Accession Number:

ADA071878

Title:

The Effect of Interblade Phase Angle and Solidity on the Time-Variant Aerodynamic Response of a Compressor Stator.

Descriptive Note:

Interim rept. 1 May 78-1 May 79,

Corporate Author:

GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV

Personal Author(s):

Report Date:

1979-06-01

Pagination or Media Count:

55.0

Abstract:

The overall objective of this experimental program was to quantify the effects of the reduced frequency as well as the interblade phase angel and associated solidity variations on the fundamental time-variant aerodynamics relevant to forced response in turbomachinery. This was accomplished in a large, low speed, single-stage research compressor which permitted variation of the interblade phase angle and solidity by varying the number of rotor to stator blades. A single value of interblade phase angle, 36 degrees and a corresponding value of solidity of .758, the aerodynamically induced fluctuating surface pressure distributions on the downstream vane row, with the primary source of excitation being the upstream rotor wakes, were measured over a wide range of compressor operating conditions. The individual vane surface data were investigated to determine the effect of interblade phase angle and solidity on the overall unsteady pressure magnitude as well as to determine the dynamic pressure coefficient and aerodynamic phase lag for the unsteady pressure differential across the vanes. The unsteady pressure differential data were correlated with predictions from a state-of-the-art flat plate cascade transverse gust analysis. Author

Subject Categories:

  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE