<p>The design parameters axial gap and stator count of highpressure turbine stages are evaluated numerically towards theirinfluence on the unsteady aerodynamic excitation of rotorblades. Of particular interest is if and how unsteadyaerodynamic considerations in the design could reduce the riskofhigh cycle fatigue (HCF) failures of the turbine rotor.</p><p>A well-documented 2D/Q3D non-linear unsteady code (UNSFLO)is chosen to perform the stage flow analyses. The evaluatedresults are interpreted as aerodynamic excitation mechanisms onstream sheets neglecting 3D effects. Mesh studies andvalidations against measurements and 3D computations provideconfidence in the unsteady results. Three test cases areanalysed. First, a typical aero-engine high pressure turbinestage is studied at subsonic and transonic flow conditions,with four axial gaps (37% - 52% of cax,rotor) and two statorconfigurations (43 and 70 NGV). Operating conditions areaccording to the resonant conditions of the blades used inaccompanied experiments. Second, a subsonic high pressureturbine intended to drive the turbopump of a rocket engine isinvestigated. Four axial gap variations (10% - 29% ofcax,rotor) and three stator geometry variations are analysed toextend and generalise the findings made on the first study.Third, a transonic low pressure turbine rotor, known as theInternational Standard Configuration 11, has been modelled tocompute the unsteady flow due to blade vibration and comparedto available experimental data.</p><p>Excitation mechanisms due to shock, potential waves andwakes are described and related to the work found in the openliterature. The strength of shock excitation leads to increasedpressure excitation levels by a factor 2 to 3 compared tosubsonic cases. Potential excitations are of a typical wavetype in all cases, differences in the propagation direction ofthe waves and the wave reflection pattern in the rotor passagelead to modifications in the time and space resolved unsteadypressures on the blade surface. The significant influence ofoperating conditions, axial gap and stator size on the wavepropagation is discussed on chosen cases. The wake influence onthe rotorblade unsteady pressure is small in the presentevaluations, which is explicitly demonstrated on the turbopumpturbine by a parametric study of wake and potentialexcitations. A reduction in stator size (towards R≈1)reduces the potential excitation part so that wake andpotential excitation approach in their magnitude.</p><p>Potentials to reduce the risk of HCF excitation in transonicflow are the decrease of stator exit Mach number and themodification of temporal relations between shock and potentialexcitation events. A similar temporal tuning of wake excitationto shock excitation appears not efficient because of the smallwake excitation contribution. The increase of axial gap doesnot necessarily decrease the shock excitation strength neitherdoes the decrease of vane size because the shock excitation mayremain strong even behind a smaller stator. The evaluation ofthe aerodynamic excitation towards a HCF risk reduction shouldonly be done with regard to the excited mode shape, asdemonstrated with parametric studies of the mode shapeinfluence on excitability.</p><p><b>Keywords:</b>Aeroelasticity, Aerodynamics, Stator-RotorInteraction, Excitation Mechanism, Unsteady Flow Computation,Forced Response, High Cycle Fatigue, Turbomachinery,Gas-Turbine, High-Pressure Turbine, Turbopump, CFD, Design</p>

<p>Coatings are frequently applied on gas turbine components inorder to restrict surface degradation such as corrosion andoxidation of the structural material or to thermally insulatethe structural material against the hot environment, therebyincreasing the efficiency of the turbine. However, in order toobtain accurate lifetime expectancies and performance of thecoatings system it is necessary to have a reliableunderstanding of the mechanical properties and failuremechanisms of the coatings.