A study was conducted to determine the suitability of an advanced technology Regenerated Intercooled Turbine Engine (RITE) for aircraft propulsion. A cycle performance analysis was conducted for a 250 shp, 25000 ft cruise turboprop engine for a pressurized twin engine six-place turboprop aircraft. The RITE engine cycle consists of a two-stage compressor with a rotary intercooler, gas generator turbine driving the compressors, a combustor, rotary regenerator, and power turbine. Cycles were analyzed over a range of design-point pressure ratios and heat exchanger sizes at a turbine inlet temperature of 2500 F. An aircraft and its flight characteristics were defined to evaluate candidate engines on the basis of prescribed mission fuel consumption. After preliminary design selection, a life cycle cost analysis was performed in which the reference engine was compared to a conventional turboprop engine. The selected engine design achieves a cruise specific fuel consumption of 0.252 lb/hp-hr which is about half that of a conventional engine with the same power rating. The predicted life cycle cost of the engine is lower without an intercooler, due to marginal improvement in cycle efficiency contributed by intercooling.
Regenerative intercooled turbine engine (RITE) study
Regeneratives Turbotriebwerk mit Zwischenkuehlung (RITE) Studie
AIAA-Papers ; 1-10
1984
10 Seiten, 13 Bilder, 7 Tabellen, 4 Quellen
Aufsatz (Konferenz)
Englisch
Regenerative Intercooled Turbine Engine (RITE) study
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