Patent ID: 6471474
Filing Date: 2002-10-29
Classification: F01D,F04D,Y10S,Y10T

Abstract:
A method of fabricating a rotor assembly to facilitate reducing circumferential rim stress concentration in a gas turbine engine, the rotor assembly including a rotor that includes a radially outer rim and a plurality of rotor blades extending radially outward from the outer rim, the outer rim including an outer surface, each rotor blade including a leading edge and a trailing edge, said method comprising the steps of:forming a plurality of circumferentially concave indentations into the outer rim between adjacent rotor blades, wherein each indentation includes a compound radius that extends circumferentially between adjacent blades; and extending the indentations from the rotor blade leading edge towards the rotor blade trailing edge, such that the indentations do not extend to the trailing edge.