Abstract
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 heat exchanger, combined with a double-decked 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.
Cite
CITATION STYLE
Shapiro, J., & Levy, A. (1990). Gas turbine with intermediate heat exchanger for flight application. In Proceedings of the ASME Turbo Expo (Vol. 2). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/90-GT-197
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