Devising a method for calculating the turboshaft gas turbine engine performance involving a blade-by-blade description of the multi-stage compressor in a two-dimensional setting

The design and adjustment of modern gas turbine engines significantly rely on the use numerical research methods. This paper reports a method devised for calculating thermogasdynamic parameters characteristics turboshaft engine. special feature given is two-dimensional blade-by-blade description compressor in engine system. Underlying calculation nonlinear mathematical model that makes it possible to describe established processes occurring individual nodes general. To build model, modular principle was chosen, involving construction system interrelated coordinated models their elements. approach used modeling flow estimate by significant number characterize its operation. With help reported method, effect changing geometric height take into consideration influence variable modes air intake or overflow various cross-sections along tract, determine input radial unevenness verify described, throttle single-stage with 12-stage axial performed. Comparison results experimental data showed satisfactory convergence. Thus, standard deviation from 0.45 % characteristics, 0.4 power, 0.15 specific fuel consumption. Development improvement methods make improve quality competitiveness locally-made aircraft engines.