Heat treatment for dual alloy turbine wheels
AssigneeAllied-Signal Inc.
InventorGeorge S. Hoppin, III
Life of this patent
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Abstract
A dual alloy gas turbine rotor is heat treated by HIP bonding a cast superalloy blade ring to a consolidated, powdered-metal hub. After bonding, the assembly is solution treated and aged at certain specific temperatures so as to optimize the mechanical properties of the dual alloy assembly for use in a high performance gas turbine engine.
Claims10
A method of heat-treating a dual alloy component of the type having a first portion made from a first nickel base superalloy containing about 15% Cr, 17% Co, 5.3% Mo, 4% Al and 3.5% Ti and a second portion made from a second nickel base superalloy containing about 8.2% Cr, 10% Co, 0.6% Mo, 10% W, 3% Ta, 5.5% Al and 1% Ti, comprising the steps of:
- heating the component at about 2040.degree. F. for about two hours,
- rapidly air cooling the component to room temperature,
- reheating the component to about 1600.degree. F. for about 16 hours,
- allowing the component to cool,
- reheating the component to about 1400.degree. F. for 16 hours, and
- allowing the component to cool.
A method of manufacturing a dual alloy turbine rotor for a high performance gas turbine engine, comprising the steps of:
- providing a hub portion made from a first nickel base superalloy containing about 15% Cr 17% Co, 5.3% Mo, 4% Al and 3.5% Ti;
- providing a blade portion made from a second nickel base superalloy containing about 8.2% Cr, 10% Co, 0.6% Mo, 10% W, 3% Ta, 5.5% Al, and 1% Ti;
- bonding said hub portion to said blade portion by hot isostatic pressure;
- solution treating the bonded portions at about 2040.degree. F. for about 2 hours;
- reheating the bonded portions to about 1600.degree. F. for about 16 hours, and
- again reheating the bonded portions to about 1400.degree. F. for another 16 hours.
A dual alloy turbine rotor comprising a hub portion composed of a first nickel base superalloy composition having high tensile strength at elevated temperatures,
- a blade portion composed of a second nickel base superalloy composition having high creep-rupture strength at elevated temperatures,
- said hub portion being metallurgically bonded to said blade portion to form a unitary rotor, and
- said rotor being heat treated after bonding by solutionizing at about 2040.degree. F. and double aging, first at about 1600.degree. F. and then at about 1400.degree. F.
Dependencies are inferred from the claim text.