Calculation Analysis of an Axial Compressor Supersonic Stage Impeller

There is an evident trend to elevate pressure ratio of a
single stage of a turbo compressors - axial compressors in particular.
Whilst there was an opinion recently that a pressure ratio 1,9 was a
reasonable limit, later appeared information on successful modeling
tested of stages with pressure ratio up to 2,8. The authors recon that
lack of information on high pressure stages makes actual a study of
rational choice of design parameters before high supersonic flow
problems solving. The computer program of an engineering type was
developed. Below is presented a sample of its application to study
possible parameters of the impeller of the stage with pressure ratio
3,0. Influence of two main design parameters on expected efficiency,
periphery blade speed and flow structure is demonstrated. The results
had lead to choose a variant for further analysis and improvement by
CFD methods.

• Y. B. Galerkin
• E. Y. Popova
• K. V. Soldatova

• Supersonic stage
• impeller
• efficiency
• flow rate coefficient
• work coefficient
• loss coefficient
• oblique shock
• direct shock.

[1] Galerkin, Y.B Turbocompressors. - Мoscow. - 2010. – С. 596. (in
Russian)
[2] Galerkin Y. B., Popov Y. A. Optimization of the axial compressors flow
path at a stage of candidates’ comparison. Part 1. // Compressors &
Pneumatics. – Moscow. - 2009. – No.5. – P.2-9 (in Russian).
[3] Galerkin Y. B., Popov Y. A. Optimization of the axial compressors flow
path at a stage of candidates’ comparison. Part 2. // Compressors &
Pneumatics. – Moscow. - 2009. – No.6. – P.1-19 (in Russian).
[4] Galerkin Y. B., Popov Y. A. Optimization of the axial compressors flow
path at a stage of candidates’ comparison. Part 3. // Compressors &
Pneumatics. – Moscow. - 2009. – No.7. – P. 6-12 (in Russian).
[5] Komarov A.P. Axial blade cascades test. Turbo machines and jet
apparatus. – Moscow. –1967. – С. 67-110. (in Russian).