Pracovní podmínky atomizérů v reálných operacích v průmyslu a zemědělství se liší od podmínek laboratorních, ve kterých jsou atomizéry testovány. Částečné přiblížení k realističtějším podmínkám nám může poskytnout použití větrného tunelu. Větrný tunel se používá k simulaci okolního proudění. Studium spreje ve větrném tunelu nám poskytne realističtější představu o chování spreje. Tato diplomová práce se zabývá návrhem malého, nízko rychlostního větrného tunelu pro experimenty s tlakovými vířivými tryskami s obtokem v příčném a podélném proudění. Existuje mnoho typů větrných tunelů, ale jako nejvhodnější typ byl zvolen otevřený, výtlačný větrný tunel s uzavřenou testovací sekcí. Výhodou jsou jeho kompaktní rozměry, ochrana částí tunelu před kapičkami spreje a poměrně jednoduchý návrh. Konstrukce větrného tunelu se skládá z několika částí, každá část je zkonstruována tak, aby bylo dosaženo co nejlepší kvality proudu v testovací sekci. Sprej je zkoumán pomocí optických metod Fázové Dopplerovské anemometrie (PDA), Laserové Dopplerovské anemometrie (LDA), Integrální laserová anemometrie (PIV) a pomocí vysokorychlostního záznamu. Tyto optické metody kladou speciální požadavky na konstrukci tunelu, především na konstrukci testovací sekce, která musí umožňovat optický přístup ke spreji a musí být pro tyto měřící techniky uzpůsobena. Rychlost v testovací sekci se pohybuje v rozmezí 0 až 40 m/s s intenzitou turbulence pod 0,7 %. V závěru práce je ukázka vizualizace spreje, v příčném proudění, pomocí vysokorychlostní kamery. Okolní proudění mění rozpadovou vzdálenost spreje, úhel kužele spreje i jeho tvar. Dochází k vymývání menších kapek, které jsou unášeny okolním proudem.

An approach for designing a high-enthalpy wind tunnel driven by exothermic chemical reactions was developed. Nozzle contours were designed using CONTUR, a program implementing the method of characteristics, to design nozzle contours at various flow conditions. A reacting mixture including nitrous oxide has been identified as the best candidate for providing clean air at high temperatures. The nitrous oxide has a few performance factors that were considered, specifically the combustion of the gas. Initial CFD simulations were performed on the nozzle and test region to validate flow characteristics and possible issues. Initial results show a fairly uniform exit velocity and ability to perform testing. In a second phase of the work, two generic, high-speed missile configurations were explored using numerical simulation. The mean flow was computed on both geometries at 0 and 45 roll and 0, 1, and 10 angle of attack. The computations identified complex flow structures, including three-dimensional shock/boundary-layer interactions, that varied considerably with angle of attack. <br>

