Accession Number : AD0379802

Title :   STUDY PROGRAM FOR TURBO-COOLER FOR PRODUCING ENGINE COOLING AIR.

Descriptive Note : Final rept. 1 Nov 65-30 Nov 66,

Corporate Author : GENERAL APPLIED SCIENCE LABS INC WESTBURY N Y

Personal Author(s) : Nathan,I. ; Panunzio,S. ; Recarey,M.

Report Date : FEB 1967

Pagination or Media Count : 124

Abstract : A study has been made of potential systems for cooling hypersonic vehicles. The systems studied employ a supersonic turbine which lowers the free stream stagnation air temperature by extracting shaft power, which may be utilized in several ways. Various cycles with and without heat exchangers were studied. The cooling, structural, bearing and seal problems associated with such systems were considered. Aerothermodynamic design data charts are presented. (Author)

Descriptors :   (*HYPERSONIC AIRCRAFT, COOLING + VENTILATING EQUIPMENT), (*GAS TURBINES, COOLING + VENTILATING EQUIPMENT), HYPERSONIC FLOW, AIR COOLED, AIRCRAFT ENGINES, FEASIBILITY STUDIES, PRESSURE, SUPERSONIC CHARACTERISTICS, DESIGN, HEAT EXCHANGERS, COOLING (U) AXIAL FLOW TURBINES, DUCT INLETS, INLET GUIDE VANES, STAGNATION POINT, DECELERATION, ACCELERATION, SUPERSONIC DIFFUSERS, TURBINE BLADES, EVAPOTRANSPIRATION, LIQUID COOLED, HEAT TRANSFER, GAS BEARINGS, SEALS

Subject Categories : Aircraft
      Air Condition, Heating, Lighting & Ventilating

Distribution Statement : APPROVED FOR PUBLIC RELEASE