the platform (18).
Lee, Ching-Pang (Cincinnati, OH), Waywood, Anthony (Cincinnati, OH), Johnson, Erik (Cedar Park, TX), Koester, Steven (Toledo, OH)
15/ 544,034
January 28, 2015
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH [0001] Development of this invention was supported in part by the United States Department of Energy, Contract No. DE-FC26-05NT42644. Accordingly, the United States Government may have certain rights in this invention.