Ce travail de recherche a pour objectif de présenter la conception de tunnels au moyen de la méthode hyperstatique aux coefficients de réaction (HRM). Les modèles développés par la méthode HRM sont tout d'abord proposés pour étudier le comportement de tunnels en forme de fer à cheval inversée dans différentes conditions, par exemple en considérant deux cas de charge, deux géométries différentes de revêtement de tunnel, deux cas de coefficients de réaction différents, changement de la rigidité des coefficients de réaction, conditions de sol multicouches, surcharges en surface et sol saturés. Les modèles présentés permettent d’aboutir à des prévisions qualitatives avec une efficacité de calcul élevée par rapport à la modélisation numérique en différences finies. Une analyse paramétrique est ensuite réalisée pour estimer le comportement du revêtement de tunnel en forme de fer à cheval dans un grand nombre de cas couvrant les conditions généralement rencontrées dans la pratique. Ensuite, en prenant comme exemple un tunnel métropolitain à deux voies, une série de fonctions mathématiques est déduite et utilisée dans le processus d'optimisation d’un tunnel de forme complexe, ce qui offre aux concepteurs de tunnels un support théorique leur permettant de choisir la forme optimale du tunnel à mettre en oeuvre. L’effet de différents paramètres, tels que le coefficient des terres au repos, le module d’Young du sol, la profondeur du tunnel, les surcharges en surface, sur les efforts internes et la forme du tunnel. Dans la dernière partie du manuscrit, l’influence d’un changement de température sur les efforts dans le revêtement d’un tunnel circulaire au moyen de la méthode HRM est étudiée en tenant compte de différents facteurs, tels que l’épaisseur du revêtement de tunnel, le module d’élasticité du revêtement et le coefficient de dilatation thermique du sol. / This research work aims to present the design of tunnel by means of the Hyperstatic Reaction Method (HRM). The models developed by the HRM method are firstly proposed for investigating the behaviour of U-shaped tunnels under different conditions, considering two load cases, two different geometries of U-shaped tunnel lining, two different cases of springs, change of the spring stiffness, multi-layered soil conditions, surcharge loading, and saturated soil masses. The presented models permit to obtain good predictions with a high computational efficiency in comparison to finite difference numerical modelling. Then a parametric analysis has permitted to estimate the U-shaped tunnel lining behaviour in a large number of cases which cover the conditions that are generally encountered in practice. Thereafter, taking a twin-lane metro tunnel as an example, a series of mathematical functions used in the optimization progress of sub-rectangular tunnel shape is deduced, which gives to tunnel designers a theoretical support to choose the optimal sub-rectangular tunnel shape. The effect of different parameters, like the lateral earth pressure factor, soil Young’s modulus, tunnel depth, surface loads, on the internal forces and shape of sub-rectangular tunnel is then given. In the last part of the manuscript, the influence of a temperature change on the lining forces of circular tunnel by means of the HRM method is investigated, considering different factors, such as the tunnel lining thickness, lining elastic modulus and ground coefficient of thermal expansion.

The path to future aero-engines with more efficient engine architectures requires advanced thermal management technologies to handle the demand of refrigeration and lubrication. Oil systems, holding a double function as lubricant and coolant circuits, require supplemental cooling sources to the conventional fuel based cooling systems as the current oil thermal capacity becomes saturated with future engine developments. The present research focuses on air/oil coolers, which geometrical characteristics and location are designed to minimize aerodynamic effects while maximizing the thermal exchange. The heat exchangers composed of parallel fins are integrated at the inner wall of the secondary duct of a turbofan. The analysis of the interaction between the three-dimensional high velocity bypass flow and the heat exchangers is essential to evaluate and optimize the aero-thermodynamic performances, and to provide data for engine modeling. The objectives of this research are the development of engine testing methods alternative to flight testing, and the characterization of the aerothermal behavior of different finned heat exchanger configurations. A new blow-down wind tunnel test facility was specifically designed to replicate the engine bypass flow in the region of the splitter. The annular sector type test section consists on a complex 3D geometry, as a result of three dimensional numerical flow simulations. The flow evolves over the splitter duplicated at real scale, guided by helicoidally shaped lateral walls. The development of measurement techniques for the present application involved the design of instrumentation, testing procedures and data reduction methods. Detailed studies were focused on multi-hole and fine wire thermocouple probes. Two types of test campaigns were performed dedicated to: flow measurements along the test section for different test configurations, i.e. in the absence of heat exchangers and in the presence of different heat exchanger geometries, and heat transfer measurements on the heat exchanger. As a result contours of flow velocity, angular distributions, total and static pressures, temperatures and turbulence intensities, at different bypass duct axial positions, as well as wall pressures along the test section, were obtained. The analysis of the flow development along the test section allowed the understanding of the different flow behaviors for each test configuration. Comparison of flow variables at each measurement plane permitted quantifying and contrasting the different flow disturbances. Detailed analyses of the flow downstream of the heat exchangers were assessed to characterize the flow in the fins¿ wake region. The aerodynamic performance of each heat exchanger configuration was evaluated in terms of non dimensional pressure losses. Fins convective heat transfer characteristics were derived from the infrared fin surface temperature measurements through a new methodology based on inverse heat transfer methods coupled with conductive heat flux models. The experimental characterization permitted to evaluate the cooling capacity of the investigated type of heat exchangers for the design operational conditions. Finally, the thermal efficiency of the heat exchanger at different points of the flight envelope during a typical commercial mission was estimated by extrapolating the convective properties of the flow to flight conditions. / Villafañe Roca, L. (2013). Experimental Aerothermal Performance of Turbofan Bypass Flow Heat Exchangers [Tesis doctoral]. Universitat Politècnica de València. https://doi.org/10.4995/Thesis/10251/34774