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Supersonic axial compressor stage simplified analysis.

Number: pap. 1165

Author(s) : GALERKIN Y. B., SOLDATOVA K. V.

Summary

Supersonic axial stages with big pressure ratio are increasingly in demand. There is a problem to elevate pressure ratio of a stage up to 3 and more. Efficiency of a stage can be limited by shock wave losses at high supersonic speeds. The numerical analysis of losses was made in a plane cascade. Calculated losses in shock waves depend on a velocity coefficient and an angle of a shock wave. Pressure loss calculation in subsonic parts of a stage was made by a loss coefficient. Its value was chosen by an expert assessment. It is shown shock that wave losses are not an obstacle for an acceptable level of stage efficiency up to a velocity coefficient value 1.5.

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Pages: 10 p.

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Details

  • Original title: Supersonic axial compressor stage simplified analysis.
  • Record ID : 30013868
  • Languages: English
  • Source: 2014 Purdue Conferences. 22nd International Compressor Engineering Conference at Purdue.
  • Publication date: 2014/07/14

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