Aeroelastic effects in a planar flat blade cascade at high Mach number flow

Result code in 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>
Result on the web
<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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Result language
angličtina
Original language name
Aeroelastic effects in a planar flat blade cascade at high Mach number flow
Original language description
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.
Czech name
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Czech description
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Project
<a href="/en/project/GA20-11537S" target="_blank" >GA20-11537S: Experimental research on flutter excitation function in turbomachinery</a><br>
Continuities
P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Publication year
2022
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

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