Abstract
On the basis of a performance emulation model of turbofan engine, a relation curve was first employed to fix the efficiency of compression components. With the turbine blade cooling efficiency being a restriction, an optimization algorithm was developed on the premise that engine cycle parameters match. The calculation results show that when the turbine blade cooling efficiency was improved at a fixed bypass ratio, the engine overall pressure ratio corresponding to the lowest specific fuel consumption (sfc) grows on a large scale, while the lowest sfc slightly drops and the specific thrust significantly boosts.
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