Test Results from an Analytically Designed Axial Compressor Stage of 1.65:1 Pressure Ratio

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.