Transactions of Nanjing University of Aeronautics & Astronautics
Component Matching Based on Low Bypass Ratio Mixed Exhaust Turbofan Engine
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Abstract:
In order to study component matching which exists in off-design situation at the initial design stage of turbine engine, by establishing performance analysis model of low bypass ratio mixed flow turbofan engine and components characteristic data, and by applying Newton-Raphson method to solve the nonlinear equations of off-design points in flying envelop, the factors which affect matching between engine components are studied. The results show that low pressure turbine (LPT) must not operate in a critical condition, and the partial derivative (slope) of pressure ratio to similitude mass flow ratio of working point in LPT characteristic map affects the stability of engine. The smaller the slope is, the more stable the engine is. In addition, the engine is more stable when the fan characteristic map is steep.
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This work was supported in part by the Fundamental Research Funds for the Central Universities(No.NZ2016103).
Clc Number:
V231.3
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