Self-driven fan large-bypass-ratio turbofan engine with inner loop air turbine
A turbofan engine and air turbine technology, applied in the direction of machines/engines, jet propulsion devices, etc., can solve problems such as inability to make contributions to connotation economy, complex rotor dynamics, difficult manufacturing of fans and turbines, etc., to reduce technology Risk and Development Cost, Avoiding Rotordynamic Problems, Effect of Solving Speed Mismatch Problems
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[0035]For a twin-rotor turbofan engine, the total flow rate is 95.3kg / s, the internal total pressure ratio is 23, the external total pressure ratio is 1.7, the bypass ratio is 5.3, the maximum thrust is 2546.6dN, and the corresponding fuel consumption rate is 1.05kg / (dN *h). After the modified design according to the method proposed by the present invention, the total pressure ratio of the outer culvert is 1.2, and the bypass ratio is 14.3. Through the calculation of the overall performance, the maximum thrust is 3703.1dN, corresponding to the fuel consumption rate of 0.72kg / (dN*h), and the thrust ratio of the prototype The turbofan engine has increased by 45.4%, and the fuel consumption rate has decreased by 31.4%, and the performance has been greatly improved.
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