Thermoacoustic instabilities in modern high-performance, low-emission gas turbine engines are often observable as large amplitude pressure oscillations and can result in serious performance and structural degradations. These acoustic oscillations can cause oscillations in combustor through-flows and given the right phase conditions, can also drive unsteady heat release. This coupling has the potential to enhance the amplitude of pressure oscillations. To curb the potential harms caused by the existence of thermoacoustic instabilities, recent efforts have focused on the active suppression and even complete control of these instabilities. Intuitively, development of effective active combustion control methodologies is strongly dependent on the knowledge of the onset and sustenance of thermoacoustic instabilities. Specially, non-premixed spray combustion environment pose additional challenges due to the inherent unstable dynamics of sprays. The understanding of the manner in which the combustor acoustics affect the spray characteristics, which in turn result in heat release oscillation, is therefore, of paramount importance. The experimental investigations and the modeling studies conducted towards achieving this knowledge have been presented in this dissertation. Experimental efforts comprise both reacting and non-reacting flow studies. Reacting flow experiments were conducted on a overall lean direct injection, swirl-stabilized combustor rig. The investigations spanned combustor characterization and stability mapping over the operating regime. All experiments were performed under atmospheric pressure condition, which is considered as an obvious first step towards providing valuable insights into more intense processes in actual gas turbine combustors. The onset of thermoacoustic instability and the transition of the combustor to two unstable regimes were investigated via phase-locked chemiluminescence imaging and measurement and phase-locked acoustic characterization. It was found that the onset of the thermoacoustic instability is a function of the energy gain of the system, while the sustenance of instability is due to the in-phase relationship between combustor acoustics and unsteady heat release driven by acoustic oscillations. The presence of non-linearities in the system between combustor acoustic and heat release and also between combustor acoustics and air through-flow were found to exist. The impact of high amplitude limit-cycle pressure on droplet breakdown under very low mean airflow and the localized effects of forced primary fuel modulations on heat release were also investigated. The non-reacting flow experiments were conducted to study the spray behavior under the presence of an acoustic field. An isothermal acoustic rig was specially fabricated, where the pressure oscillations were generated using an acoustic driver. Phase Doppler Anemometry was used to measure the droplet velocities and sizes under varying acoustic forcing conditions and spray feed pressures. Measurements made at different locations in the spray were related to these variations in mean and unsteady inputs. The droplet velocities were found to show a second order response to acoustic forcing with the cut-off frequency equal to the relaxation time corresponding to mean droplet size. It was also found that under acoustic forcing the droplets migrate radially away from the spray centerline and show oscillatory excursions in their movement. Non-reacting flow experiments were also performed using Time-Resolved Digital Particle Image Velocimetry to characterize modulated sprays. Frequency response of droplet diameters were analyzed in the pulsed spray. These pilot experiments were conducted to assess the capability of the system to measure dynamic data. Modeling efforts were undertaken to gain physical insights of spray dynamics under the influence of acoustic forcing and to explain the experimental findings. The radial migration of droplets and their oscillatory movement were validated. The flame characteristics in the two unstable regimes and the transition between them were explained. It was found that under certain acoustic and mean air-flow condition, bands of high droplet densities were formed which resulted in diffusion type group burning of droplets. It was also shown that very high acoustic amplitudes cause secondary breakup of droplets. / Ph. D.

