Method for making a compositionally graded gas turbine disk
AssigneeGeneral Electric Company
InventorsJon Raymond Groh, Eric Allen Ott, Robert Edward Schafrik, Daniel Donald Krueger
Life of this patent
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Abstract
A compositionally graded gas turbine disk is made by preparing a rotationally symmetric radially inner segment of a gas turbine disk preform, rotating the inner segment about a central axis, spray applying a radially outer-segment material onto the radially inner segment as it rotates about the central axis, preferably achieving a gradual transition in composition, and thereafter further processing the gas turbine disk preform to produce the compositionally graded gas turbine disk.
Claims20
A method for making a compositionally graded gas turbine disk, comprising the steps of
- preparing a radially inner segment of a gas turbine disk preform, wherein the radially inner segment is formed of a radially inner-segment material, and wherein the radially inner segment is rotationally symmetric about a central axis;
- thereafter
- rotating the radially inner segment about the central axis;
- spray applying a radially outer-segment material onto the radially inner segment as it rotates about the central axis, to form a radially outer segment;
- and thereafter
- further processing the gas turbine disk preform to produce the compositionally graded gas turbine disk.
A method for making a compositionally graded gas turbine disk, comprising the steps of
- preparing a radially inner segment of a gas turbine disk preform, wherein the radially inner segment is formed of a radially inner-segment nickel-base superalloy material, and wherein the radially inner segment is rotationally symmetric about a central axis;
- thereafter
- rotating the radially inner segment about the central axis;
- spray applying a radially outer-segment material onto the radially inner segment, as it rotates about the central axis, to form a radially outer segment, wherein a composition of the radially outer-segment material is substantially the same as a composition of the radially inner-segment material at an interface between the radially outer segment and the radially inner segment, and wherein the composition of the radially outer-segment material varies with increasing distance from the interface;
- and thereafter
- further processing the gas turbine disk preform to produce the compositionally graded gas turbine disk, wherein the step of further processing includes the steps of
- compacting the gas turbine disk preform, thereafter
- upset forging the gas turbine disk preform, and thereafter
- heat treating the gas turbine disk preform.
Dependencies are inferred from the claim text.