Вплив динамічних факторів на характеристики авіаційного двигуна на режимах роботи

In the range of different flow modes for selecting the dimensions of the flow part, the rotor rotation frequency, and the design of compressors and turbines, the highest tension values for the strength were considered. For turbojet bypass engines of subsonic aircraft, this mode is used to set the maximum thrust when the rotation frequency of the rotors and the temperature of the gases in front of the turbine reach maximum values. For certain turbojet bypass engines (F) supersonic aircraft, the maximum values of rotation frequency and temperature of the gases can be reached during flight. The flow parameters for all characteristic cross-sections of the engine flow part were determined by a thermodynamic structure based on the input data: basic engine data (thrust force or power, air flow consunption, bypass stage), cycle parameters, turbocharger diagram group, efficiency factor, and coefficient of expenditure in the elements of the engine flow part, as well as acceptable values of indicators that characterize the operation of nodes (limitations), including the input-output fluidity, gas-dynamic pressure coefficients, and tension parameters. This article shows the influence of the main dynamic factors on the flow parameters of aircraft engines, namely, the structural design of turbojet bypass engines with high bypass stages. Based on the constructive implementation of the concept of the development of an aircraft engine based on thrust and parameters, an algorithm for implementing the inertia of the rotors (located in the compressor module or in the turbine module) has been developed, injecting a gas-dynamic load values on the flow parameters and the values of the braking temperature in different sections of the tract. The thermal inertia of the working object at the inlet of the node, in particular, determining the time of the transient process, the instantaneous value of the temperature, and the actual temperature of the working object at the inlet of the node (module) were determined. Non-stationary heat exchange of the working object with the construction can be achieved for the smooth running of the engine in operating modes. In addition, it is necessary to evaluate the influence of the geometric dimensions of the parts of the units on the parameters of the units, namely, the calculation of the altitude and speed, throttle, and dynamic characteristics of the aircraft engine.