Our heavyweight helicopter equal in the world does not have
In Rostov started production of the most load-lifting rotary-wing car The Russian holding «Helicopt[...]
DPIV MEASUREMENTS OF THE FLOW FIELD BETWEEN A TRANSONIC ROTOR AND AN UPSTREAM STATOR
Steven E. Gorrell, William W. Copenhaver U. S. Air Force Research Lab Propulsion Directorate Wright-Patterson AFB, Ohio
Jordi Estevadeordal
Innovative Scientific Solutions, Inc.
Beavercreek, Ohio
1. Introduction
The use of a planar non-intrusive measurement techniques such as Digital Particle Image Velocimetry (DPIV) have made it possible to investigate many aspects of unsteady fbws previously considered difficult due to the effect of a measurement probe on the fbw field, or too time consuming because of the pointwise nature of Laser Doppler Velocimetry or Laser Transit Anemometry. Furthermore, time-accurate CFD codes are being developed and are now commonly used to simulate compressors and investigate complex unsteady fbw phenomenon.
In this paper, DPIV measurements made in a transonic compressor stage are used to investigate interactions between an upstream stator and a downstream transonic rotor. In particular, the interaction between the rotor bow shock and the wake shed from the upstream stator are explored and offered as a test case for unsteady CFD comparison.
Blade-row interactions are known to have a significant impact on the aerome – chanical and aerodynamic performance of compressors. For example, Sanders and Fleeter [1] have shown shock-induced rearward forcing to elicit significant upstream surface-pressure amplitudes and a complicated forcing environment that contributes to High Cycle Fatigue (HCF). Numerous low speed and high speed experimental and numerical investigations [2], [3], [4], [5], [6], [7] have revealed how some blade row interactions improve stage pressure ratio and efficiency while others are detrimental to performance.
505
K. C. Hall et al. (eds.),
Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines, 505-519. © 2006 Springer. Printed in the Netherlands.
Previous experiments using pointwise velocimetry techniques have been used to better understand the three-dimensional geometry of rotor shocks [8], wake recovery [4], wake-shock interactions [9], [10], and for steady CFD code comparison [11].
