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Full Coverage Discrete Hole Wall Cooling: Cooling Effectiveness FREE

[+] Author Affiliations
G. E. Andrews, M. L. Gupta, M. C. Mkpadi

University of Leeds, Leeds, UK

Paper No. 84-GT-212, pp. V004T09A018; 10 pages
doi:10.1115/84-GT-212
From:
  • ASME 1984 International Gas Turbine Conference and Exhibit
  • Volume 4: Heat Transfer; Electric Power
  • Amsterdam, The Netherlands, June 4–7, 1984
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7949-8
  • Copyright © 1984 by ASME

abstract

The development of a test facility for investigating full coverage discrete hole wall cooling for gas turbine combustion chamber wall cooling is described. A low temperature test condition of 750K mainstream temperature and 300K coolant temperature was used to investigate the influence of coolant flow rate at a constant cross flow Mach number. Practical combustion conditions of 2100K combustor temperature and 700K coolant temperature are investigated to establish the validity of applying the low temperature results to practical conditions. For both situations a heat balance programme, taking into account the heat transfer within the wall was used to compute the film heat transfer coefficients. The mixing of the coolant air with the mainstream gases was studied through boundary layer temperature and CO2 profiles. It was shown that entrainment of hot flame gases between the injection holes resulted in a very low ‘adiabatic’ film cooling effectiveness.

Copyright © 1984 by ASME
Topics: Cooling
This article is only available in the PDF format.

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