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A converging slot-hole film-cooling geometry - Part 2: Transonic nozzle guide vane heat transfer and loss
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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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 ). 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.
|Journal or Publication Title:||Transactions of the ASME: Journal of Turbomachinery|
|Page Range:||pp. 461-471|
|Identification Number - DOI:||10.1115/1.1459736|
|Date Deposited:||28 Oct 2007 21:54|
|Last Modified:||18 Nov 2014 03:24|
|Item Statistics:||View statistics for this item|
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