Trailing edge noise control is an important problem associated mainly with wind turbines. As turbulence in the air flows over a wind turbine blade, it impacts the trailing edge and scatters, producing noise. Traditional methods of noise control involve modifying the physical trailing edge, or the scattering efficiency. Recently, inspired by the downy covering of owl feathers, researchers developed treatments that can be applied to the trailing edge to significantly reduce trailing edge noise. It was hypothesized that the noise reduction was due to manipulating the incoming turbulence, rather than the physical trailing edge itself, representing a new method of noise control. However, only acoustic measurements were reported, meaning the associated flow physics were still unknown. This thesis describes a comprehensive wall jet experiment to measure the flow effects near the bio-inspired treatments, termed “finlets” and “rails,” and relate those flow effects to the noise reduction. This was done using far-field microphones, a single hot-wire probe, and surface pressure fluctuation microphones. The far-field noise results showed that each treatment successfully reduced the noise, by up to 7 dB in some cases. The surface pressure measurements showed that the spanwise coherence was slightly reduced when the treatments were applied to the trailing edge. The velocity measurements clearly established the presence of a shear layer near the top of the treatments. As a whole, the dataset led to the shear-sheltering hypothesis: the bio-inspired treatments are effective based on reducing the spanwise pressure correlation and by sheltering the trailing edge from turbulent structures with the shear layer they create. / Master of Science / This thesis describes a project aimed at developing a technology inspired by the silent flight of owls, with the end goal of using this technology to reduce the noise generated by wind turbines. Specifically, the phenomenon known as "trailing edge noise" is the primary source of wind turbine noise, and is the noise source of interest here. It occurs when air turbulence (which can be thought of as unsteady air fluctuations) crashes into the rear (trailing) edge of wind turbine blades, scattering and producing noise. Typically, methods of reducing this noise source involve changing the shape of the trailing edge; this may not always be practical for existing wind turbines. Recently, inspired by the downy covering of owl feathers, researchers developed treatments that can be applied directly to the trailing edge, significantly reducing trailing edge noise. This bio-inspired concept was verified with numerous acoustic measurements. Based on those measurements, researchers hypothesized that the noise reduction was achieved by manipulating the incoming turbulence before it scattered off the trailing edge, rather than by changing the existing wind turbine blade, representing a new method of trailing edge noise control. However, as only acoustic measurements (not flow measurements) were reported, the changes in turbulence could not be examined. With the above motivation in mind, this thesis describes a comprehensive wind tunnel experiment to measure the changes in the aerodynamics and turbulence near the bio-inspired treatments, and relate those changes to the reduction in trailing edge noise. This was done using a hot-wire probe to measure the aerodynamics, as well as microphones to measure the radiated noise and surface pressure fluctuations. As a whole, the experimental results led to the shear-sheltering hypothesis: the bio-inspired treatments are effective based on the creation of a shear layer (a thin region between areas with different air speeds) which shelters the trailing edge from some turbulence, as well as by de-correlating surface pressure fluctuations along the trailing edge.

Highly loaded single stage gas turbines are being developed to minimize the turbine size and weight. Such highly loaded turbines often result in transonic flows, which imply a reduction in the efficiency due to the shock losses. The efficiency of a turbine is defined as the ratio between the real work extracted by the turbine rotor from the fluid and the maximum available enthalpy for a given pressure ratio. The relationship between turbine performance and design parameters is not yet fully comprehended due to the complexity of the flow field and unsteady flow field interactions. Hence, experimental and numerical studies remain necessary to understand the flow behavior at different conditions to advance the state of the art of the prediction tools. The purpose of the current research is to develop a methodology to determine the efficiency with an accuracy better than 1 % in a cooled and uncooled high pressure (HP) turbine tested in a short duration facility with a running time of about 0.4s. Such low level of uncertainty requires the accurate evaluation of a large number of quantities simultaneously, namely the mass flow of the mainstream, the coolant, and leakage flows properties, the inlet total pressure and total temperature, the stage exit total pressure, the shaft power, the mechanical losses and the heat transfer. The experimental work is carried out in a compression tube facility that allows testing the turbine at the temperature ratios, Re and Mach numbers encountered in real engines. The stage mass flow is controlled by a variable sonic throat located downstream of the stage exit. Due to the absence of any brake, the turbine power is converted into rotor acceleration. The accurate measurement of this acceleration as well as those of the inertia and the rotational speed provides the shaft power. The inertia of the whole rotating assembly was accurately determined by accelerating and decelerating the shaft with a known energy. The mass-flow is derived from the measured turbine inlet total pressure and the vane sonic throat. The turbine sonic throat was evaluated based on a zero-dimensional model of the turbine. The efficiencies of two transonic turbines are measured at design and off-design conditions. The turbine design efficiency is obtained as 91.8 %. The repeatability of the measurements for 95% confidence level varies between 0.3 % and 1.1 % of the efficiency depending on the test case. The theoretical uncertainty level of 1.2 % is mainly affected by the uncertainty of exit total pressure measurements. Additionally, the effect of vane trailing edge shock formations and their interactions with the rotor blade are analyzed based on the experimental data, the numerical tools and the loss correlations. The changes of blade and vane performances are measured at mid-span for three different pressure ratios which influence the vane and rotor shock mechanisms. Moreover, the unsteady forces on the rotor blades and the rotor disk were calculated by integration of the unsteady static pressure field on the rotor surface.

