EP1528224A3

Method and apparatus for cooling gas turbine engine rotor blade

Abstract

A rotor blade (40) for a gas turbine engine, includes a platform (62) including a radially outer surface (152) and a radially inner surface (144). An airfoil (60) extends radially outward from the platform. A shank (64) extends radially inward from the platform. A dovetail (66) extends from the shank such that an internal cavity is defined at least partially by the airfoil, the platform, the shank, and the dovetail. A cooling circuit extends through a portion of the shank for supplying cooling air from the cavity for impingement cooling of the platform radially inner surface.

EP1528224A3, drawing sheet 1
Sheet 1 of 2

Term

Term ended

Projected expiry passed 27 October 2024, 1.9 years ago.

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2 sheets

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  2. Sheet 2