Research

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


Reference:

Sargison, J. E., Guo, S. M., Oldfield, M. L. G., Lock, G. D. and Rawlinson, A. J., 2002. A converging slot-hole film-cooling geometry - Part 2: Transonic nozzle guide vane heat transfer and loss. Journal of Turbomachinery: Transactions of the ASME, 124 (3), pp. 461-471.

Related documents:

This repository does not currently have the full-text of this item.
You may be able to access a copy if URLs are provided below.

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.

Details

Item Type Articles
CreatorsSargison, J. E., Guo, S. M., Oldfield, M. L. G., Lock, G. D. and Rawlinson, A. J.
DOI10.1115/1.1459736
DepartmentsFaculty of Engineering & Design > Mechanical Engineering
RefereedYes
StatusPublished
ID Code2605
Additional InformationID number: ISI:000177013500019

Export

Actions (login required)

View Item