Cette étude s'inscrit dans le cadre de la compréhension des phénomènes ayant lieu dans les chambres de combustion aéronautiques. Ces phénomènes étant multiples et complexes, des simplifications sont nécessaires. L'étude se focalise uniquement sur l'évaporation de gouttelettes bi-composant en écoulements turbulents. De nombreux modèles d'évaporation existent mais l'influence de la turbulence dans le cas d'un spray est encore mal comprise. Alors que la turbulence augmente l'évaporation d'une goutte isolée, elle peut amener à la création d'amas de gouttes qui vont au contraire ralentir l'évaporation. Cette étude a donc pour but de fournir un certain nombre de données quantitatives permettant une meilleure compréhension de ces phénomènes et une amélioration des modèles. L'approche est expérimentale. L'objectif est de quantifier, d'une part l'évaporation et la dispersion de gouttelettes, d'autre part le mélange vapeur dans un écoulement de canal dont les caractéristiques seront connues. Afin de simplifier les conditions expérimentales, la température est moins élevée que dans le cas réel et la pression est la pression atmosphérique. De plus, les gouttelettes sont bi-composant (octane/3-pentanone). Le banc utilisé est divisé en deux parties. Sa partie supérieure est composée d'un système de génération de l'écoulement turbulent et d'un injecteur de gouttelettes. Sa partie inférieure est composée d'une veine dans laquelle l'écoulement diphasique est analysé. L'écoulement porteur est étudié sans le spray par Anémométrie Laser Doppler. L'écoulement présente une forte turbulence, des profils plats de vitesses moyennes et de f uctuations de vitesses, en zone établie. Les propriétés d'isotropie et la décroissance de la turbulence sont proches de celles obtenues en turbulence de grille. La phase dispersée est suivie à chaud à l'aide de deux méthodes : par Anémométrie Phase Doppler et par Fluorescence Laser Induite. L'Anémométrie Phase Doppler permet d'avoir accès simultanément au diamètre et à la vitesse de chaque goutte passant à travers le volume de mesure. En raison de la forte polydispersion, les comportements des gouttelettes vis à vis de la turbulence sont très différents. En revanche, l'homogénéisation est rapide quelque soit la classe de taille. La présence d'amas dont la quantité diminue en aval dans la veine est mis en avant. La Fluorescence Laser Induite mesure la quantité de molécules de 3-pentanone en phase liquide. L'évolution de la concentration liquide, des flux de masse et des amas est décrite. La Fluorescence Induite par Laser permet aussi de suivre la quantité de 3-pentanone en phase vapeur. L'évolution des prof ls radiaux et axiaux de concentration moyenne et des f uctuations de concentration est présentée. L'homogénéisation du mélange est quantifiée. / This work aims to understand the phenomena that occur in a combustion chamber. Due to the complexity of the phenomena encountered, simplifications are made. This study only focuses on multicomponent droplet evaporation in turbulent flows. Many evaporation models exist, but the influence of turbulence on a spray is yet not well understood. On one hand, turbulence increases the droplet evaporation rate. On the other hand, it may generate clusters, in which saturation stops the process. This study aims to give a database that can be used to improve the physical understanding of the process and to improve model performances. This is an experimental approach. The objective is to measure evaporation and dispersion of droplets and vapour mixing in a well-known turbulent flow. In the simplified test case studied here, the temperature is lower than in a real case and the pressure is atmospheric. The droplets are bi-component(octane/3-pentanone). The experimental set-up is divided into two parts. The first part, at the top, consists in a turbulence flow generator and a droplet injection device. The second part is a channel in which the two- hase flow is analysed. The carrier flow is measured using Laser Doppler Anemometry. The main flow properties are : high turbulence levels, flat profiles for the mean velocity and velocity fluctuations. The turbulence decreases and isotropic properties are close to those of grid turbulence. The dispersed phase is measured using Phase Doppler Anemometry (PDA) and Laser Induced Fluorescence (LIF). The velocity and diameter of each droplet passing through the measurement volume is measured by the PDA technique. There is a large variety of droplet behaviours due to the large polydispersion and turbulence. Droplet clusters are measured. Their amounts decrease with the distance from the injector. The concentration of 3-pentanone can be measured with the LIF technique. The evolution of the liquid concentration, mass flux and droplet clusters is described. The mean vapour concentration and its fluctuations are measured along the axial and radial axis. The mixing of the vapour is characterised

