HIGH ALTITUDE PERFORMANCE TESTING DEVICE AND PRESSURE CONTROL METHOD FOR THE SAME

摘要

PROBLEM TO BE SOLVED: To provide a reliable high altitude performance testing device and a pressure control method for the same capable of precisely keeping internal pressure at a predetermined test pressure in corresponding to the variation of the exhaust gas quantity in an engine performance test and capable of continuously testing stably for a long period of time without possibility of surge and choke. SOLUTION: Gas in a sealed chamber 10 housing an aircraft engine 1 is sucked, compressed to atmospheric pressure and discharged to an outside by an axial compressor 12. Fresh air quantity supplied to the inlet side of the axial compressor 12 is simultaneously controlled to maintain a pressure ratio of the axial compressor constant. COPYRIGHT: (C)2005,JPO&NCIPI