Effect of the end-wall vortex generator jets on the performance of a high subsonic compressor cascade

Abstract

This paper presents a numerical and experimental result of the end-wall vortex generator jets for controlling corner separation and enhancing the aerodynamic performance in a high subsonic (Ma = 0.7) compressor cascade. The experiments were carried out on a compressor cascade at design point ( i = 0°) and off-design points ( i = −2°, 2°, and 4°). At design point, the total pressure loss coefficient could be reduced up to 12.1%.With the increase in the incidence, the control effect is enhanced first and then reduced. The maximum total pressure loss reduction is up to 14.6% when the incidence is 2°. The numerical study is further conducted to analyze the flow pattern and the vortex structure. The jet vortex is formed downstream of the jet hole using the vortex generator jets, the cross flow on the end wall is also suppressed.

Optimization of the hole exit shape of the vortex generator jets in a compressor cascade

“…More comparison of experiments and numerical results can be found in the reference. 22 In general, the used numerical method is feasible and meets the requirements of this study.…”

“…In order to verify the accuracy of the numerical methods, the same simulation conditions with 14,22 are used. Figure 7 shows the distribution of the outlet total pressure loss coefficient of the experimental and numerical results for both baseline and VGJs cases.…”