</p><p>In this thesis, mechanical and fracture behaviour have beenstudied for a NiAl coating applied by a pack cementationprocess, an air-plasma sprayed NiCoCrAlY bondcoat, a vacuumplasma-sprayed NiCrAlY bondcoat and an air plasma-sprayed ZrO₂+ 6-8 % Y₂O₃topcoat. The mechanical tests were carried out ata temperature interval between room temperature and 860oC.Small punch tests and spherical indentation were the testmethods applied for this purpose, in which existing bending andindentation theory were adopted for interpretation of the testresults. Efforts were made to validate the test methods toensure their relevance for coating property measurements. Itwas found that the combination of these two methods givescapability to predict the temperature dependence of severalrelevant mechanical properties of gas turbine coatings, forexample the hardness, elastic modulus, yield strength, fracturestrength, flow stress-strain behaviour and ductility.Furthermore, the plasma-sprayed coatings were tested in bothas-coated and heat-treated condition, which revealedsignificant difference in properties. Microstructuralexamination of the bondcoats showed that oxidation with loss ofaluminium plays an important role in the coating degradationand for the property changes in the coatings.</p><p><b>Keywords:</b>small punch test, miniaturised disc bendingtests, spherical indentation, coatings, NiAl, APS-NiCoCrAlY,VPS-NiCrAlY, mechanical properties</p>

<p>Katalytisk förbränning är en lovande teknik för användning vid kraftgenerering, särskilt för</p><p>gasturbiner. Genom att använda katalytisk förbränning kan man nå mycket låga emissioner av kväveoxider</p><p>(NOX), kolmonoxid (CO) och oförbrända kolväten (UHC) samtidigt, vilket är svårt vid</p><p>konventionell förbränning. Förutom att man erhåller låga emissioner, kan katalytisk förbränning stabilisera</p><p>förbränningen och kan därmed användas för att uppnå stabil förbränning för gaser med låga</p><p>värmevärden. Denna avhandling behandlar huvudsakligen högtemperaturdelen av den katalytiska</p><p>förbränningskammaren. Kraven på denna del har visat sig svåra att nå. För att den katalytiska förbränningskammaren</p><p>ska kunna göras till ett alternativ till den konventionella, måste katalysatorer</p><p>med bättre stabilitet och aktivitet utvecklas.</p><p>Målet med denna avhandling har varit att utveckla katalysatorer med högre aktivitet och stabilitet,</p><p>lämpliga för högtemperaturdelen av en katalytisk förbränningskammare för förbränning av naturgas.</p><p>En mikroemulsionsbaserad framställningsmetod utvecklades för att undersöka om den kunde ge</p><p>katalysatorer med bättre stabilitet och aktivitet. Bärarmaterial som är kända för sin stabilitet, magnesia</p><p>och hexaaluminat, framställdes med den nya metoden. Mikroemulsionsmetoden användes också</p><p>för att impregnera de framställda materialen med de mer aktiva materialen perovskit (LaMnO3) och</p><p>ceriumdioxid (CeO2). Det visade sig att mikroemulsionsmetoden kan användas för att framställa katalysatorer</p><p>med bättre aktivitet jämfört med de konventionella framställningsmetoderna. Genom att</p><p>använda mikroemulsionen för att lägga på aktiva material på bäraren erhölls också en högre aktivitet</p><p>jämfört med konventionella beläggningsstekniker.</p><p>Eftersom katalysatorerna ska användas under lång tid i förbräningskammaren utfördes också en</p><p>åldringsstudie. Som jämförelse användes en av de mest stabila materialen som rapporterats i litteraturen:</p><p>LMHA (mangan-substituerad lantan-hexaaluminat). Resultaten visade att LMHA deaktiverade</p><p>mycket mer jämfört med flera av katalysatorerna innehållande ceriumdioxid på hexaaluminat som</p><p>framställts med den utvecklade mikroemulsionstekniken.</p> / <p>Catalytic combustion is a promising technology for power applications, especially gas turbines.</p><p>By using catalytic combustion ultra low emissions of nitrogen oxides (NO_X), carbon monoxide (CO)</p><p>and unburned hydrocarbons (UHC) can be reached simultaneously, which is very difficult with conventional</p><p>combustion technologies. Besides achieving low emission levels, catalytic combustion can</p><p>stabilize the combustion and thereby be used to obtain stable combustion with low heating-value</p><p>gases. This thesis is focused on the high temperature part of the catalytic combustor. The level of</p><p>performance demanded on this part has been proven hard to achieve. In order to make the catalytic</p><p>combustor an alternative to the conventional flame combustor, more stable catalysts with higher activity</p><p>have to be developed.