Quasi-Dynamic Approximation of Unsteady Pressure Distribution for Transonic Airfoils in Flutter

Result code in IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F61388998%3A_____%2F23%3A00571961" target="_blank" >RIV/61388998:_____/23:00571961 - isvavai.cz</a>

Alternative codes found

RIV/46747885:24220/23:00011152

Result on the web

<a href="https://asmedigitalcollection.asme.org/turbomachinery/article/145/8/081010/1160238/Quasi-Dynamic-Approximation-of-Unsteady-Pressure?searchresult=1" target="_blank" >https://asmedigitalcollection.asme.org/turbomachinery/article/145/8/081010/1160238/Quasi-Dynamic-Approximation-of-Unsteady-Pressure?searchresult=1</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1115/1.4062181" target="_blank" >10.1115/1.4062181</a>

Result language

angličtina

Original language name

Quasi-Dynamic Approximation of Unsteady Pressure Distribution for Transonic Airfoils in Flutter

Original language description

A lack of reliable experimental data on transonic blade flutter in real turbomachines hampers the further improvement of computational design predictions for off-design operation regimes of newly-built machines. Acquiring unsteady pressure distribution on blades in real turbomachines already in operation is practically impossible. The goal of this work is to explore if an approximate unsteady pressure distribution can be created experimentally in a simple aerodynamic tunnel by composing a sequence of blade surface steady pressures acquired for gradually varying blade incidence angle offsets. An essential condition for such an approximation is the assumption that the dynamic pressure component induced by the blade motion is substantially smaller than the flow pattern changes caused by the variation of interblade channel geometry. The methodology is proposed for blade sections with prevailing two-dimensional flow. A dedicated test facility, called the blade flutter module (BFM), has been built and used for this purpose. The BFM is a linear cascade consisting of five transonic airfoils that can be operated either in a static or a dynamic regime. For the dynamic operation, any of the blades can be forcedly and independently oscillated at frequencies of up to 400 Hz with a maximum angular amplitude of 3 deg. The obtained results confirm that within the range of the test conditions, the proposed compounded quasi-dynamic approach exhibits similar characteristics to dynamically acquired unsteady blade pressures. This is true for a test range of a maximum inlet Mach number of 1.09, maximum blade oscillating frequency of 100 Hz, and measurement of unsteady pressure distribution on a blade suction surface. The corresponding blade chord based reduced frequency is 0.21.

Czech name

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Czech description

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Type

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

CEP classification

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OECD FORD branch

20302 - Applied mechanics

Project

<a href="/en/project/LTAUSA19036" target="_blank" >LTAUSA19036: Advanced experimental research on synchronous and non-synchronous blade vibration</a><br>

Continuities

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Publication year

2023

Confidentiality

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

Name of the periodical

Journal of Turbomachinery-Transactions of the Asme

ISSN

0889-504X

e-ISSN

1528-8900

Volume of the periodical

145

Issue of the periodical within the volume

8

Country of publishing house

US - UNITED STATES

Number of pages

15

Pages from-to

081010

UT code for WoS article

001021833500016

EID of the result in the Scopus database

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