Aerodynamic response of a blade cascade to torsional excitation of one blade at subsonic and transonic velocities

Result code in IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F25%3A00637476" target="_blank" >RIV/61388998:_____/25:00637476 - isvavai.cz</a>

Alternative codes found

RIV/68407700:21220/25:00386293 RIV/46747885:24220/25:00013695

Result on the web

<a href="https://www.sciencedirect.com/science/article/pii/S2212540X25000306?pes=vor&utm_source=scopus&getft_integrator=scopus" target="_blank" >https://www.sciencedirect.com/science/article/pii/S2212540X25000306?pes=vor&utm_source=scopus&getft_integrator=scopus</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.jppr.2025.05.006" target="_blank" >10.1016/j.jppr.2025.05.006</a>

Result language

angličtina

Original language name

Aerodynamic response of a blade cascade to torsional excitation of one blade at subsonic and transonic velocities

Original language description

The trend of increasing the power-to-weight ratios of aircraft turbofan engines and efficiency of steam turbines leads to designs with long and slender blades often operating at transonic flow conditions. Such blades are prone to undesirable and possibly destructive vibrations caused by engine-order excitation or induced by flow itself. To shed more light on this problem and to extend the existing knowledge, this paper presents experimental and numerical study on torsional mode vibration of one blade in a linear blade cascade of flat profiles. In this study, dynamic loading and pressure distributions were investigated at subsonic, supercritical and transonic flow regimes while the blade was kinematically excited by a motor and shaft mechanism at reduced frequencies up to k = 0.47. Dynamic flow structure development was documented and analyzed based on numerical simulations. Furthermore, dependence of energy transfer over an oscillation cycle on frequency and exit Mach number was investigated. Results revealed significant hysteresis in the flow field configuration particularly at supercritical and transonic cases. Hysteresis is manifested namely by different development of supersonic regions when the oscillating blade passes through the zero deflection during upstroke and downstroke. Resulting aerodynamic moment is non-harmonic and there is an increasing phase lag with respect to the blade deflection when oscillation frequency increases. In majority of investigated regimes, hysteresis resulted in aerodynamic damping of the blade oscillation.

Czech name

—

Czech description

—

Type

J_imp - Article in a specialist periodical, which is included in the Web of Science database

CEP classification

—

OECD FORD branch

20302 - Applied mechanics

Project

<a href="/en/project/LUAUS23231" target="_blank" >LUAUS23231: Origins and mechanisms of flutter and non-synchronous vibration in modern turbomachines operating at wide range of regimes</a><br>

Continuities

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Publication year

2025

Confidentiality

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Name of the periodical

Propulsion and Power Research

ISSN

2212-540X

e-ISSN

2212-540X

Volume of the periodical

14

Issue of the periodical within the volume

2

Country of publishing house

CN - CHINA

Number of pages

15

Pages from-to

259-273

UT code for WoS article

001551762900001

EID of the result in the Scopus database

2-s2.0-105009941550