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A Converging Slot-Hole Film-Cooling Geometry-Part 2: Transonic Nozzle Guide Vane Heat Transfer and Loss

Citation

Sargison, JE and Guo, SM and Oldfield, MLG and Lock, GD and Rawlinson, AJ, 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 0889-504X (2002) [Refereed Article]

DOI: doi:10.1115/1.1459736

Abstract

This paper presents the first experimental measurements on an engine representative nozzle guide vane, of a new film-cooling hole geometry, a convergingslot-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 flat-plate tests described in Part 1 of this paper. Stereolithography was used to manufacture a resin model of a transonic, engine representative nozzle guide vane in which seven rows of previously tested fan-shaped film-cooling holes were replaced by four 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 computer-video 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 midspan traverses of a four-hole pyramid probe downstream of the nozzle guide vane.

Item Details

Item Type:Refereed Article
Research Division:Engineering
Research Group:Aerospace Engineering
Research Field:Aircraft Performance and Flight Control Systems
Objective Division:Transport
Objective Group:Aerospace Transport
Objective Field:Air Safety
Author:Sargison, JE (Dr Jane Sargison)
ID Code:23954
Year Published:2002
Web of Science® Times Cited:53
Deposited By:Engineering
Deposited On:2002-08-01
Last Modified:2007-10-30
Downloads:0

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