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Impingement Cooling for Modern Combustors: Experimental Analysis and Preliminary Design

[+] Author Affiliations
Bruno Facchini, Marco Surace, Lorenzo Tarchi

University of Florence, Firenze, Italy

Paper No. GT2005-68361, pp. 1291-1300; 10 pages
doi:10.1115/GT2005-68361
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 3: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4726-8 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

The aim to reach very low emission limits has recently changed several aspects of combustor fluid dynamics. Among them, combustor cooling experienced significant design efforts to obtain good performances with unfavorable conditions. This paper deals with experimental research and 1D numerical simulations of impingement cooling from multiple jet arrays, performed in the first two years of the European research project LOPOCOTEP. Geometries are derived from typical LPP combustor cooling configurations, i.e. small and sparse holes, due to low coolant mass flow rate and high pressure losses (compared to typical blade cooling parameters). Tests are performed with both transient and steady-state technique, using TLC (Thermochromic Liquid Crystal) wide-band formulations. Results are obtained in terms of local distributions of heat transfer coefficient and effectiveness. Average values are compared with calculations to validate numerical code and derive useful indications on effectiveness variation for different blowing rate. It is accordingly found that literature results almost match the measurements. It is also shown that measured row-by-row effectiveness values can be usefully employed in a preliminary design stage. Data concerning holes discharge coefficients are also presented.

Copyright © 2005 by ASME

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