Method and apparatus for reducing rotor assembly circumferential rim stress
AssigneeGeneral Electric Company
InventorStephen Michael Carter
Life of this patent
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Abstract
A rotor assembly for a gas turbine engine operates with reduced circumferential rim stress. The rotor assembly includes a rotor including a plurality of rotor blades and a radially outer platform. The rotor blades extend radially outward from the platform. A root fillet extends circumferentially around each blade between the blades and platforms. The platforms include an outer surface including a plurality of indentations extending between adjacent rotor blades. Each indentation extends from a leading edge of the platform to a trailing edge of the platform with a depth that tapers to an approximate zero depth at the trailing edge.
Claims20
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 an outer platform and a plurality of circumferentially spaced apart rotor blades extending radially outward from the outer platform, the outer platform including an outer surface, a leading edge, and a trailing edge, each rotor blade including a root fillet extending between the outer platform outer surface and each rotor blade, said method comprising the steps of:
- forming in the outer platform outer surface, between each set of adjacent rotor blades, one indentation, and thereby forming a plurality of indentations, and extending the indentations from the outer platform leading edge to the outer platform trailing edge.
A rotor assembly for a gas turbine engine, said rotor assembly comprising a rotor comprising a plurality of rotor blades and a radially outer platform, said plurality of rotor blades extending radially outwardly from said platform, said outer platform comprising an outer surface, a leading edge, and a trailing edge, said outer surface comprising one indentation, formed between each set of adjacent rotor blades, and thereby forming a plurality of indentations, and the indentations extending from the outer platform leading edge to said outer platform trailing edge, said outer surface configured to reduce circumferential rim stress concentration between each of said rotor blades and said outer platform.
A gas turbine engine comprising a rotor assembly comprising a rotor comprising a plurality of rotor blades and a radially outer platform, said plurality of rotor blades extending radially outwardly from said rotor assembly outer platform, each of said rotor blades comprising a root fillet extending between each of said rotor blades and said rotor assembly outer platform, said rotor assembly outer platform comprising an outer surface, a leading edge, and a trailing edge, said outer surface comprising each set of adjacent rotor blades, and thereby forming a plurality of indentations, and the indentations extending from the outer platform leading edge to said outer platform trailing edge, said outer surface configured to reduce circumferential rim stress concentration between each of said rotor assembly rotor blades and said rotor assembly outer platform.
Dependencies are inferred from the claim text.