Accession Number:

ADA090546

Title:

The Effects of Solidity, Interblade Phase Angle and Reduced Frequency on the Time-Variant Aerodynamic Response of a Compressor Stator.

Descriptive Note:

Final rept. 1 May 79-1 May 80,

Corporate Author:

GENERAL MOTORS CORP INDIANAPOLIS IN DETROIT DIESEL ALLISON DIV

Personal Author(s):

• Jay,Robert L.
• Bennett,William A.

Report Date:

1980-06-01

Pagination or Media Count:

198.0

Abstract:

An experimental investigation was conducted to provide basic unsteady pressure distributions on a stationary vane row, with the primary source of excitation being the wakes generated from an upstream rotor. This was accomplished over a wide range of key parameters in a large-scale, low-speed, single stage compressor. The excitation, the velocity defect created by the rotor blade wakes, was measured with a crossed hot wire. The resulting time-variant aerodynamic response was measured by means of flush mounted high response pressure transducers mounted on a stator vane over a wide range in incidence angles. The dynamic data were analyzed to determine the chordwise distribution of the dimensionless dynamic pressure coefficient and aerodynamic phase lag as referenced to the transverse gust at the vane leading edge. Author

Descriptors:

• *VIBRATION
• *NONUNIFORM FLOW
• *COMPRESSOR STATORS
• FREQUENCY
• FLOW FIELDS
• HOT WIRE ANEMOMETERS
• TURBOMACHINERY
• COMPRESSOR BLADES
• PHASE SHIFT
• TEST FIXTURES
• AXIAL FLOW COMPRESSORS

Subject Categories:

• Fluid Mechanics
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE