High altitude long endurance unmanned aircraft impose unique contraints on candidate engine propulsion systems and types. Piston, rotary and gas turbine engines have been proposed for such special applications. Of prime importance is the requirement for maximum thermal efficiency (minimum specific fuel consumption) with minimum waste heat rejection. Engine weight, although secondary to fuel economy, must be evaluated when comparing various engine candidates. Weight can be minimized by either high degrees of turbocharging with the piston and rotary engines, or by the high power density capabilities of the gas turbine. The design characteristics and features of a conceptual high pressure ratio intercolled turboprop are discussed. The intended application would befor long endurance aircraft flying at an altitude of 60.000 ft. (18.300 m). It is estimated that such a turboprop would be capable of thermal efficiencies exceeding 40 % with current state-of-the-art component efficiency levels and an overall compressor pressure ratio of 66.0. Projected Power (at altitude) to weight ratio is comparable to that of competitive piston and rotary engines.
High pressure ratio intercooled turboprop study
Studie einer Propellerturbine mit Zwischenkühlung und hohem Druckquotient
1992
11 Seiten, 12 Bilder, 2 Tabellen, 8 Quellen
Aufsatz (Konferenz)
Englisch
High Pressure Intercooled Turbine Engine Concept
SAE Technical Papers | 1988
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