Loss Reduction in Axial-Flow Compressors Through Low-Speed Model TestingSource: Journal of Engineering for Gas Turbines and Power:;1985:;volume( 107 ):;issue: 002::page 354Author:D. C. Wisler
DOI: 10.1115/1.3239730Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: A systematic procedure for reducing losses in axial-flow compressors is presented. In this procedure, a large, low-speed, aerodynamic model of a high-speed core compressor is designed and fabricated based on aerodynamic similarity principles. This model is then tested at low speed where high-loss regions associated with three-dimensional endwall boundary layers, flow separation, leakage, and secondary flows can be located, detailed measurements made, and loss mechanisms determined with much greater accuracy and much lower cost and risk than is possible in small, high-speed compressors. Design modifications are made by using custom-tailored airfoils and vector diagrams, airfoil endbends, and modified wall geometries in the high-loss regions. The design improvements resulting in reduced loss or increased stall margin are then scaled to high speed. This paper describes the procedure and presents experimental results to show that in some cases endwall loss has been reduced by as much as 10 percent, flow separation has been reduced or eliminated, and stall margin has been substantially improved by using these techniques.
keyword(s): Compressors , Testing , Axial flow , Flow separation , Design , Airfoils , Leakage , Mechanisms , Boundary layers , Flow (Dynamics) AND Measurement ,
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contributor author | D. C. Wisler | |
date accessioned | 2017-05-08T23:20:11Z | |
date available | 2017-05-08T23:20:11Z | |
date copyright | April, 1985 | |
date issued | 1985 | |
identifier issn | 1528-8919 | |
identifier other | JETPEZ-26618#354_1.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/99831 | |
description abstract | A systematic procedure for reducing losses in axial-flow compressors is presented. In this procedure, a large, low-speed, aerodynamic model of a high-speed core compressor is designed and fabricated based on aerodynamic similarity principles. This model is then tested at low speed where high-loss regions associated with three-dimensional endwall boundary layers, flow separation, leakage, and secondary flows can be located, detailed measurements made, and loss mechanisms determined with much greater accuracy and much lower cost and risk than is possible in small, high-speed compressors. Design modifications are made by using custom-tailored airfoils and vector diagrams, airfoil endbends, and modified wall geometries in the high-loss regions. The design improvements resulting in reduced loss or increased stall margin are then scaled to high speed. This paper describes the procedure and presents experimental results to show that in some cases endwall loss has been reduced by as much as 10 percent, flow separation has been reduced or eliminated, and stall margin has been substantially improved by using these techniques. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing | |
type | Journal Paper | |
journal volume | 107 | |
journal issue | 2 | |
journal title | Journal of Engineering for Gas Turbines and Power | |
identifier doi | 10.1115/1.3239730 | |
journal fristpage | 354 | |
journal lastpage | 363 | |
identifier eissn | 0742-4795 | |
keywords | Compressors | |
keywords | Testing | |
keywords | Axial flow | |
keywords | Flow separation | |
keywords | Design | |
keywords | Airfoils | |
keywords | Leakage | |
keywords | Mechanisms | |
keywords | Boundary layers | |
keywords | Flow (Dynamics) AND Measurement | |
tree | Journal of Engineering for Gas Turbines and Power:;1985:;volume( 107 ):;issue: 002 | |
contenttype | Fulltext |