The Martian atmosphere is of great scientific interest, both because of its similarity to Earth’s atmosphere, and because of its relevance to exploration of Mars. Although satellite instruments have provided a wealth of atmospheric data, they have provided little information about the atmospheric boundary layer. Conditions in the lowest few metres of the Martian atmosphere are perhaps the most directly interesting to humans, as this is the portion of our own atmosphere with which we have the most contact. In this thesis is described the design, calibration and operations planning for a new wind sensor for use on Mars. This sensor is lighter and smaller than previous Mars wind sensors. At the time of writing, the wind sensor is on its way to Mars as part of the science payload of Beagle 2, a small exobiology lander due to arrive in December 2003. The Beagle 2 wind sensor (B2WS) is a hot-film anemometer. Three platinum films are equally spaced around the surface of a vertical cylinder. A known current is dissipated in each film, heating the film 40-80°C above the ambient gas temperature. The film temperature is obtained by measuring its resistance. An effective heat transfer coefficient is then calculated for each film. A novel scheme has been developed which allows calculation of a wind vector from the differences between these heat transfer coefficients, rather than from their average. This makes the measured wind vector less prone to common-mode errors such as uncertainties in air temperature or sky temperature. The sensor was calibrated in a low density wind tunnel, optimised to provide stable winds of air or carbon dioxide at Martian pressures (5 – 10 mbar) and speeds (0.5 – 30 m/s). The flow field in the test section was calculated using analytical and finite element modelling techniques, and validated experimentally using a pitot probe. This facility’s stability and accuracy represent a significant improvement over previous calibration facilities. An analytical model of heat flow in the sensor has been developed in order to permit correction for conditions which may be encountered on Mars, but were not tested for in the wind tunnel. The wind sensor’s performance in a real Martian atmosphere is simulated using wind and temperature data from a previous Mars lander. The position of the wind sensor position at the end of Beagle 2's motorised arm allows several new possibilities for wind measurement on Mars that were unavailable in previous missions. The height of the wind and air temperature sensors can be adjusted to any height between 20 and 95 cm above the ground. The temperature sensor can be scanned horizontally and vertically above the lander to study convective updrafts above the heated lander. Planned operations sequences on Mars are discussed.

Human health is significantly influenced by inhaled aerosols. Insight to the aerosol transport and deposition mechanisms is a prerequisite for both, toxicological protection against harmful particles and efficient application of inhaled therapeutic aerosols. The purpose of this doctoral thesis was to gain new knowledge of this topic on the basis of in vitro measurements. Phase-Doppler Anemometry was chosen for aerosol transport measurement, for it allows simultaneous measurement of particle size and velocity. Results were processed by means of statistical methods and frequency analysis. Deposition of spherical aerosol particles was measured by Positron Emission Tomography, while deposition of fibrous aerosol was measured by Phase-Contrast Microscopy combined with automated image analysis. All experiments were performed on physical models created on the basis of the real lung geometry. New knowledge of flow characteristics, transition from laminar to turbulent flow, effect of breathing pattern or particle size on aerosol transport and deposition in human lungs are outcomes of this work. Significant effect of the oral cavity was ascertained due to comparison of aerosol deposition in realistic and semi-realistic model with cylindrical smooth walls. Acquired data not merely extended our knowledge of aerosol behavior in lungs but it can also be used for validation of numerical simulations.

