EFFECT OF TIP CLEARANCE AND ROTOR-STATOR AXIAL GAP ON AXIAL COMPRESSOR PERFORMANCE

Abstract

The goal of this thesis is to expand on current understanding about tip clearance and rotor-stator axial hole on engine performance, with a focus on faster-equipment components (i.e. enthusiasts or compressors). Various high-fidelity three-dimensional Computational Fluid Dynamics (CFD) models have been developed using a transonic compressor degree (i.e. NASA stage 37). The current research focuses on the effect of rotor tip clearance on the degree of a transonic axial compressor. Because of the relative motion between the rotor and stator blades, the float subject on this equipment is very unstable.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 utilising 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.