Kinney & Lange, P.A.
Hybrid vapor and film cooled turbine blade
An apparatus for a gas turbine engine includes an airfoil defining a leading edge and a trailing edge, a root located adjacent to the airfoil, a vapor cooling system, and a film cooling system for cooling the airfoil in conjunction with the vapor cooling system. The vapor cooling system includes a vaporization section located within the airfoil and a condenser section located within the root.
United Technologies Corporation
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James W. James D.
Norris Hill