Separated Flow in a Low-Speed Two-Dimensional Cascade: Part II—Cascade Performance

Abstract

This study was conducted for the purpose of providing a more fundamental understanding of separated flow in cascades and to provide performance data for fully stalled blade rows. Cascades of a single blade geometry and a solidity of unity were studied for three stagger angles and the full range of angle of attack extending well into the stalled flow regime. The Reynolds number was also varied for a limited number of cases. Results from velocity and pressure measurements made in the cascade and the overall cascade performance evaluated from these measurements are presented. In addition, results from a numerical simulation of the flow through a cascade of flat plate airfoils are used to illustrate further the effects of blade stagger and to define the correct limits for the cascade performance. The results indicate that the slope of the total pressure loss versus angle of attack curve for the flow immediately downstream of the cascade is steeper for cascades with greater stagger. The normal force coefficient was found to increase to a peak value near the angle of attack where full leading edge stall first occurs. A further increase in angle of attack results in a decline in the normal force coefficient. The peak value of the normal force coefficient is greater and occurs at a higher angle of attack for the cascades with smaller stagger.

Oblique inlet pressure loss for swirling flow entering a catalyst substrate

“…The dotted line corresponds to a substrate length of L/d = 10. This model is better suited for turbulent flow, as confirmed by some sources[8,15].…”

Budget Analysis of Turbulent Kinetic Energy in Corner Separation : Rans vs Les

“…For a compressor it occurs at the junction of the end-wall and the blade suction side. The corner separation has been investigated experimentally on linear compressor cascades [3,4,2,5], and numerically [6], but its physics is not yet entirely understood.…”