Расчет степени двухконтурности ТРДД

Abstract

It is shown that the bypass ratio turbojet engine (turbojet) depends on the change of thermodynamic parameters of the air at a height оflan blades. When calculating the degree of bypass of the modern method, it is constant regardless off an speed and is determined only by the ratio of airspace for the first and second circuits. Accounting for non-uniformity of the flow of air on the fan blade height to determine changes in bypass ratio turbofan engines with throttling.