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Effect of Blade Passage Surface Heat Extraction on Axial Compressor Performance

[+] Author Affiliations
P. N. Shah, C. S. Tan

Massachusetts Institute of Technology, Cambridge, MA

Paper No. GT2005-68815, pp. 327-341; 15 pages
doi:10.1115/GT2005-68815
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

Axial compressor performance with heat extraction via blade passage surfaces (compressor cooling) is compared to its adiabatic counterpart, using computational experiments and meanline modeling. For a multistage compressor with an adiabatic design point, results at fixed corrected rotor speed indicate that if available, compressor cooling would: (i) raise the overall pressure ratio (at a given corrected flow), (ii) raise the maximum mass flow capability, (iii) raise the efficiency, defined as the ratio of isentropic work for a given pressure ratio to actual shaft work, and (iv) provide rear stage choking relief at low corrected speed. In addition, it is found that, if available, cooling in the front stages is better than in the rear stages. This is primarily a thermodynamic effect that results from the fact that, for a given gas, the compression work required to achieve a given pressure ratio decreases as the gas becomes colder. Heat transfer considerations indicate that the engineering challenges lie in achieving high enough heat transfer rates to provide significant impact to the compressor’s performance.

Copyright © 2005 by ASME
Topics: Heat , Compressors , Blades

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