Tereshchenko I. Conception of integration of power plant with turbofan unit and aircraft

The concept of aerothermogasdynamic integration of a double bypass gas turbine engine with a turbofan unit and a stepped engine nacelle of an aircraft power plant is scientifically grounded in the work. A scientific and methodological apparatus has been created for analyzing the process of aerothermogasdynamic integration of multi-pass turbojet engines with a rear-mounted turbofan unit and engine nacelle of an aircraft power plant. The theoretical foundations of aerothermogasdynamic integration of a multi-pass turbojet engine with a turbofan unit and a power plant nacelle with boundary layer control on the surface of the engine nacelle of a gas generator module have been created. Based on the results of computational and experimental studies, recommendations were obtained to justify the requirements for aerothermogasdynamic integration of a stepped engine nacelle and gas turbine engine with a turbofan unit of an aircraft power plant and determine the optimal values of the process parameters of a of double bypass gas turbine engine in accordance with the calculated flight conditions.