Assessing reduction gear mass in the problem of optimizing parameters of the working process of a turboprop engine at the initial design stage

The paper analyzes mathematical models of the mass of the reduction gear as part of a turboprop engine power plant in the problem of optimizing the parameters of the working process of the gas turbine engine at the initial design stage. The necessity of optimal matching of the main parameters of the power plant and the aircraft based on their system performance criteria is the main feature of the initial design of turboprop engines. To solve the problem of optimizing the parameters of the engine work process, under certain design constraints, it is important to know the take-off weight of the aircraft in the formation of which the weight of the power plant with a turboprop engine is one of important components that actually determine the coordination of the aircraft and engine parameters. The mass of the reduction gear of a turboprop engine makes up a significant part of the power plant mass. The existing models of the mass of the power plant with a turboprop engine do not separate the weight of the gear from the weight of the power plant. Thereby, the reduction gear weight is erroneously associated with gear parameters used in the model of the mass of the engine. This does not include the obvious dependence of the gear mass on the transmitted power which is closely linked to the distribution of the free energy of the turboprop engine.