Patent ID: 6974306
Filing Date: 2005-12-13
Classification: F01D

Abstract:
1. In combination, an internally cooled turbine blade and a rotor disc for a gas turbine engine, the turbine disc and the turbine blade cooperating to form an air cavity therebetween, the air cavity being defined by a disc first wall extending generally radially relative to the turbine disc and along a general direction of a rotation axis of the rotor disc, a disc second wall extending generally parallel to the first wall, an upstream entry end and a downstream end, a flow of cooling air in use entering the air cavity generally at an angle to the first wall by reason of rotation of the air cavity relative to the flow of cooling air, the first wall thereby in use redirecting the flow of cooling air entering the cavity towards the downstream end of the cavity, the turbine blade comprising a series of inlets communicating with the air cavity and with internal cooling passages defined inside the turbine blade, and at least one deflector extending into the air cavity, the deflector extending generally from said first wall to a position nearer to but remote from the second wall, the deflector thereby adapted to divert cooling air entering the cavity away from the first wall and generally towards the second wall.