Investigation of the Flow Field and Aerodynamic Load on Impellers under Guide Vanes with a Self-Induced Slot in Compressor Radial Inlet

Abstract

The flow field and the efficiency of the compressor can be improved and increased by the guide vane in the radial inlet chamber. However, the guide vane generates the wake and results in the rotor–stator interaction, which threatens the safety of the impeller. This paper investigated the guide vane with a self-induced slot (SIS) in a radial inlet, and the self-induced slot was a passive flow control method. Through computational fluid dynamics (CFD) simulation, the radial inlet containing unevenly distributed guide vanes (UGVs) in the hydrogen compressor was studied to clarify the flow phenomenon in the radial inlet and the aerodynamic load on the impellers. The simulation results showed that the self-induced slot did not affect the compressor performance but improved the pure wake style to the weak wake near the shroud region. The aerodynamic load on the impeller leading edge was obtained under different radial inlets through unsteady simulation. The dominant frequency and the pulse amplitude of aerodynamic load were obtained by fast Fourier transforms (FFTs). The SIS model had lower amplitude values at the impeller passing frequency, and the reduction in amplitude was about 18% compared to the UGV model near the impeller shroud region.

Angle-Regulating Rule of Guide Vanes of Variable Geometry Turbine Adjusting Mechanism

“…A numerical simulation of multihole impingement cooling of a turbine guide vane cavity [12] with a complex pin fin structure was conducted. Xin et al [13] carried out a numerical simulation of a radial intake chamber with guide vanes with self-guide grooves. Guide vanes could improve and enhance the flow and efficiency of the airflow within the compressor.…”

Numerical study on the effect of radial inlet chamber on the performance of oblique flow compressor

“…Grimaldi [10] experimentally tested the overall performance of compressor units with different RIC models and found that there needed to be a balance between the complexity of the RIC structure and the impact on first-stage performance. Xin [11] numerically calculated compressor with uneven guide vanes and the results show that the guide vanes wake and the pressure load threaten the impeller safe operation. Pazzi [12] tested the performance of a typical RIC through numerical simulation and experiment, and found that the number and structure of shunt blades in the RIC have a great influence on the flow field, mainly because it can change the distribution of aerodynamic parameters in the tangential direction.…”