Boundary Layer Development in Axial Compressors and Turbines: Part 4 of 4—Computations and Analyses-Reference-Cited by-同舟云学术

Boundary Layer Development in Axial Compressors and Turbines: Part 4 of 4—Computations and Analyses

Published:1997-01-01 Issue:1 Volume:119 Page:128-139
ISSN:0889-504X
Container-title:Journal of Turbomachinery
language:en
Short-container-title:

Author:

Halstead D. E.¹,Wisler D. C.¹,Okiishi T. H.²,Walker G. J.³,Hodson H. P.⁴,Shin H.-W.¹

Affiliation:

1. GE Aircraft Engines, Cincinnati, OH 45215

2. Iowa State University, Ames, IA 50011

3. University of Tasmania, Hobart, Tasmania

4. University of Cambridge, Cambridge, United Kingdom

Abstract

This is Part Four of a four-part paper. It begins with Section 16.0 and concludes the description of the comprehensive experiments and computational analyses that have led to a detailed picture of boundary layer development on airfoil surfaces in multistage turbomachinery. In this part, the computational predictions made using several modern boundary layer codes are presented. Both steady codes and an unsteady code were evaluated. The results are compared with time-averaged and unsteady integral parameters measured for the boundary layers. Assessments are made to provide guidance in using the predictive codes to locate transition and predict loss. Conclusions from the computational analyses are then presented.

Publisher

ASME International

Subject

Mechanical Engineering

Link

http://asmedigitalcollection.asme.org/turbomachinery/article-pdf/119/1/128/5840414/128_1.pdf

Reference10 articles.

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