Accession Number : AD0693658

Title :   A METHOD OF CALCULATING A RETURN-CIRCUIT RIG WITH CYLINDRICAL BLADING CONFIGURATIONS ACCORDING TO A GIVEN RADIAL PRESSURE GRADIENT,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Shnee,Ya. I. ; Boyko,A. V.

Report Date : 15 MAY 1969

Pagination or Media Count : 13

Abstract : Approximate method is presented for calculating an inverse problem of the axisymmetric flow of a compressible fluid in a blade apparatus with cylindrical boundaries and a constant blockage (the constriction of the interblade passage) along the radius t/b equals const). Since it was not possible to obtain satisfactory results by using successive approximations, the Euler motion equation including derivatives of the radial velocity component was used in this method. It is assumed that the geometrical parameters of the cascade were given and that the working medium flow rate at the mean radius practically equaled the actual flow rate. The total parameters and the distribution of the specific flow rates at the stage inlet and the compression coefficients in the cascade volume were also given. The problem was solved by using a fixed grid and by dividing the cascade meridional projections into n sections along the z-axis and into k segments along the radius. (Author)

Descriptors :   (*JET ENGINE INLETS, THREE DIMENSIONAL FLOW), COMPRESSIBLE FLOW, EQUATIONS OF MOTION, PARTIAL DIFFERENTIAL EQUATIONS, FLOW FIELDS, COMPRESSOR BLADES, INTERACTIONS, USSR

Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE