Accession Number:

ADA277234

Title:

Development of a Cascade Simulation of Fan-Passage Flow

Descriptive Note:

Master's thesis

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s):

Report Date:

1993-12-01

Pagination or Media Count:

139.0

Abstract:

A small-scale blowdown wind tunnel apparatus was developed to investigate techniques to alleviate the negative effects of shock-boundary layer interaction in the blading of aircraft engine fans. Using shadowgraph and surface injection techniques, probe surveys and static pressure measurements, it was shown that acceptable periodicity and repeatability could be obtained in a two-passage cascade model at M1.4 if air supply pressure, back pressure and porous-wall bleed pressures were properly controlled. It was also shown that local separation due to shock boundary layer interaction was present at the design flow incidence of 1. 15 degrees, but not at 0.85 degrees. Complete data are reported for the design condition to serve as a baseline for separation alleviation experiments. Necessary hardware and software developments are also documented. Shock-boundary layer interaction, Transonic fan simulation, Boundary layer separation.

Subject Categories:

  • Air Conditioning, Heating, Lighting and Ventilating
  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE