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A Converging Slot-Hole Film-Cooling Geometry: Part 1 — Low-Speed Flat-Plate Heat Transfer and Loss

[+] Author Affiliations
J. E. Sargison, S. M. Guo, M. L. G. Oldfield

University of Oxford, Oxford, UK

G. D. Lock

University of Bath, Bath, UK

A. J. Rawlinson

Rolls Royce plc, Derby, UK

Paper No. 2001-GT-0126, pp. V003T01A012; 10 pages
doi:10.1115/2001-GT-0126
From:
  • ASME Turbo Expo 2001: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration
  • New Orleans, Louisiana, USA, June 4–7, 2001
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7852-1
  • Copyright © 2001 by ASME

abstract

This paper presents experimental measurements of the performance of a new film cooling hole geometry - the Converging Slot-Hole or Console. This novel, patented geometry has been designed to improve the heat transfer and aerodynamic loss performance of turbine vane and rotor blade cooling systems. The physical principles embodied in the new hole design are described, and a typical example of the console geometry is presented.

The cooling performance of a single row of consoles was compared experimentally with that of typical 35° cylindrical and fan-shaped holes and a slot, on a large-scale, flat-plate model at engine representative Reynolds numbers in a low speed tunnel with ambient temperature main flow. The hole throat area per unit width is matched for all four hole geometries. By independently varying the temperature of the heated coolant and the heat flux from an electrically heated, thermally insulated, constant heat flux surface, both the heat transfer coefficient and the adiabatic cooling effectiveness were deduced from digital photographs of the colour play of narrow-band thermochromic liquid crystals on the model surface.

A comparative measurement of the aerodynamic losses associated with each of the four film-cooling geometries was made by traversing the boundary layer at the downstream end of the flat plate.

The promising heat transfer and aerodynamic performance of the console geometry have justified further experiments on an engine representative nozzle guide vane in a transonic annular cascade presented in Part 2 of this paper [1].

Copyright © 2001 by ASME

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