Book Description
The General Aviation Propulsion (GAP) Program Turbine Engine Element focused on the development of an advanced small turbofan engine. Goals were good fuel consumption and thrust-to-weight ratio, and very low production cost. The resulting FJX-2 turbofan engine showed the potential to meet all of these goals. The development of the engine was carried through to proof of concept testing of a complete engine system. The proof of concept engine was ground tested at sea level and in altitude test chambers. A turboprop derivative was also sea-level tested. Glenn Research Center TURBOFAN ENGINES; TURBINE ENGINES; ENGINE DESIGN; GENERAL AVIATION AIRCRAFT; PROPULSION; THRUST-WEIGHT RATIO; ALTITUDE TESTS; PRODUCTION COSTS; TEST CHAMBERS; FUEL CONSUMPTION
