In the development phase of an aircraft gasturbine, the required performances of the gasturbine components, for example fan, compressor, combustor and turbine, are decided after general consideration of the engine total performance. In case of compressor the design value of mass flow, compression ratio, efficiency, and surge margins correspond to these component performances. For accomplishing the required performance, the tedious and expensive works of design for modification, production and tests were laboriously repeated as in the past. As efficiently promoting these development cycle, it is important to get the useful data for two purposes, one is redesign for getting better performance and the other is to fix variable factors adjusting the difference from design values. This paper introduces the practical and useful method describing the relation between component performances of the compressor and the combination of the stator setting angle analyzing by statistical methods based on the experimental data.
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