COMPRESSOR BLADE BOUNDARY-LAYERS .2. MEASUREMENTS WITH INCIDENT WAKES

被引：42

作者：

DONG, Y

CUMPSTY, NA

机构：

[1] Gas Turbine Engineering Division, Ruston Gas Turbines Ltd., Lincoln

[2] Department of Engineering, Whittle Laboratory, University of Cambridge, Cambridge

[3] Whittle Laboratory, University of Cambridge

来源：

JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME | 1990年 / 112卷 / 02期

关键词：

D O I：

10.1115/1.2927637

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

This paper follows directly from Part 1 by the same authors and describes measurements of the boundary layer on a supercritical-type compressor blade with wakes from a simulated moving upstream blade row convected through the passage. (The blades and the test facilities together with the background are described in Part 1). The results obtained with the wakes are compared to those with none for both low and high levels of inlet turbulence. The transition process and boundary layer development are very different in each case, though the overall momentum thickness at the trailing edge is fairly similar. None of the models for transition is satisfactory when this is initiated by moving wakes. © 1990 by ASME.

引用

页码：231 / 240

页数：10