Numerical Investigation on the Effect of Vortex Generator on Axial Compressor Performance

Abstract

The performance of the compressor blade is considerably influenced by secondary flow effects, like the cross flow on the end wall as well as corner flow separation between the wall and the blade. The present work is focused on the studying the effects of Vortex Generator (VG) on NASA Rotor 37 test case using Computational Fluid Dynamics (CFD). VG helps in controlling the inception of the stall by generating vortices and energizes the low momentum boundary layer flow which enhances the rotor performance. Three design configuration namely, Counter-rotating, Co-rotating and Plow configuration VG are selected based on the improved aerodynamic performance discussed in reference [1]. These VG are located at 90% span and 42% chord on suction side surface of the blade. Among the three configurations, the first configuration has greater impact on the end wall cross flow and flow deflection which resulted in enhanced numerical stall margin of 5.4% from baseline. The reasons for this numerical stall margin improvement are discussed in detail.

Prediction of aerodynamic performance of NREL offshore 5‐MW baseline wind turbine considering power loss at varying wind speeds

“…With the increasing x/c , the values on the suction and pressure sides exhibited a downward trend and an upward trend, respectively, gradually converging close to 0 in the trailing edge direction (where x/c approaches 1), demonstrating a parabolic change as a whole. The analysis results indicate that the presence of a laminar separation bubble on the pressure side (where the inflow point nears the leading edge) because of high‐speed air flow and that approached 0 here 51–54 . In addition, because the shear stress of the fluid wall was dominated by the flow velocity, the distance was longer and the flow velocity was higher on the suction side, resulting in a larger .…”

“…pressure side (where the inflow point nears the leading edge) because of high-speed air flow and that C s approached 0 here. [51][52][53][54] In addition, because the shear stress of the fluid wall was dominated by the flow velocity, the distance was longer and the flow velocity was higher on the suction side, resulting in a larger C s . However, the distance was shorter, and the flow velocity was lower on the pressure side; C s was also smaller than that on the suction side.…”

Aerodynamic performances improvement of NACA 4415 profile by passive flow control using vortex generators

“…Optimal drag coefficient was obtained taking into account several parameters such as the VG height, the position from the leading edge and the aperture. The effects of VG attached at different locations and at various attack angles have been studied by Gopinathan et al (2015), Kumar et al (2016) and Agarwal et al (2016). They found that at small attack angles, the VG have insignificant effects with a small decrease in the lift force and a small increase in the drag force.…”

Empirical and Numerical Analysis of Aerodynamic Drag on a Typical SUV Car Model at Different Locations of Vortex Generator

“…The results showed that maximum drag reduction of 12% and lift reduction of 60% were attained and further reduction achieved significantly through motorization of VG with respect to wind speed. Shubham Agarwal et al (2016) investigated the aerodynamic behavior on wing with the effect of VG location. The flow field measured on the wing with VG attached at various locations and angle attack varied.…”