Methodology to Study the Behavior of Tracer Particles in the Flow Field of Rotor 37 Using CFD Data

摘要

In air-breathing applications, non-intrusive optical techniques are one of the best ways to estimate the velocity of flow. The presence of tracer particles in these applications causes uncertainty in the velocity estimation. The impact of particle presence has been dealt with and quantified in many of the previous works for stationary transonic flows. In the current work, a method to understand the effect of the tracer particle presence in a rotating turbomachinery case is presented. National Aeronautics and Space Administration (NASA) Rotor 37 has been one of the standard cases for testing Computational Fluid Dynamics (CFD) codes in turbomachinery applications. Rotor 37 CFD data was post-processed by spawning particles with mass into its flow field. The Lagrangian Particle Tracking (LPT) method was implemented to obtain the particle data. Preliminary results obtained showed a significant impact on the velocity prediction in the downstream region of the inlet bow shock and the passage shock. It was also found out that at 70% span the passage shock causes high variation in velocity downstream when compared to its respective CFD data.