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INTERNAL COOLING SYSTEM WITH CONVERGING-DIVERGING EXIT SLOTS IN TRAILING EDGE COOLING CHANNEL FOR AN AIRFOIL IN A TURBINE ENGINE

United States Patent Application

20180038233
A1
View the Complete Application at the US Patent & Trademark Office
An airfoil (10) is disclosed for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more converging-diverging exit slots (20) configured to increase the effectiveness of the cooling system (14) at the trailing edge (34) of the airfoil (10) by increasing the contact of cooling fluids with internal surfaces (24, 30) of the pressure and suction sides (36, 38) of the airfoil (10). In at least one embodiment, the trailing edge cooling channel (18) may include one or more converging-diverging exit slots (20) to further pressurize the trailing edge cooling channel (18) and may be formed by a first and second ribs (80, 82) extending between an outer walls (13, 12) forming the pressure and suction sides (36, 38). The converging-diverging exit slot (20) may be formed from a first converging section (84) having an inlet (86) with a larger cross-sectional area than an outlet (88) and is formed from a second diverging section (90) having an inlet (92) with a smaller cross-sectional area than an outlet (94).
Lee, Ching-Pang (Cincinnati, OH), Myers, Caleb (Cincinnati, OH), Johnson, Erik (Cedar Park, TX), Koester, Steven (Toledo, OH)
15/ 552,882
March 17, 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.