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1
Content available Parallelized numerical code for derivation of heat transfer coefficient from experimental data
Telega J., Doerffer P., Szwaba R., Kaczyński P.
TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk
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2015
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Vol. 19, No 2
197--205
EN
An application of parallel computation capabilities in the MATLAB language for the analysis of experimental data concerning the heat transfer coefficient on ribbed walls is presented in this paper. A description of the experimental study, mathematical model and numerical implementation is also given. The obtained results of measurements and calculations shown here clearly indicate the influence of ribbed walls on the heat transfer coefficient distribution in an internal, subsonic flow.
2
Content available Novel elecrostatic wind energy converter: an overview
Nowakowska H., Lackowski M., Ochrymiuk T., Szwaba R.
TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk
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2015
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Vol. 19, No 2
207--218
EN
The article discusses the historical development and embodiments of the concept of generating electricity from wind energy without the use of wind turbines, so called electrostatic bladeless generators or generators without moving parts. A simplified theory and the principles of operation of generators that use a motion of charged particles in an electric field occurring under the drag force of the wind are described. Two contemporary solutions utilising the principle that has reached an implementation stage, EWICON and AerovoltaicTM, are presented in detail.
3
Content available Influence of limiting walls on shock wave structure in single passage test section with compressor profile
Piotrowicz M., Flaszyński P., Szwaba R.
TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk
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2015
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Vol. 19, No 2
141--152
EN
The shock wave boundary layer interaction on the suction side of a transonic compressor blade is one of the main objectives of the TFAST project (Transition Location Effect on Shock Wave Boundary Layer Interaction). In order to look more closely into the flow structure on the suction side of the blade, a design of a turbine passage model in a rectilinear transonic wind tunnel was proposed. The model which could reproduce the flow structure, the shock wave location, the pressure distribution and the boundary layer development similar to the obtained in a reference cascade profile is the main objective of the design presented here. The design of the proposed test section is very challenging, because of the existence of a shock wave, its interaction with the boundary layer and its influence on the 3-D flow structure in the test section. The paper presents the influence of the test section geometry configuration on the flow structure as an effect of the shock wave boundary layer interaction.
4
Content available Influence of air cooling and air-jet vortex generator on flow structure in turbine passage
Szwaba R., Flaszyński P., Szumski J. A., Doerffer P.
TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk
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2015
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Vol. 19, No 2
153--166
EN
The paper concerns the experimental investigations and numerical simulations of a high loaded model of a turbine blade. An increase in the blade load leads to enlargement of a local supersonic zone terminated by a shock wave on the suction side. The Mach number upstream of the shock reaches up to 1.6. The interaction of the shock wave with a boundary layer at such a high Mach number leads to a strong separation. Streamwise vortices generated by air-jets were used for the interaction control. The work presents the experimental and numerical results of the application of an air-jets vortex generator on the suction side of cooled turbine blades. Very interesting results were obtained in the context of the air cooling and air-jet vortex generator influence on the flow structure in the turbine passage.
5
Content available Aerodynamic anhancement in inner channel of turbine blade
Kaczyński P., Szwaba R., Puchowski B., Doerffer P., Flaszyński P.
TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk
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2015
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Vol. 19, No 2
101--110
EN
This paper presents the numerical and experimental study of the flow structure in a radial cooling passage model of a gas turbine blade. The investigations focus on the flow aerodynamics in the channel, which is an accurate representation of the configuration used in aero engines. The flow structure and pressure drop were measured by classical measurement techniques. The stagnation pressure and velocity measurements in a channel outlet plane were performed. The investigations concerning the flow field and heat transfer used in the design of radial cooling passages are often developed from simplified models. It is important to note that real engine passages do not have perfect rectangular cross sections, but include corner fillets, ribs with fillet radii and special orientation. Therefore, this work provides detailed fluid flow data for a model of radial cooling geometry which possesses very realistic features. The main purpose of these investigations was to study different channel configurations and their influence on the flow structure and pressure losses in a radial cooling passage of a gas turbine blade.
6
Oddziaływanie strumieniowych generatorów wirów wzdłużnych na obszar oderwania
Szwaba R.
Zeszyty Naukowe Instytutu Maszyn Przepływowych Polskiej Akademii Nauk w Gdańsku
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2013
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nr 558/1517
1--187
7
Experimental and numerical analysis of a streamwise vortex generator for subsonic flow
Flaszyński P., Szwaba R.
Inżynieria Chemiczna i Procesowa
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2006
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T. 27, z. 3/1
985-997
EN
The total pressure measurements at two sections downstream of the jet hole (streamwise vortex generator) for the main flow Mach numbers 0.3 and 0.8 are presented. Experimental data are compared with the numerical results (FLUENT and SPARC) for one jet hole inclination. Differences of the streamwise vortex structures predicted by the codes are compared.
PL
Przedstawiono wyniki obliczeń numerycznych dwoma kodami (FLUENT i SPARC) na tle badań eksperymentalnych generatora wirów wzdłużnych dla liczb Macha przepływu głównego 0.3 i 0.8. Porównano ciśnienie całkowite w dwóch przekrojach za otworem, przez który odbywa się wydmuch. Przedstawiono strukturę wiru wzdłużnego uzyskaną za pomocą obu programów.
8
Measurement of the air density gradient in transonic flows by the schlieren - speckle photography technique
Szwaba R.
Turbulence : international journal
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2005
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Vol. 11
45-53
EN
This paper presents the description of two non-intrusive optical measurement techniques, which based on refraction and deflection of light rays. These techniques are the Schlieren method and the speckle photography. Especially the latter one have been gain an interesting recently due to dynamic development of computer techniques and digital photography. One of the important parameters in speckle photography is the resolution of the CCD chip of the camera and available resolution reach 16 mln pixels nowadays. Using tliis measurement technique we can obtain the quantitative information of density gradient in the flow with the high spatial resolution. This feature cause that this measurement technique can be use for investigation in turbulent flow.
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