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Aeroacoustic Noise Source Investigation in the Case of the Blade Cascade
Procházka, Pavel P. ; Antoš, Pavel ; Šnábl, Pavel
The blade cascade consisted of five NACA 0010 profiles is examined in the framework of project dealing with nonlinear dynamic phenomenon related to stall flutter of flexible profiles with pitch degree of freedom in subsonic flow. Various angles of attack (AoA) of the cascade generates different (broadband) aeroacoustic noise. The goal of this article is to describe the existence of possible noise sources using two experimental methods – Particle Image velocimetry (PIV) and hot-wire (HW) anemometry.
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Experimental and numerical evaluation of blade cascade instability using travelling wave mode approach
Chindada, Sony ; Šnábl, Pavel ; Pešek, Luděk
The stability of experimental blade cascade with five NACA 0010 profiles was measured and evaluated with travelling wave mode approach with three inner blades oscilating. The measured moment of the middle blade consist of not only the aerodynamic moment from the flow but also structural moment from the blade dynamics. Two days of obtaining the aerodynamic moment from the measured data are herein presented and the results compared. In addition, numercial simulations were done and the results from 2D CFD analysis in ANSYS are compared with the experimental data.
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Turbine blade linkages in reduced modal synthesis model
Pešek, Luděk ; Šnábl, Pavel
The paper is the first stage of our modelling turbine blade linkages in reduced modal synthesis model. The modal synthesis method is used for the dynamic behaviour studies of turbine bladed wheels with frictional inter-blade linkages and in case of the microslips the stiffening effect of the linkages play an important role in wheel dynamics. The paper presents the first results of modal analysis of the wheel when springs were used to substitute the linkages in the modal synthesis model.
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Effect of oscillating blade on tonal noise of blade cascade with five NACA 0010 profiles
Šnábl, Pavel ; Pešek, Luděk ; Radolf, Vojtěch ; Antoš, Pavel ; Procházka, Pavel P. ; Prasad, Chandra Shekhar
The airfoil tonal noise is a well known phenomenon which appears on single airfoils in moderate Reynolds numbers at low angles of attack. It can appear on small aircrafts, fans, wind turbines etc. In thispaper, it was observed on a blade cascade consisting of five NACA 0010 profiles placed in a closed rectangular channel with hard walls when for given conditions, i.e. flow velocity and angle of attack, the cascade tunes to one single frequency. During the middle blade oscillation, the single tone splits up to several tones with lower intensity modulated by the excitation frequency. Thus, the oscillation of one blade suppresses the tonal noise generation in the cascade.
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Flutter methodology using reduced order aeroelastic model
Prasad, Chandra Shekhar ; Pešek, Luděk ; Šnábl, Pavel
The present research project is focused on development of fast and efficient numerical method based on reduced order aeroelastic method (ROAM) for modeling and analysis of \nclassical flutter in the low pressure (LP) stage steam turbine blade. Stability diagram such as aerodynamic damping (AD) of aeroelasticity of cascade of 3D turbine blades used as a prime \ncharacterization factor. In the calculation of the S-curve/AD, the problem of classical flutter formation associated with running waves is considered here. Running waves is simulated by \nthe inter-blade phase shift of the blades in the cascade. Panel method based boundary element flow solver is employed for calculation of unsteady aerodynamic forces. This method is good \ncompromise of speed and accuracy for the estimation of the stability of the blades on a classical flutter. One way loose coupling technique between PM based flow solver and the structural \nmodel. For the structural part modal model synthesis (MMS) method is adopted in the ROAM solver. MMS is adopted to further reduced the computational cost. The ROAM simulated AD \nand pressure distribution over blade is compared high fidelity CFD data on real blade geometry provided by Doosan Skoda Power s.r.o. Furthermore, the ROAM results are also compared \nwith experimentally obtained results on two different linear cascade. The ROAM model shows good agreement with linear cascade results, however, there is noticeable discrepancy with real blade CFD results.
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Torque and Flow Field Optical Measurements of The Single Blade Under Stall Flutter
Procházka, Pavel P. ; Uruba, Václav ; Šnábl, Pavel
The single blade NACA0010 was exposed to the incoming flow inside a channel with rectangular cross-section. The blade was investigated for three different working regimes. The first configuration was for fixed blade. The second regime was for fluttering blade due to flow instabilities and the last one was performed for blade under force excitation. The flow field was measured using Particle Image Velocimetry. A force transducer and a small rotary encoder were used to evaluate the force ratios.
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Identifikace materiálových konstant nových pryží tlumících segmentů z modální analýzy železničního pryží odpruženého kola
Šulc, Petr ; Pešek, Luděk ; Šnábl, Pavel ; Bula, Vítězslav
Cílem modální analýzy bylo porovnat a identifikovat materiálové konstanty dvou navržených směsí pryžových tlumících segmentů železničního kola. Modální analýza byla řešena ve dvou etapách, a to experimentálně a následně numericky. Experimentální modální analýza probíhala v laboratoři ÚT s použitím jednobodového buzení (SIMO) na gumo-odpruženém kole, a to pro obě navržené varianty pryžových segmentů s označením 42809 a 46809. Z této dynamické analýzy byly získány vlastní frekvence a tvary kmitání kola v pásmu do 6,5kHz. Materiálové konstanty pryže byly získány na základě ladění materiálových parametrů pryžových segmentů, tj. modulu pružnosti a koeficientu speciálního modelu proporcionální tlumení, 3D MKP modelu železničního kola na hodnoty vlastních frekvencí a poměrných útlumů vybraných tvarů vlastního kmitání kol.
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