A single stage axial compressor was designed for 1.53:1 pressure ratio using a quasi-three dimensional design method which consists of an iterative calculation between the radial equilibrium and blade-to-blade analyses including surface boundary layers.This stage was tested in place of the production first stage of a three stage axial combined with a single stage centrifugal (3A+1C) compressor in a research gas generator. Based on stator exit traverses, the research stage reached 87.8% adiabatic efficiency and 1.65:1 pressure ratio at the design speed. The overall compressor efficiency improved significantly at high speeds in comparison with the existing 3A+1C compressor, without any obvious performance deterioration at part speed.Some aspects of the design method are discussed and the test results are presented in this paper.
Test Results from an Analytically Designed Axial Compressor Stage of 1.65:1 Pressure Ratio
Sae Technical Papers
Turbine Powered Executive Aircraft Meeting ; 1980
1980-04-01
Conference paper
English