CFD Analysis of Tip clearance and axial rotor-stator gap on the performance of axial Compressor

Abstract

A transonic compressor degree has been used to develop various high-fidelity three-dimensional Computational Fluid Dynamics (CFD) models (i.e. NASA stage 37). The current investigation focuses on the impact of rotor tip clearance in a transonic axial compressor degree. The float subject on this machinery is extremely unstable because to the relative motion between the rotor and stator blades. Furthermore, the device is complicated by a variety of technological consequences such as tip clearances, blade complexity, and axial distance variations between the stator and rotor. As a result, one of the most challenging tasks a CFD professional can accomplish is to investigate a complicated, strongly 3-dimensional flow discipline inside a compressor. The NASA 37 transonic axial compressor degree with a rotor tip clearance of 0.5mm is investigated utilizing numerical simulations using the ANSYS CFX software package. All simulations for the first stage, Rotor–Stator, were run. The experimental investigation and the standard performance parameters acquired from modelling of tip clearance were found to be in good agreement.