Mass Flow Limitation of Supersonic Blade Rows Due to Leading Edge Blockage
| Autor: | Zhong Yongxing, Heinz-Adolf Schreiber, Hans Starken |
|---|---|
| Rok vydání: | 1985 |
| Předmět: |
Physics
Supersonic wind tunnel Leading edge Materials science Blade (geometry) business.industry Mass flow Rayleigh flow Aerospace Engineering Structural engineering Mechanics Mach wave Physics::Fluid Dynamics symbols.namesake Axial compressor Mach number symbols Supersonic speed business Ludwieg tube Transonic Row |
| Zdroj: | International Journal of Turbo and Jet Engines. 2 |
| ISSN: | 2191-0332 0334-0082 |
| DOI: | 10.1515/tjj.1985.2.4.285 |
| Popis: | The supersonic flow passing through the blade row of an axial flow compressor depends on the magnitude of the axial inlet Mach number. If the upstream stream tube is convergent, the axial Mach number remains subsonic and the unique incidence relation holds between inlet Mach number and inlet flow angle. This paper presents the influence of leading edge thickness and suction surface angle on the unique incidence and choking of supersonic blade rows. The theoretical results were experimentally verified in supersonic cascade wind tunnel tests.Copyright © 1984 by ASME |
| Databáze: | OpenAIRE |
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