Flow field investigations in the free bypass jet flow of a V2527 engine at Ground Operation using SPIV

Abstract

The investigation of the flow field at the nozzle exit of a full scale aero-engine using Stereo Particle Image Velocimetry (SPIV) aims at providing important reference and validation data required for reliable modeling and prediction. Furthermore, the turbulent jet engine exhaust flow is of prominent interest for the aerodynamic and -acoustic characterization of an aircraft engine. Especially the development of the free shear-layer between fan-bypass flow and outer flow is an important source of high-frequency noise as well as of big interest for modeling the turbulence of a jet flow correctly by advanced RANS methods. The SPIV measurements have been performed at free running fan phase positions and with a large number of statistically independent samples enabling a turbulence characterization of the fan-bypass and corresponding shear layer flow based on mean- and RMS-fields of all three velocity components, POD analysis and two-point-correlation functions.