</p><p>The objective of this work was to develop catalysts with higher activity and stability, suitable</p><p>for the high-temperature part of a catalytic combustor fueled by natural gas. A microemulsion-based</p><p>preparation method was developed for this purpose in an attempt to increase the stability and activity</p><p>of the catalysts. Supports known for their stability, magnesia and hexaaluminate, were prepared using</p><p>the new method. The microemulsion method was also used to impregnate the prepared material with</p><p>the more active materials perovskite (LaMnO₃) and ceria (CeO₂). It was shown that the microemulsion</p><p>method could be used to prepare catalysts with better activity compared to the conventional</p><p>methods. Furthermore, by using the microemulsion to apply active materials onto the support a</p><p>significantly higher activity was obtained than when using conventional impregnation techniques.</p><p>Since the catalysts will operate in the catalytic combustor for extended periods of time under</p><p>harsh conditions, an aging study was performed. One of the most stable catalysts reported in the</p><p>literature, LMHA (manganese-substituted lanthanum hexaaluminate), was included in the study for</p><p>comparison purposes. The results show that LMHA deactivated much more strongly compared to</p><p>several of the catalysts consisting of ceria supported on lanthanum hexaaluminate prepared by the</p><p>developed microemulsion method.</p>

Thermal barrier coatings (TBC’s) are used to provide both thermal insulation and oxidation protection to high temperature components within gas turbines. The development of turbines for power generation and aviation has led to designs where the operation conditions exceed the upper limits of most conventional engineering materials. As a result there has been a drive to improve thermal barrier coatings to allow the turbine to operate at higher temperatures for longer. The focus of this thesis has been to design thermal barrier coatings with lower conductivity and longer lifetime than those coatings used in industry today. The work has been divided between the development of new generation air plasma spray (APS) TBC coatings for industrial gas turbines and the development of suspension plasma spray (SPS) TBC systems. The route taken to achieve these goals with APS TBC’s has been twofold. Firstly an alternative stabiliser has been chosen for the zirconium oxide system in the form of dysprosia. Secondly, control of the powder morphology and spray parameters has been used to generate coating microstructures with favourable levels of porosity. In terms of development of SPS TBC systems, these coatings are relatively new with many of the critical coating parameters not yet known. The focus of the work has therefore been to characterise their lifetime and thermal properties when produced in a complete TBC system. Results demonstrate that dysprosia as an alternative stabiliser gives a reduction in thermal conductivity. While small at room temperature and in the as produced state; the influence becomes more pronounced at high temperatures and with longer thermal exposure time. The trade-off for this lowered thermal conductivity may be in the loss of high temperature stability. Overall, the greatest sustained influence on thermal conductivity has been from creating coatings with high levelsof porosity. In relation to lifetime, double the thermo-cyclic fatigue (TCF) life relative to the industrial standard was achieved using a coating with engineered porosity. Introducing a polymer to the spray powder helps to generate large globular pores within the coating together with a large number of delaminations. Such a structure was shown to be highly resistant to TCF testing. SPS TBC’s were shown to have much greater performance relative to their APS counterparts in thermal shock life, TCF life and thermal conductivity. Columnar SPS coatings are a prospective alternative for strain tolerant coatings in gas turbine engines.

