ВЫБОР И ОПТИМИЗАЦИЯ ОСНОВНЫХ ПАРАМЕТРОВ ТУРБОКОМПРЕССОРОВ ПРИ ПРОЕКТИРОВАНИИ И ДОВОДКЕ ГТД

Abstract

The choice and optimization of the rotational speed, the number of stages, the axial velocities distribution, reactivity, diametric dimensions and flow path shape, the blade rows width, changes in the height of the flow path in the compressors and turbines of the gas turbine engine are considered. The method for determining the total pressure recovery ratio and its relationship with the efficiency of blade rows, stages, compressors and turbines is proposed. It is shown that with the same value of this indicator in these elements, the maximum efficiency of compressors and turbines in the composition of turbocompressors is achieved. It is proposed to use this indicator at an early design stage to determine the optimal stages number and the work distribution between them, the change in work along the flow path height. It is shown how the position of the points for the stages and the optimal flow path shape are determined on the Smith diagrams. Various methods are proposed for parameters choosing of the blade profiles for the first, last and for intermediate steps. It is shown how these methods are used when fine-tuning compressors and turbines based on the results of GTE tests. The results of approbation of the developed design and refinement methods are given on examples of changing the geometry of the blade rows and the flow path in the replaceable flow path of the centrifugal blower for the R-16 "Ufa" gas compressor unit, the refinement of the 3-stage LPC for perspective two spool turbofan engine, comparison with the results of simulation in the DVIGw system , 2D and 3D CAD / CAE-modeling.