Accession Number:

ADA067969

Title:

The Influence of Compressor Inlet Guide Vane / Stator Relative Circumferential Positioning on Blade Wake Transport and Interaction.

Descriptive Note:

Interim rept. 30 Sep 77-31 Aug 78,

Corporate Author:

IOWA STATE UNIV AMES ENGINEERING RESEARCH INST

Personal Author(s):

Report Date:

1978-09-01

Pagination or Media Count:

125.0

Abstract:

A periodically sampling hot-wire measurement system was used to obtain numerous periodic-average Electronically and arithmetically averaged values of periodically sampled data three-dimensional velocity vector data for flow through the first stage inlet guide vane, rotor, and stator rows of a low-speed, multistage, axial-flow research compressor. New data are presented for the maximum noise circumferential position of the first stator blade row. Comparisons are made between these data and similar data previously acquired and reported for the minimum noise configuration of the compressor. The inlet guide vane IGV wake avenue was found to interest first stator row blades at two span locations, one near the hub and the other near the tip, for maximum noise and at only one span location, near mid-span, for minimum noise. This difference in IGV wake stator leading edge intersection patterns resulted in variations of the first stator exit flow deviation angle near the hub and tip portions of the compressor annulus. These variations were explained in terms of the larger fluctuations of stator inlet flow associated with the inlet guide vane wake avenues.

Descriptors:

• *WAKE
• *AXIAL FLOW COMPRESSORS
• *INLET GUIDE VANES
• EXPERIMENTAL DATA
• FLOW FIELDS
• HOT WIRE ANEMOMETERS
• COMPRESSOR ROTORS
• THREE DIMENSIONAL FLOW
• COMPRESSOR STATORS
• AXIAL FLOW COMPRESSOR BLADES
• COMPRESSOR NOISE

Subject Categories:

• Hydraulic and Pneumatic Equipment
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE