Patent ID: 6837683
Filing Date: 2005-01-04
Classification: F01D,F05D

Abstract:
1. An aerofoil having leading and trailing edges for a gas turbine engine comprising inner chambers, at least one of said chambers adjacent said leading edge of said aerofoil being provided with a cooling fluid inlet and at least one other chamber adjacent said trailing edge being provided with a cooling fluid outlet, the inner chambers having passageways linking one chamber to an adjacent chamber and the chambers being arranged in series from the leading edge to the trailing edge of the aerofoil such that cooling fluid flow is directed within the aerofoil from the leading edge region to the trailing edge region of the aerofoil and each said chamber having an internal wall and wherein the passageways are angled to direct the cooling air from one chamber to an adjacent chamber on to said internal wall of the adjacent chamber so as to provide impingement cooling thereof and to provide cooling air to successive sections of the internal surfaces of the aerofoil suction and pressure surfaces.