Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

Abstract

Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability. Aerodynamic performance of the compressor was evaluated using three-dimensional Reynolds-averaged Navier-Stokes equations using the k-e turbulence model with a scalable wall function. The numerical results for the typical performance parameters without stator splitter blades were validated in comparison with experimental data. The numerical results of a parametric study using four geometric parameters (chord length, coverage angle, height and position) of the stator splitter blades showed that the operational stability of the single-stage axial compressor enhances remarkably using the stator splitter blades. The splitters were effective in suppressing flow separation in the stator domain of the compressor at near-stall condition which affects considerably the aerodynamic performance of the compressor.

Aerodynamic and structural performances of a single-stage transonic axial compressor with blade fillet radius

“…(2019, 2021) and Pham et al . (2020a, b), is demonstrated in Figure 9, where the surface streamlines are separated or reattached on the rotor blade suction side at peak adiabatic efficiency condition. In both cases, the separation line seemed to split the rotor blade suction surface into two parts, as shown in Figure 9.…”

Large-Eddy Simulation of Flow Separation Control in Low-Speed Diffuser Cascade with Splitter Blades

“…This model provides a solution for the design of an ultra-high-loaded axial compressor. Pham [27] installed splitter blades to the stator of a single-stage axial compressor, effectively improving the operation stability. The splitter blades effectively restrained the flow separation in the stator at near-stall conditions.…”