Aeroelastic effects in a planar flat blade cascade at high Mach number flow
Identifikátory výsledku
Kód výsledku v IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F46747885%3A24220%2F22%3A00010504" target="_blank" >RIV/46747885:24220/22:00010504 - isvavai.cz</a>
Výsledek na webu
<a href="https://hal.science/hal-03715702v2/document" target="_blank" >https://hal.science/hal-03715702v2/document</a>
DOI - Digital Object Identifier
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Alternativní jazyky
Jazyk výsledku
angličtina
Název v původním jazyce
Aeroelastic effects in a planar flat blade cascade at high Mach number flow
Popis výsledku v původním jazyce
The paper reports on measurements of unsteady pressure and aeroelastic response of a simplified turbine blade cascade under kinematic excitation. The flow velocities ranged from high subsonic to transonic regimes and reduced frequencies were between k = 0 – 0.41. Unsteady pressures measured by six miniature pressure transducers in the oscillating blade are shown for one representative measurement, and blade oscillation amplitudes compared for the whole measurement matrix. The results show strong pressure oscillations near the leading edge due to switching between subsonic and supersonic airflow. The oscillation amplitudes of the blade sharply increase with the frequency and are weakly influenced by the Mach number.
Název v anglickém jazyce
Aeroelastic effects in a planar flat blade cascade at high Mach number flow
Popis výsledku anglicky
The paper reports on measurements of unsteady pressure and aeroelastic response of a simplified turbine blade cascade under kinematic excitation. The flow velocities ranged from high subsonic to transonic regimes and reduced frequencies were between k = 0 – 0.41. Unsteady pressures measured by six miniature pressure transducers in the oscillating blade are shown for one representative measurement, and blade oscillation amplitudes compared for the whole measurement matrix. The results show strong pressure oscillations near the leading edge due to switching between subsonic and supersonic airflow. The oscillation amplitudes of the blade sharply increase with the frequency and are weakly influenced by the Mach number.
Klasifikace
Druh
O - Ostatní výsledky
CEP obor
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OECD FORD obor
20304 - Aerospace engineering
Návaznosti výsledku
Projekt
<a href="/cs/project/GA20-11537S" target="_blank" >GA20-11537S: Experimentální výzkum budicí funkce flutteru v turbostrojích</a><br>
Návaznosti
P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)
Ostatní
Rok uplatnění
2022
Kód důvěrnosti údajů
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů