The main aim of this paper is the development of an integrated solver for the optimization of the cycle, the size and the weight of a gas turbine engine. The solver is based on the Genetic Algorithm techniques. The selected engine configuration is a two spool, separated flow turbofan with a low pressure compressor linked to the fan. The problem is to find the values of some parameters of engine cycle optimizing some engine performance and geometric parameters. The considered cycle parameters are: the by pass ratio, the presure ratio of fan, low and high pressure compressor and the turbine inlet temperature. The engine parameters are the specific thrust, the Specific Fuel Consumption (SFC), the cold and hot specific exhaust area (A8/m0 e Ai9/m0), the engine lenght, the thrust to weight ratio, etc. The paper shows some examples of solver application by carrying out both single target and multi target optimization processes.
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