United States of America As Represented by the Administrator of Nasa

John Gayda

Timothy P Gabb

Ronald Dean Noebe

Michael V Nathal

Pete T Kantzos

Peter T Kantzos

Ignacy Telesman

A low solvus, high refractory alloy having unusually versatile processing mechanical property capabilities for advanced disks and rotors in gas turbine engines. The nickel base superalloy has a composition consisting essentially of, in weight percent, 3.0&#x2013;4.0 Al, 0.02&#x2013;0.04 B, 0.02&#x2013;0.05 C, 12.0&#x2013;14.0 Cr, 19.0&#x2013;22.0 Co, 2.0&#x2013;3.5 Mo, greater than 1.0 to 2.1 Nb, 1.3 to 2.1 Ta, 3.0&#x2013;4.0 Ti, 4.1 to 5.0 W, 0.03&#x2013;0.06 Zr, and balance essentially Ni aid incidental impurities. The superalloy combines ease of processing with high temperature capabilities to be suitable for use in various turbine engine disk, impeller, and shaft applications. The Co and Cr levels of the superalloy can provide low solvus temperature for high processing versatility. The W, Mo, Ta, and Nb refractory element levels of the superalloy can provide sustained strength, creep, and dwell crack growth resistance at high temperatures.

Nickel base superalloy turbine disk

A multi-layered component, such as a rocket engine combustion chamber, includes NiAl or NiAl-based alloy as a structural layer on the 'hot' side of the component. A second structural layer is formed of material selected from Ni-based superalloys, Co-based alloys, Fe-based alloys, Cu, and Cu-based alloys. The second material is more ductile than the NiAl and imparts increased toughness to the component. The second material is selected to enhance one or more predetermined physical properties of the component. Additional structural layers may be included with the additional material(s) being selected for their impact on physical properties of the component.

NiAl-based approach for rocket combustion chambers

A heat treatment assembly and heat treatment methods are disclosed for producing different microstructures in the bore and rim portions of nickel-based superalloy disks, particularly suited for gas turbine applications. The heat treatment assembly is capable of being removed from the furnace and disassembled to allow rapid fan or oil quenching of the disk. For solutioning heat treatments of the disk, temperatures higher than that of this solvus temperature of the disk are used to produce coarse grains in the rim of each disk so as to give maximum creep and dwell crack resistance at the rim service temperature. At the same time, solution temperature lower than the solvus temperature of the disk are provided to produce fine grain in the bore of the disk so as to give maximum strength and low cycle fatigue resistance.

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Avon Lake, OH, United States of America

John Gayda