United States of America As Represented by the Administrator of Nasa

Michael V Nathal

Ronald Dean Noebe

Bruce M Steinetz

Patrick H Dunlap, Jr

Susan L Draper

Frank J Ritzert

Jeffrey J DeMange

James L Smialek

Timothy P Gabb

John Gayda

Anita Garg

Edwin A Crombie

Rebecca A MacKay

A process for forming a single crystal superalloy wave spring is provided. In one embodiment, the process may include machining a wave spring from a single crystal superalloy slab after optimizing its orientation using diffraction techniques so that the wave spring will exhibit optimal spring properties.

Process for forming a single crystal superalloy wave spring

A process for forming a high temperature single crystal canted spring is provided. In one embodiment, the process includes fabricating configurations of a rapid prototype spring to fabricate a sacrificial mold pattern to create a ceramic mold and casting a canted coiled spring to form at least one canted coil spring configuration based on the ceramic mold. The high temperature single crystal canted spring is formed from a nickel-based alloy containing rhenium using the at least one coil spring configuration.

Process for forming a high temperature single crystal canted spring

A composition of the invention is a high temperature shape memory alloy having high work output, and is made from (Ni+Pt+Y)Ti, wherein x is present in a total amount of 49-55 atomic %, Pt is present in a total amount of 10-30 atomic %, Y is one or more of Au, Pd, and Cu and is present in a total amount of 0 to 10 atomic %. The alloy has a matrix phase wherein the total concentration of Ni, Pt, and the one or more of Pd, Au, and Cu is greater than 50 atomic %.

Precipitation hardenable high temperature shape memory alloy

According to the invention, compositions of Ni&#x2014;Ti&#x2014;Pt high temperature, high force, shape memory alloys are disclosed that have transition temperatures above 100&#xb0; C.; have narrow hysteresis; and produce a high specific work output.

High work output NI-TI-PT high temperature shape memory alloys and associated processing methods

A nickel-base superalloy article for use in turbines has increased creep resistance and lower density. The superalloy article includes, as measured in % by weight, 6.0-12.0% Mo, 5.5-6.5% Al, 3.0-7.0% Ta, 0-15% Co, 2.0-6.0% Cr, 1.0-4.0% Re, 0-1.5% W, 0-1.5% Ru, 0-2.0%-Ti, 0-3.0% Nb, 0-0.2% Hf, 0-0.02% Y, 0.001-0.005% B, 0.01-0.04% C, and a remainder including nickel plus impurities.

Low density, high creep resistant single crystal superalloy for turbine airfoils

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.

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Strongsville, OH, United States of America

Michael V Nathal