Accession Number:

ADA261613

Title:

Model Fan Passage Flow Simulation

Descriptive Note:

Master's thesis

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s):

Report Date:

1992-12-01

Pagination or Media Count:

175.0

Abstract:

Two-dimensional experimental and numerical simulations of a transonic fan blade passage were conducted at a Mach number of 1.4 to provide baseline data for the study of the effects of vortex generating devices on the suction surface shock-boundary layer interaction. In the experimental program, a probe and traverse system were designed and constructed. A new data acquisition system was adapted to record data from probe measurements and multiple scans of static pressure ports. Impact pressure behind two model fan passages and static pressures across the shock-boundary layer interaction were measured for a design and one off-design flow incidence in a blow-down wind tunnel. The passage shocks were positioned in similar locations by rotating the model to a decreased flow incidence. Fan passage losses were obtained by integrating probe measurements. The losses compared favorably with a numerical Navier-Stokes solution and one engineering loss model, Static pressure distributions were also found to compare favorably with numerical results.... Shock-boundary layer interaction, Transonic fan simulation, Fan passage loss estimation, Boundary layer separation.

Subject Categories:

  • Aerodynamics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE