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2026
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| Accés en línia: | https://doi.org/10.5281/zenodo.20003737 |
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| author | Šidlof, Petr Šimurda, David Lepicovsky, Jan Štěpán, Martin Šidlof, Pavel |
| author_facet | Šidlof, Petr Šimurda, David Lepicovsky, Jan Štěpán, Martin Šidlof, Pavel |
| contents | <p>The paper reports on a redesign of a test rig for investigation<br>of flutter of turbomachinery blades in high-speed airflow,<br>together with the first experimental results. The test section,<br>mounted in the high-speed wind tunnel, consists of a linear<br>cascade of five prismatic blades. A new mechanism was<br>developed and tested, allowing controlled kinematic excitation<br>of three middle blades with a continuously adjustable interblade<br>phase angle (IBPA). The experimental setup is equipped with a<br>laser triangulation sensor measuring the blade oscillation,<br>unsteady pressure probes in the blade suction surface, straingauge<br>bridges on the blade shafts monitoring the total torque<br>and a schlieren optical setup with high-speed camera for<br>visualization of the flow field around the middle blade. The<br>measured data were analyzed for inlet Mach number of 1.09,<br>frequency of blade oscillation of 150 Hz and interblade phase<br>angles ranging from –90 deg to 180 deg. The pressure oscillation<br>amplitude along the blade reached its maximum for<br>IBPA = -90 deg at 40% of the chord length, and its minimum for<br>IBPA = +45 deg. Among all measured cases, the most distinct<br>behavior was observed when the blades oscillated out of phase<br>(IBPA=180 deg). In this condition, the normal shock on the<br>pressure surface oscillated strongly from a point far downstream<br>up to the leading edge, and the total torque exhibited the highest<br>peak value.</p> |
| format | Recurso digital |
| id | zenodo_https___doi_org_10_5281_zenodo_20003737 |
| institution | Zenodo |
| language | |
| publishDate | 2026 |
| publisher | Zenodo |
| record_format | zenodo |
| spellingShingle | MEASUREMENT OF TRANSONIC AIRFLOW IN AN OSCILLATING BLADE CASCADE WITH VARIABLE INTERBLADE PHASE ANGLE Šidlof, Petr Šimurda, David Lepicovsky, Jan Štěpán, Martin Šidlof, Pavel Turbomachinery Propulsion Aeromechanics <p>The paper reports on a redesign of a test rig for investigation<br>of flutter of turbomachinery blades in high-speed airflow,<br>together with the first experimental results. The test section,<br>mounted in the high-speed wind tunnel, consists of a linear<br>cascade of five prismatic blades. A new mechanism was<br>developed and tested, allowing controlled kinematic excitation<br>of three middle blades with a continuously adjustable interblade<br>phase angle (IBPA). The experimental setup is equipped with a<br>laser triangulation sensor measuring the blade oscillation,<br>unsteady pressure probes in the blade suction surface, straingauge<br>bridges on the blade shafts monitoring the total torque<br>and a schlieren optical setup with high-speed camera for<br>visualization of the flow field around the middle blade. The<br>measured data were analyzed for inlet Mach number of 1.09,<br>frequency of blade oscillation of 150 Hz and interblade phase<br>angles ranging from –90 deg to 180 deg. The pressure oscillation<br>amplitude along the blade reached its maximum for<br>IBPA = -90 deg at 40% of the chord length, and its minimum for<br>IBPA = +45 deg. Among all measured cases, the most distinct<br>behavior was observed when the blades oscillated out of phase<br>(IBPA=180 deg). In this condition, the normal shock on the<br>pressure surface oscillated strongly from a point far downstream<br>up to the leading edge, and the total torque exhibited the highest<br>peak value.</p> |
| title | MEASUREMENT OF TRANSONIC AIRFLOW IN AN OSCILLATING BLADE CASCADE WITH VARIABLE INTERBLADE PHASE ANGLE |
| topic | Turbomachinery Propulsion Aeromechanics |
| url | https://doi.org/10.5281/zenodo.20003737 |