HEAT-TRANSFER AND AERODYNAMICS OF A HIGH RIM SPEED TURBINE NOZZLE GUIDE VANE TESTED IN THE RAE ISENTROPIC LIGHT PISTON CASCADE (ILPC)

被引:8
作者
HARASGAMA, SP [1 ]
WEDLAKE, ET [1 ]
机构
[1] ROYAL AEROSP ESTAB,DEPT PROPULS,FARNBOROUGH GU14 0LS,HANTS,ENGLAND
来源
JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME | 1991年 / 113卷 / 03期
关键词
D O I
10.1115/1.2927887
中图分类号
TH [机械、仪表工业];
学科分类号
0802 ;
摘要
Detailed heat transfer and aerodynamic measurements have been made on an annular cascade of highly loaded nozzle guide vanes. The tests were carried out in an Isentropic Light Piston test facility at engine representative Reynolds number, Mach number, and gas-to-wall temperature ratio. The aerodynamics indicate that the vane has a weak shock at 65-70 percent axial chord (midspan) with a peak Mach number of 1.14. The influence of Reynolds number and Mach number on the Nusselt number distributions on the vane and endwall surfaces are shown to be significant. Computational techniques are used for the interpretation of test data.
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页码:384 / 391
页数:8
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