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Progress in the Utilization of an Oxide-Dispersion-Strengthened Alloy for Small Engine Turbine Blades
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Abstract
The conventional means of improving gas turbine engine performance typically involves increasing the turbine inlet temperature; however, at these higher operational temperatures the high pressure turbine blades require air-cooling to maintain durability. But air-cooling imposes design, material, and economic constraints not only on the turbine blades but also on engine performance.
The use of uncooled turbine blades at increased operating temperatures can offer significantly improved performance in small gas turbine engines.
A program to demonstrate uncooled MA6000 high pressure turbine blades in a GTEC TFE731 turbo-fan engine is being conducted under contract to NASA-Lewis Research Center (NAS3-20073). The project goals include demonstration of the advantages of using uncooled MA6000 turbine blades as compared with cast directionally solidified MAR-M 247 blades.
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Citation
Beatty, T. and Millan, P., "Progress in the Utilization of an Oxide-Dispersion-Strengthened Alloy for Small Engine Turbine Blades," SAE Technical Paper 841512, 1984, https://doi.org/10.4271/841512.Also In
References
- Benjamin J.S. “Dispersion Strengthened Superalloys by Mechanical Alloying“” Met. Trans. 1 Oct. 1970
- Benjamin J.S. Cairns R.L. “Elevated Temperature Mechanical Properties of a Dispersion Strengthened Superalloy“” Modern Development in Powder Metallurgy Hausner H. 1971
- INCO Alloy MA6000 Huntington W. Va.
- Tien J.K. “Alloy Design with Oxide Dispersions and Precipitates” Fundamental Aspects of Structural Alloy Design Jaffee R.I. Wilcox B.A. 1977
- GTEC NASA/MATE Project IV Quarterly Report No. 92 October 1983
- Glasgow T.K. “Creep Shear Behavior of the Oxide Dispersion Strengthened Superalloy MA6000E” NASA TM-82704 1981