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Integrated Accessory Systems for Small Gas Turbine Engines
Final rept. 1 May 1973-30 Jun 1975
PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FL FLORIDA RESEARCH AND DEVELOPMENT CENTER
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The intent of the Integrated Accessory Systems for the Small Gas Turbine Engines Program was to optimize the controls and accessory systems for the next generation of small turboshaft gas turbine engines for Army helicopter applications. A 1977 development time frame was considered. A primary objective of the program was to reduce vulnerability of the controls and accessory components without severely compromising other important design criteria. During the Phase I conceptual design phase, analyses and preliminary designs of Control and Accessory C and A configurations for both front- and rear-drive engines were accomplished. Phase II included preliminary design of two candidate control and accessory systems and selection of one system for detailed design. A tower shaft control and accessory drive with an air turbine starter was selected, and a detailed system design of all C and A components was accomplished. The critical items of the C and A system were identified and test programs were recommended for Phase III. Phase III included testing of the following critical items 1 fuel pump inducer inlet suction tests, 2 high-speed oil pump cavitation tests, 3 electronics cooling techniques performance tests, 4 power turbine overspeed sensor performance tests, and 5 starter overrunning clutch endurance tests.
APPROVED FOR PUBLIC RELEASE