In the United States, natural gas turbine generators account for approximately 7% of the total primary energy consumed. A one percent increase in gas turbine efficiency could result in savings of approximately 30 million dollars for operators and, subsequently, electricity end-users. The efficiency of a gas turbine engine is tied directly to the temperature at which the products of combustion enter the first stage, high-pressure turbine. The maximum operating temperature of the turbine components’ materials is the major limiting factor in increasing the turbine inlet temperature. In fact, current turbine inlet temperatures regularly exceed the melting temperature of the turbine vanes through advanced vane cooling techniques. These cooling techniques include vane surface film cooling, internal vane cooling, and the addition of a thermal barrier coating (TBC) to the exterior of the turbine vane. Typically, the performance of vane cooling techniques is evaluated using the adiabatic film effectiveness. However, the adiabatic film effectiveness, by definition, does not consider conjugate heat transfer effects. In order to evaluate the performance of internal vane cooling and a TBC it is necessary to consider conjugate heat transfer effects. The goal of this study was to provide insight into the conjugate heat transfer behavior of actual turbine vanes and various vane cooling techniques through experimental and analytical modeling in the pursuit of higher turbine inlet temperatures resulting in higher overall turbine efficiencies. The primary focus of this study was to experimentally characterize the combined effects of a TBC and film cooling. Vane model experiments were performed using a 10x scaled first stage inlet guide vane model that was designed using the Matched Biot Method to properly scale both the geometrical and thermal properties of an actual turbine vane. Two different TBC thicknesses were evaluated in this study. Along with the TBCs, six different film cooling configurations were evaluated which included pressure side round holes with a showerhead, round holes only, craters, a novel trench design called the modified trench, an ideal trench, and a realistic trench that takes manufacturing abilities into account. These film cooling geometries were created within the TBC layer. Each of the vane configurations was evaluated by monitoring a variety of temperatures, including the temperature of the exterior vane wall and the exterior surface of the TBC. This study found that the presence of a TBC decreased the sensitivity of the thermal barrier coating and vane wall interface temperature to changes in film coolant flow rates and changes in film cooling geometry. Therefore, research into improved film cooling geometries may not be valuable when a TBC is incorporated. This study also developed an analytical model which was used to predict the performance of the TBCs as a design tool. The analytical prediction model provided reasonable agreement with experimental data when using baseline data from an experiment with another TBC. However, the analytical prediction model performed poorly when predicting a TBC’s performance using baseline data collected from an experiment without a TBC. / text

This thesis proposes a method and develops a model for the participation of a combined cycle power plant to power system frequency control. Through the period of integration to the UCTE system, (Union for Coordination of Transmission of Electricity in Europe) frequency behavior of Turkey&rsquo / s grid and studies related to its improvement had been a great concern, so is the reason that main subject of my thesis became as &ldquo / Power System Frequency Control&rdquo / . Apart from system-wide global control action (secondary control) / load control loops at power plants, reserve power and its provision even at the minimum capacity generation stage, (primary control) are the fundamental concerns of this subject. The adjustment of proper amount of reserve at the power plants, and correct system response to any kind of disturbance, in the overall, are measured by the quality of the frequency behaviour of the system. A simulator that will simulate a dynamic gas turbine and its control system model, together with a combined cycle power plant load controller is the outcome of this thesis.

