0

Full Content is available to subscribers

Subscribe/Learn More  >

Numerical Study of Discrete Tip Injection in a Transonic Axial Compressor

[+] Author Affiliations
Hossein Khaleghi

Shiraz University, Shiraz, Iran

Joao A. Teixeira

Cranfield University, Cranfield, UK

Paper No. GT2010-23608, pp. 525-535; 11 pages
doi:10.1115/GT2010-23608
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

This paper reports on a time-accurate simulation of discrete tip injection upstream of a transonic axial compressor, NASA Rotor-67. Twenty two discrete injectors were placed around the casing upstream of the blade to investigate the effect of injector-rotor interaction at near-stall condition. Time-accurate simulations were performed with and without tip injection at stable and unstable operating points. Although the injected mass flow rate is very small, the range extension obtained promises the effective use of such injection in suppressing rotating stall at early stages of formation, with almost no efficiency penalty incurred. The effect of injection on the tip flow structure and unsteady response of the leakage flow are presented and discussed. Results indicate that injection periodically pushes the tip leakage vortex and passage shock rearward. The location of the leakage vortex with injection was found to be backward of that without injection, at the near-stall condition of the non-injection case. At the near-stall point of the injection case, however, the tip leakage vortex was at some situations rearward and at some situations forward, as compared with the non-injection case. In other words, the leakage vortex in the injection case oscillates around the location of the time-averaged leakage vortex without injection. This is the situation, at which, the interface between the leakage and oncoming flows tends to become parallel to the leading-edge plane. The effect of injection on the boundary layer separation from the casing wall is also investigated. The rotor operation at in-stall condition for both the injection and non-injection cases is studied and the path into instability is discussed for each case. The propagation of a low-velocity region near the pressure surface and leading-edge of the blade was found to be responsible for the detachment of the passage shock from the leading-edge and upstream movement of the leakage vortex, leading to the occurrence of the leading-edge vortex spillage, for both the injection and non-injection cases.

Copyright © 2010 by ASME
Topics: Compressors

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