0

Full Content is available to subscribers

Subscribe/Learn More  >

PIV Measurements of the Flow in the Tip Region of a Compressor Rotor

[+] Author Affiliations
David Tan, Yuanchao Li, Ian Wilkes, Rinaldo L. Miorini, Joseph Katz

Johns Hopkins University, Baltimore, MD

Paper No. FEDSM2014-21593, pp. V01BT10A031; 11 pages
doi:10.1115/FEDSM2014-21593
From:
  • ASME 2014 4th Joint US-European Fluids Engineering Division Summer Meeting collocated with the ASME 2014 12th International Conference on Nanochannels, Microchannels, and Minichannels
  • Volume 1B, Symposia: Fluid Machinery; Fluid-Structure Interaction and Flow-Induced Noise in Industrial Applications; Flow Applications in Aerospace; Flow Manipulation and Active Control: Theory, Experiments and Implementation; Multiscale Methods for Multiphase Flow; Noninvasive Measurements in Single and Multiphase Flows
  • Chicago, Illinois, USA, August 3–7, 2014
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 978-0-7918-4622-3
  • Copyright © 2014 by ASME

abstract

An axial turbomachine, adapted from the NASA Glenn Low-Speed Axial Compressor (LSAC), has been assembled for detailed flow and turbulence measurements in the JHU optical refractive index matched facility. The test section consists of a row of twenty inlet guide vanes (IGV), followed by fifteen rotor blades, then twenty stator blades. The blades have the same geometry, but lower aspect ratio as the inlet guide vanes and the first stage of the LSAC facility at NASA Glenn. Although smaller in scale, the Reynolds number based on the tip speed and rotor blade chordlength are comparable to those of the LSAC. The casing, rotor blades, as well as half the IGVs and stator blades are made of transparent acrylic, matched with the refractive index of the working fluid, a concentrated solution of sodium iodide and water. The facility is designed to allow optical flow measurements in all three blade rows and from all directions. Results presented in this paper are based on 2D PIV measurements focusing on the flow structure in the tip region of the rotor blade for two flow rates, one of them just above the stall level. Included are phase-averaged distributions of velocity, circumferential vorticity, and turbulent kinetic energy in several meridional planes dissecting the tip at different chordwise locations. They follow the evolution of the Tip Leakage Vortex (TLV) as it rolls up near the blade suction side, migrates across the rotor passage, and subsequently bursts. Upon bursting, the distinct high vorticity core is replaced by a broad region of elevated vorticity, which occupy a substantial fraction of the passage. Sample instantaneous realizations and higher resolution stereo-PIV data are also provided. The turbulent kinetic energy is high near the vortex core, in the shear layer connecting the vortex to the blade tip, and around the point of flow separation on the endwall casing, where the leakage flow meets the main passage flow.

Copyright © 2014 by ASME

Figures

Tables

Interactive Graphics

Video

Country-Specific Mortality and Growth Failure in Infancy and Yound Children and Association With Material Stature

Use interactive graphics and maps to view and sort country-specific infant and early dhildhood mortality and growth failure data and their association with maternal

NOTE:
Citing articles are presented as examples only. In non-demo SCM6 implementation, integration with CrossRef’s "Cited By" API will populate this tab (http://www.crossref.org/citedby.html).

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In