This paper presents an analytical method to estimate accurately the compressor air mass flow rates and high pressure turbine inlet temperature of a two spool turbofan engine on the basis of the characteristics of a high pressure turbine and a combustor. The off-design performance was used as the characteristic of a high pressure turbine. The pressune loss rates and the combustion efficiency was selected as the characteristics of a combustor. The off-design performance was analysed from the total pressure loss coefficient analysis of the stator and the blade, and design data. The pressure loss rates was acquired in the model combustor experiments. The combustion efficiency was calculated on the basis of incomplete combustion component parts of the engine exhaust gas. In this paper, this method was applied to a low bypass ratio two spool turbofan engine and compared with the model compressor test data. The results showed to be useful to estimate the turbofan engine components performance such as fan, compressor, high pressure turbine and low pressure turbine.
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