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Evaluation and Test of a Liquid Metal Coupled Regenerator System for Aircraft Turboshaft Engines
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English
Abstract
The theoretical and practical aspects of applying liquid metal coupled regenerators to aircraft gas turbine shaft engines are discussed. The results of parametric studies for determining optimum heat exchanger surface geometries for a typical 1000 hp engine are presented. The design integration of the regenerator in the powerplant is described. The results of a test program on a specially designed liquid metal regenerator system demonstrate the feasibility and performance of such a system for aircraft turbine engines.
Authors
Citation
Lombardo, S., "Evaluation and Test of a Liquid Metal Coupled Regenerator System for Aircraft Turboshaft Engines," SAE Technical Paper 630492, 1963, https://doi.org/10.4271/630492.Also In
References
- London A. L. Kays W. M. “Liquid-Coupled Regenerators for Turboprops,” Aeronautical Engineering Review 1952
- Ferris J. R. TREC Technical Report 61-46 “Liquid Metal Regenerator Feasibility Study for a Lightweight Turboshaft Engine,” U. S. Army Transportation Research Command, Fort Eustis, Virginia April 1961
- Barnes D. R. Cherish P. Cox L. R. Kump D. J. TREC Technical Report 61-47, “Engine Test and Evaluation Report, Liquid Metal Regenerator for a Lightweight Turboshaft Engine,” U.S. Army Transportation Research Command, Fort Eustis, Virginia November 1961
- “Liquid Metals Handbook,” Sodium-NaK Supplement, TID 5277, A. E.G., Department of the Navy, Washington, D. C., July 1955
- Liquid Metals Inc., Technical Brochure FSEC-54-3 (a), Box 266, Westford, Mass.