High power/weight ratio and low SFC are the most important requirements for an airborne engine. This may be achieved by a gas turbine engine with an intermediate test exchanger, combined with a double-dected compressor-turbine design. In this engine, the specific fuel consumption is minimal at 70 % of maximum power-output for best fuel economy in helicopter engines. The additional weight, due to its design, is compensated by fuel saved in less than one hour flight for a 926 kW cruise power engine. This paper describes a gas turbine with an intermediate heat exchanger as proposed by Shapiro et al (1985). It creates a significant decrease of the engine SFC and increase of power/weight ratio when compared to conventional regenerative and nonregenerative gas turbines. In addition, an integral axial compressor-axial turbine unit further decreases the overall engine length and weight.
Gas turbine with intermediate heat exchanger for flight application
Gasturbine mit Zwischenwärmetauscher für Flugzeuge
ASME-Papers ; 1-4
1990
4 Seiten, 6 Bilder, 2 Tabellen, 5 Quellen
Conference paper
English
Automotive gas turbine heat exchanger development
Automotive engineering | 1996
|Automotive Gas Turbine Heat Exchanger Development
SAE Technical Papers | 1996
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