Afin de satisfaire les exigences de sécurité requises dans l’aviation civile, la stratégie adoptée consiste à multiplier les chaînes de mesure pour une même information. Il est aujourd’hui recommandé d’introduire une chaîne de mesure dissemblable (reposant sur un principe physique différent) afin d’augmenter le niveau de sécurité. Dans cette optique, Thales mène des travaux sur le développement d’un anémomètre laser Doppler embarqué sur aéronef. Ce capteur, composé de quatre axes LiDAR (Light Detection And Ranging) répartis autour de l’avion, permet d’estimer la vitesse air par l’analyse de la réflexion de l’onde laser émise sur les particules présentes dans l’air.L’objectif de ces travaux est de concevoir une chaîne de traitement du signal LiDAR adaptée à un capteur sur avion. Cette chaîne, basée sur une représentation temps-fréquence, inclut des étapes de détection du signal utile optimisée pour les conditions de faible ensemencement en particules, de sélection des aérosols utiles dans un nuage et d’estimation robuste afin de contrôler la qualité de la mesure. Cette chaîne de traitement, évaluée lors d’une campagne d’essais réalisée à l’observatoire du Pic du Midi, apporte un gain de performances élevé dans les situations critiques. L’architecture du système a été le second axe d’étude. Une méthode d’estimation du vecteur vitesse à partir des estimations effectuées sur chaque axe LiDAR et d’un modèle aérodynamique de l’avion permet de compenser les perturbations observées à proximité de ce dernier. Puis, une procédure d’optimisation de l’architecture est proposée afin d’améliorer les performances du capteur. Les performances de la chaîne de traitement présentée devront être évaluées en conditions réelles, lors d’essais en vol, afin de sonder une grande variété de conditions atmosphériques et d’évaluer le gain apporté et les faiblesses éventuelles du traitement proposé en fonction de ces conditions. / The method use to respect security requirements in civil aviation consists in multiplying measuring chains for the same information. Now, it is recommended to add a dissimilar measuring chain, based on a different physical principle, in order to improve security level. Thus, Thales works on the development of a laser Doppler anemometer embedded on aircraft. This sensor is composed by four LiDAR (Light Detection And Ranging) axis distributed around the aircraft and air speed is estimated by the analysis of the reflection of the emitted laser wave on particles.This thesis objective is to design a LiDAR signal processing chain adapted to an aircraft sensor. The process is based on a time-frequency representation and it includes methods for signal detection in low concentrated air mass, useful particles selection in clouds and robust estimation to control measure reliability. The process has been evaluated during a test campaign realized at the Pic du Midi observatory. Its performances are greatly improved, especially in critical situations.The system architecture has also been studied. An estimation method designed from estimations performed on different LiDAR axis and an aerodynamic model of an aircraft is proposed in order to compensate for air mass perturbations close to the aircraft. Then, an optimization process is presented to improve sensor performances.The signal processing chain will have to be evaluated by flight tests, to explore a large atmospheric conditions variety and to quantify its strengths and weaknesses depending on conditions.

This work is concerned with the response of a Blasius boundary layer to dielectric-barrier-discharge (DBD) plasma actuators for the purpose of using these devices in bypass transition control. The plasma actuators consist of a spanwise-periodic array of high voltage electrodes, which are oriented to produce streamwise vortex pairs. The structure of actuator-induced streaks is measured using hot-wire anemometry over a streamwise distance of approximately 100 boundary layer thicknesses, and is decomposed into 4 spanwise Fourier modes. The modal content and corresponding streamwise growth characteristics are discussed for ten plasma actuator geometries over multiple excitation voltages and freestream velocities. Actuator power consumption was found to control the streak amplitude, whereas freestream velocity affected both amplitude and streamwise extent of the streaks. A common relationship between disturbance energy and power consumption was found among actuators of different dielectric thickness and similar electrode geometry.

This work is concerned with the response of a Blasius boundary layer to dielectric-barrier-discharge (DBD) plasma actuators for the purpose of using these devices in bypass transition control. The plasma actuators consist of a spanwise-periodic array of high voltage electrodes, which are oriented to produce streamwise vortex pairs. The structure of actuator-induced streaks is measured using hot-wire anemometry over a streamwise distance of approximately 100 boundary layer thicknesses, and is decomposed into 4 spanwise Fourier modes. The modal content and corresponding streamwise growth characteristics are discussed for ten plasma actuator geometries over multiple excitation voltages and freestream velocities. Actuator power consumption was found to control the streak amplitude, whereas freestream velocity affected both amplitude and streamwise extent of the streaks. A common relationship between disturbance energy and power consumption was found among actuators of different dielectric thickness and similar electrode geometry.

