The study of a Turbine Bypass Remote Augmentor Lift System for V/STOL Aircraft was designed to identify the most promising turbine bypass engine (TBE) cycle for combination with a remote augmentor lift system (RALS) and to evaluate the merits of this combination relative to other V/STOL propulsion concepts. Engine cycle selections were based on compromise between hover balance and high-speed performance characteristics. Three candidate TBE cycles selected for study were: 15-percent-bleed TBE with simple RALS, 30-percent-bleed TBE with simple RALS and 15-percent-bleed TBE with a turbo-compressor-RALS combination. Conventional turbofan-RALS and lift-plus-lift/cruise (L+LC) concepts provided bases for comparison. A preliminary engine design was developed for each propulsion concept and integrated into a airplane configuration design. The performance of each airplane was analyzed using methods appropriate for the conceptual design level. All of the aircraft were resized for equivalent capability using a supersonic deck-launched intercept (DLI) mission, specified combat performance and hover load capability. Fair comparisons could then be based on takeoff gross weight (TOGW) and life-cycle cost (LCC). The turbo-compressor RALS design was chosen as the best TBE-powered concept based on TOGW, LCC and alternate mission perfomance, as well as operational design considerations. Sizing and performance results, together with studies of variations of design groundrules and mission requirements, indicate that overall this TBE-RALS configuration was superior to the turbofan-RALS design and competitive with L+LC.
Study of turbine bypass remote augmentor lift system for V/STOL aircraft
Untersuchung eines Mantelstromtriebwerks als getrennter Steigfaehigkeitsverstaerker fuer Senkrechtstarter
AIAA-Papers ; Okt ; 1-13
1985
13 Seiten, 15 Bilder, 5 Tabellen, 8 Quellen
Conference paper
English