Model Fan Passage Flow Simulation
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1992
- Accession Number
- ADA261613
Entities
People
- David D. Myre
Organizations
- Naval Postgraduate School