Η διδακτορική διατριβή πραγματεύεται την πειραματική διερεύνηση της αλληλεπίδρασης δέσμης εκροής νέφους σταγονιδίων νερού με το θερμικά στρωματοποιημένο,τυρβώδες ρευστο-θερμικό πεδίο που αναπτύσσεται πάνω από οριζόντια θερμαινόμενη επίπεδη επιφάνεια. Τα φαινόμενα και οι φυσικοί μηχανισμοί που διέπουν την ως άνω αλληλεπίδραση πέρα από τη σημασία τους σε σχέση με τη βασική έρευνα στο πεδίο των ρευστοθερμικών φαινομένων, παρουσιάζουν ενδιαφέρον σε πληθώρα πρακτικών προβλημάτων όπως κατά τον ψεκασμό καυσίμου σε κινητήρες εσωτερικής καύσης και καυστήρες, στη διφασική ψύξη ηλεκτρονικών, στην μετεωρολογία, στην πυρόσβεση, σε διεργασίες απόθεσης και επικάλυψης κ.α. Το ρευστο-θερμικό πεδίο αναπτύσσεται πάνω από οριζόντια θερμαινόμενη επιφάνεια μεταλλικής πλάκας μέσα σε ορθογωνική κοιλότητα με ανοικτή οροφή. Το νέφος σταγονιδίων δημιουργείται σε έναν νεφελοποιητή και εκτοξεύεται μέσα από ένα ακροφύσιο κυλινδρικού σωλήνα εσωτερικής διαμέτρου 4mm, κάθετα προς την οριζόντια επίπεδη επιφάνεια και σε σημαντική απόσταση από αυτήν (50cm), δημιουργώντας αρχικά μια διφασική δέσμη εκροής σταγονιδίων. Για την δημιουργία βάσης δεδομένων αναφοράς, σημαντικό μέρος της εργασίας αναφέρεται στην καταγραφή και μελέτη του θερμικού πεδίου ελεύθερης συναγωγής που δημιουργείται πάνω από τη θερμαινόμενη πλάκα χωρίς την παρουσία σταγονιδίων. Αντίστοιχα μελετήθηκε η ανάπτυξη της δέσμης εκροής σταγονιδίων σε ισοθερμοκρασιακές συνθήκες. Η παραμετρική μελέτη της αλληλεπίδρασης δέσμης εκροής σταγονιδίων και θερμικά στρωματοποιημένου πεδίου πραγματοποιήθηκε για δέσμες σε δύο αριθμούς Reynolds και για δύο ρυθμούς ροής θερμότητας από την πλάκα. Οι αριθμοί Reynolds που επιβάλλονται στη ροή δέσμης του νέφους (mistjet) είναι σχετικά χαμηλοί έτσι ώστε να ισχυροποιηθεί σχετικά η επίδραση του τοιχώματος και κυρίως οι ροϊκές δομές που δημιουργούνται λόγω των ανωστικών δυνάμεων κοντά στη θερμαινόμενη επιφάνεια. Η σύνθετη ροή που παράγεται λόγω της σημαντικής απόστασης μεταξύ του ακροφυσίου και της επίπεδης επιφάνειας - στόχου κατατάσσεται στην κατηγορία των δεσμών εκροής ασθενούς πρόσκρουσης. Οι παράμετροι που εξετάζονται περιλαμβάνουν μέσα και τυρβώδη χαρακτηριστικά τόσο των σταγόνων (μέγεθος και ταχύτητα), όσο και της θερμοκρασιακής κατανομής πάνω από την θερμαινόμενη πλάκα. Το θερμικό πεδίο σε συνθήκες ελεύθερης μεταφοράς και υπό την επίδραση της ροής των σταγονιδίων καταγράφτηκε με τη βοήθεια θερμοζεύγους πολύ μικρών διαστάσεων ώστε να αλλοιώνει όσο το δυνατόν λιγότερο τη ροή. Οι διαστάσεις του αισθητηρίου είναι σημαντικά μικρότερες της κλίμακας μήκους Kolmogorov και επομένως το αισθητήριο κρίθηκε ικανό για την ανάλυση όλων των σχετικών κλιμάκων της ροής. Το πεδίο νέφους σταγονιδίων μελετήθηκε με την τεχνική Ανεμομετρίας Φάσης Doppler (PhaseDopplerAnemometry - PDA) η οποία επιτρέπει την μέτρηση τόσο της ταχύτητας όσο και του μεγέθους των σταγονιδίων παρέχοντας τη δυνατότητα συσχέτισης των δύο μεγεθών για τον ενδελεχή χαρακτηρισμό της συμπεριφοράς των σταγονιδίων. Η τεχνική αυτή είναι μια από τις λίγες μη παρεμβατικές μεθόδους σημειακών μετρήσεων σε διφασικά ροϊκά πεδία η οποία δίνει πληροφορία για τη συγκέντρωση και την παροχή, με την τελευταία να αποτελεί σημαντικό εργαλείο στον υπολογισμό της εξάτμισης. Τα αποτελέσματα των μετρήσεων κατά την αλληλεπίδραση των πεδίων (θερμικού και σταγονιδίων) μελετώνται και συγκρίνονται με τις συνθήκες αναφοράς της στρωματοποιημένης ροής του θερμοκρασιακού πεδίου και της ισόθερμης ροής του πεδίου ταχυτήτων δίνοντας πληροφορία για την επίδραση του νέφους σταγονιδίων στους μηχανισμούς τυρβώδους μεταφοράς. Αναγνωρίστηκε ως κυρίαρχη δομή του πεδίου