Flow Angularity and Swirl Flow Analysis on Transonic Compressor Rotor by 1-Dimensional Dynamic Turbine Engine Compressor Code and CFD Analysis

Abstract

The performance and stability of a low-bypass turbofan transonic axial compressor with a nonuniform inlet flow is a significant concern in recent times. In both military and commercial aircraft, serpentine ducts produce significant inlet swirl distortion. Moreover, the nonuniform inlet flow frequently acts upon aircraft gas-turbine engines causing deteriorating effects on the aircraft engine. High circumferential swirl flows and inlet flow angularity decrease the aerodynamic performance and the stall margin and increase the rotor blade loading. The current paper is aimed at the investigation of the flow field in the tip clearance region of low-bypass turbofan transonic compressor rotor under nonuniform circumferential flow conditions through numerical simulation using Ansys CFX. The mathematical models based on 1D Mean Line Code and Dynamic Turbine Engine Compressor Code (DYNTECC) are used to analyze the nonuniform inlet swirl flow of the compressor rotor. The mathematical model is limited to compute the multistage compressor characteristics for the compression system and the combustor of a turbine engine. For the single-stage swirl flow analysis current paper focuses on the CFD based results. The results based on CFD show that co-swirl patterns slightly improve the stability range of the compressor; counter-swirl flows diminish it.