Model fan passage flow simulation
Myre, David D.
Shreeve, Raymond P.
Hobson, Garth V.
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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 transverse system were designed and constructed. A new data acquisition system was adapted to record data from probe surveys 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 incidence and one off-design 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 the probe measurements. The losses compared favorably with a numerical Navier-Stokes solution and one engineering model. Static pressure distributions were also found to compare favorably with numerical results.
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