Advanced Auxiliary Power System
Final technical rept. Nov 1968-May 1972
AIRESEARCH MFG CO OF ARIZONA PHOENIX
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The purpose of the program was to advance the technology of small Auxiliary power units, using the secondary power system requirements of a hypothetical fighter aircraft of mid-1970 as a goal and an auxiliary power system as a test bed for exploratory development. The APU was 10 in. in diameter by 24 in. long, and the design-point performance goal was 300 equivalent shaft horsepower at 2200F turbine inlet temperature and sea level, 130F ambient conditions. Other design-point goals included an 111 cycle pressure ratio, 55- lbmin bleed-air at 61 pressure ratio, and a total system weight under 200 lb, including the starting system. The program resulted in technological advancements in the axial-centrifugal compressor, including variable inlet guide vanes, uncooled 2200F combustion, an advanced radial in-flow cooled-turbine, uncooled columbium nozzles, and an advanced high-speed torque converter with lockup feature.
- Attack and Fighter Aircraft
- Electric Power Production and Distribution