Exploratory Experiments for Simple Approximation of Blade Flutter Aerodynamic Loading Function

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F46747885%3A24220%2F22%3A00010503" target="_blank" >RIV/46747885:24220/22:00010503 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/61388998:_____/22:00564780

Výsledek na webu

<a href="https://doi.org/10.1115/GT2022-83351" target="_blank" >https://doi.org/10.1115/GT2022-83351</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1115/GT2022-83351" target="_blank" >10.1115/GT2022-83351</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Exploratory Experiments for Simple Approximation of Blade Flutter Aerodynamic Loading Function

Popis výsledku v původním jazyce

Exploratory experiments to verify a newly proposed simple method determining an approximate form of unsteady blade loading function are described in this paper In this newly proposed approach, a time-dependent blade loading will be substituted for by a series of static loadings acquired for a range of blade incidence angle offsets. The sequence of static loadings will be converted into a time-dependent quasi-dynamic function computationally. In the course of this project a new test facility for forced blade flutter research capable of transonic inlet flow at high oscillation blade frequencies was designed and built at the IT CAS laboratory. A series of test runs simulating blade flutter conditions were carried out for the inlet Mach number range from 0.6 up to 1.09 and blade oscillation frequencies up to 80 Hz. A blade static loading function was created as a pressure difference measured while the blade was not moving and it was set to the outermost incidence angle offsets of plus/minus 1 deg. A blade dynamic loading function was determined as a peak-to-peak amplitude of measured pressure fluctuation while the blade was oscillated at a frequency of 80 Hz. A very good agreement between the measured blade static and blade dynamic loading functions indicates the potentials of the proposed quasi-dynamic method to closely estimate blade loading functions, at least for the reported range of cascade operation conditions.

Název v anglickém jazyce

Exploratory Experiments for Simple Approximation of Blade Flutter Aerodynamic Loading Function

Popis výsledku anglicky

Exploratory experiments to verify a newly proposed simple method determining an approximate form of unsteady blade loading function are described in this paper In this newly proposed approach, a time-dependent blade loading will be substituted for by a series of static loadings acquired for a range of blade incidence angle offsets. The sequence of static loadings will be converted into a time-dependent quasi-dynamic function computationally. In the course of this project a new test facility for forced blade flutter research capable of transonic inlet flow at high oscillation blade frequencies was designed and built at the IT CAS laboratory. A series of test runs simulating blade flutter conditions were carried out for the inlet Mach number range from 0.6 up to 1.09 and blade oscillation frequencies up to 80 Hz. A blade static loading function was created as a pressure difference measured while the blade was not moving and it was set to the outermost incidence angle offsets of plus/minus 1 deg. A blade dynamic loading function was determined as a peak-to-peak amplitude of measured pressure fluctuation while the blade was oscillated at a frequency of 80 Hz. A very good agreement between the measured blade static and blade dynamic loading functions indicates the potentials of the proposed quasi-dynamic method to closely estimate blade loading functions, at least for the reported range of cascade operation conditions.

Druh

D - Stať ve sborníku

CEP obor

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OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/LTAUSA19036" target="_blank" >LTAUSA19036: Pokročilý experimentální výzkum synchronního a nesynchronního kmitání lopatek</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2022

Kód důvěrnosti údajů

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

Název statě ve sborníku

Proceedings of the ASME Turbo Expo

ISBN

978-079188606-9

ISSN

—

e-ISSN

—

Počet stran výsledku

10

Strana od-do

—

Název nakladatele

The American Society of Mechanical Engineers

Místo vydání

—

Místo konání akce

Rotterdam

Datum konání akce

1. 1. 2022

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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