συναγωγής το κινούμενο πλούμιο συχνά μορφής μανιταριού. Η μορφή των κατανομών πυκνότητας πιθανότητας (PDF) ερμηνεύθηκε σε σχέση με το ιστορικό δημιουργίας και ανταλαγών θερμότητας των επί μέρους αερίων μαζών που διέρχοτναι από τη θέση μέτρησης. Στις κατανομές φασματικής ισχύος (PSD) του σήματος της θερμοκρασίας αναγνωρίσθηκε ιδιοσυχνότηταπου υποδεικνύει την παρουσία δομής μεγάλης κλίμακας. Αναφορικά με το πεδίο σταγονιδίων παρατηρήθηκε ότι η παρουσία της επιφάνειας – στόχου επιβραδύνει τις δέσμες πρόσπτωσης ελαττώνοντας και τις διακυμάνσεις στην περιοχή του τοιχώματος. Η θέρμανση επηρεάζει τις μέσες και κυμαινόμενες ταχύτητες σε σημαντική απόσταση από την οριζόντια πλάκα, ενώ το μέγεθος των σταγονιδίων μειώνεται κατάντη της ροής με διαφορετικές τάσεις ως προς τον Re. Αυξημένες τιμές της μέσης διαμέτρου Sauter (D32) παρατηρούνται κοντά στην επιφάνεια ειδικά για την περίπτωση ισόθερμου ψεκασμού του υψηλότερου Re. Η θέρμανση της επιφάνειας έχει σημαντική επίπτωση στον περιορισμό της αυξητικής τάσης της παροχής αέρα λόγω συμπαράσυρσης, που είναι πιο εμφανής στις περιπτώσεις χαμηλού Re. / The interaction of a water mist jet with the thermally stratified turbulent field developing over a horizontal heated flat plate, in an open top cavity, is investigated experimentally. The physical phenomena dominating this interaction, besides their importance for theoretical thermo-fluids, influence a wide spectrum of applications including fuel injection in internal combustion engines and burners, electronics cooling, meteorology, fire extinguishing, deposition and coating processes etc. Water mist, generated in a nebulizer, is sprayed through a cylindrical orifice of internal diameter 4mm, vertically, towards the horizontal surface and at considerable distance from it (50cm). In order to establish a reference case data base, a significant part of the work refers to data collection and study on the thermal convection field characteristics, in the absence of the spray mist, as well as on the isothermal mist jet development. The interaction field has been investigated for mist jets of two Reynolds numbers and at two flat plate heating rates. The mist jet Reynolds numbers were rather low in order to enhance the influence of the plate and the flow structures generated due to buoyancy. Mean and turbulent characteristics of the spray (velocity and size) and the temperature distribution were monitored. A small thermocouple, significantly smaller than the Kolmogorov length scale, was used for temperature measurements. Droplet velocities and sizes were measured with Phase Doppler Anemometry, which also provided concentration and flux measurements. Moving plumes, often in the form of mushrooms, were identified as the dominant structures in the convection field. The form of temperature probability density functions was related to the past history of formation and heat exchange of air masses crossing the measuring point. An eigenfrequency, identified in the temperature power spectra indicates the presence of a large scale structure. The presence of the target plate decelerates the mist jets reducing also turbulent fluctuations close to the surface. Heating influences the mean and fluctuating velocities at considerable distance from the plate, reducing the rate of jet mass flux growth due to entrainment, more evidently for the low Re jet. Droplet sizes decrease downstream, presenting different trends in relation to Re. Increased values of the Sauter mean diameter (D32) are observed very close to the plate surface, particularly for the high Re number, isothermal jet.