EP1908922A3

Device and method for hybrid vapor and film cooling of a turbine blade

Abstract

An apparatus for a gas turbine engine includes an airfoil (22) defining a leading edge (28) and a trailing edge (30), a root (26) located adjacent to the airfoil (22), 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 (36) located within the airfoil (22) and a condenser (40) section located within the root (26).

EP1908922A3, drawing sheet 1
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Term

1 yearto projected expiry

Projected expiry 26 September 2027, counted from filing; an application has no term until it is granted.

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