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A converging slot-hole film-cooling geometry - Part 2: Transonic nozzle guide vane heat transfer and loss

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Sargison, JE and Guo, SM and Oldfield, MLG and Lock, GD (2002) A converging slot-hole film-cooling geometry - Part 2: Transonic nozzle guide vane heat transfer and loss. Transactions of the ASME: Journal of Turbomachinery, 124 (3). pp. 461-471. ISSN 0889504x

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Abstract

This paper presents the first experimental measurements on
an engine representative nozzle guide vane, of a new film
cooling hole geometry, a Converging Slot-Hole or Console.
The patented console geometry is designed to improve the heat
transfer and aerodynamic performance of turbine vane and
rotor blade cooling systems. These experiments follow the
successful validation of the console design in low-speed flatplate
tests described in Part 1 of this paper (Sargison et al [1]).
Stereolithography was used to manufacture a resin model
of a transonic, engine representative nozzle guide vane in
which 7 rows of previously tested fan-shaped film-cooling
holes were replaced by 4 rows of consoles. This vane was
mounted in the annular vane ring of the Oxford Cold Heat
Transfer Tunnel for testing at engine Reynolds numbers, Mach
numbers and coolant to mainstream momentum flux ratios
using a heavy gas to simulate the correct coolant to mainstream
density ratio.
Heat transfer data were measured using wide band
thermochromic liquid crystals and a modified analysis
technique. Both surface heat transfer coefficient and the
adiabatic cooling effectiveness were derived from computervideo
records of hue changes during the transient tunnel run.
The cooling performance, quantified by the heat flux at engine
temperature levels, of the console vane compares favourably
with that of the previously tested vane with fan-shaped holes.
The new console film cooling hole geometry offers
advantages to the engine designer due to a superior
aerodynamic efficiency over the fan-shaped hole geometry.
These efficiency measurements are demonstrated by results
from mid span traverses of a four hole pyramid probe
downstream of the nozzle guide vane.

Item Type: Article
Journal or Publication Title: Transactions of the ASME: Journal of Turbomachinery
Page Range: pp. 461-471
ISSN: 0889504x
Identification Number - DOI: 10.1115/1.1459736
Date Deposited: 28 Oct 2007 21:54
Last Modified: 24 Oct 2017 22:11
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