IMPROVEMENT OF CALCULATION METHOD OF LOSSES IN THE ELEMENTS OF FLOW PART OF ENGINES USING EXPERIMENTAL DATA
Presented improvement of the method of the equivalent diffuser which is widely used for calculations of losses in the diffuser channels of gas turbine engines (GTE) and products of rocket and space technology (RST). The method is improved for calculation of the diffuser channels of complex geometry that connects the turbine at different diameters and having a large taper area of the flow. The improvement is made of using data from experimental studies performed on the model of the diffuser in conditions as close as possible to his field work as part of GTE. The comparison of the coefficients of the recovery of the total pressure are experimentally studied the diffuser channel with the values obtained by the method of equivalent diffuser. The specification method is equivalent to the diffuser produced from the coefficients of the amendment, determined for different angles of the equivalent diffuser and in a wide range of modes of GTE.