This thesis describes validated improvements in the modelling of micron-sized particle deposition within gas turbine engine secondary air systems. The initial aim of the research was to employ appropriate models of instantaneous turbulent flow behaviour to RANS CFD simulations, allowing the trajectory of solid particulates in the flow to be accurately predicted. Following critical assessment of turbophoretic models, the continuous random walk (CRW) model was chosen to predict instantaneous fluid fluctuating velocities. Particle flow, characterised by non-dimensional deposition velocity and particle relaxation time, was observed to match published experimental vertical pipe flow data. This was possible due to redefining the integration time step in terms of Kolmagorov and Lagrangian time scales, reducing the disparity between simulations and experimental data by an order of magnitude. As no high temperature validation data for the CRW model were available, an experimental rig was developed to conduct horizontal pipe flow experiments under engine realistic conditions. Both the experimental rig, and a new particulate concentration measurement technique, based on post test aqueous solution electrical conductivity, were qualified at ambient conditions. These new experimental data compare well to published data at non-dimensional particle relaxation times below 7. Above, a tail off in the deposition rate is observed, potentially caused by a bounce or shear removal mechanism at higher particle kinetic energy. At elevated temperatures and isothermal conditions, similar behaviour is observed to the ambient data. Under engine representative thermophoretic conditions, a negative gas to wall temperature gradient is seen to increase deposition by up to 4.8 times, the reverse decreasing deposition by a factor of up to 560 relative to the isothermal data. Numerical simulations using the CRW model under-predict isothermal deposition, though capturing relative thermophoretic effects well. By applying an anisotropic Lagrangian time scale, and cross trajectory effects of the external gravitational force, good agreement was observed, the first inclusion of the effect within the CRW model. A dynamic mesh morphing method was then developed, enabling the effect of large scale particle deposition to be included in simulations, without continual remeshing of the fluid domain. Simulation of an impingement jet array showed deposition of characteristic mounds up to 30% of the hole diameter in height. Simulation of a passage with film-cooling hole off-takes generated hole blockage of up to 40%. These cases confirmed that the use of the CRW generated deposition locations in line with scant available experimental data, but widespread airline fleet experience. Changing rates of deposition were observed with the evolution of the deposits in both cases, highlighting the importance of capturing changing passage geometry through dynamic mesh morphing. The level of deposition observed, was however, greater than expected in a real engine environment and identifies a need to further refine bounce-stick and erosion modelling to complement the improved prediction of impact location identified in this thesis.

Submitted by JOSÉ RAMON COPA REY null (jcoparey@gmail.com) on 2018-09-14T03:34:23Z No. of bitstreams: 1 Tesis José R. Copa Rey.pdf: 5579664 bytes, checksum: 29f9e65ff72c472b08614891d5361d0e (MD5) / Approved for entry into archive by Pamella Benevides Gonçalves null (pamella@feg.unesp.br) on 2018-09-14T12:35:08Z (GMT) No. of bitstreams: 1 coparey_jr_dr_guara.pdf: 5579664 bytes, checksum: 29f9e65ff72c472b08614891d5361d0e (MD5) / Made available in DSpace on 2018-09-14T12:35:08Z (GMT). No. of bitstreams: 1 coparey_jr_dr_guara.pdf: 5579664 bytes, checksum: 29f9e65ff72c472b08614891d5361d0e (MD5) Previous issue date: 2018-08-03 / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / O bagaço e a palha são resíduos do processamento industrial da cana-de-açúcar que constituem uma importante fonte de recurso para cogeração de energia no setor sucroalcooleiro. Os sistemas de cogeração neste setor geram potência mecânica ou elétrica e vapor, que são utilizados no próprio processo e o excedente é vendido as concessionárias de energia. Porém, estes sistemas encontram-se bem abaixo do potencial real. Uma alternativa tecnológica que poderá contribuir com a oferta de excedentes de energia elétrica é a introdução da tecnologia BIG-GT (gaseificadores de biomassa associados a turbina a gás e caldeira de recuperação). O presente trabalho, tem como objetivo o estudo termoeconômico da incorporação desta tecnologia em usinas sucroalcooleiras como alternativa para o aumento de geração de eletricidade. As análises energéticas e exergéticas foram realizadas para quatro possíveis configurações de uma usina sucroalcooleira com a integração da tecnologia BIG-GT com o objetivo de avaliar a eficiência de geração de eletricidade e vapor de processo, bem como o aproveitamento global de energia de cada uma delas. Na análise termoeconômica, é determinado o custo de produção de gás de gaseificação, eletricidade e vapor do processo no sistema proposto, assim como, tempo de recuperação do investimento. Na parte final do trabalho foi realizada a otimização multiobjetiva do sistema considerando três funções objetivo: tecnológica, econômica e ambiental, para identificar a configuração com melhor comportamento. De acordo com os resultados obtidos no estudo conclui-se que o caso III que estuda a gaseificação em leito fluidizado circulante pressurizado e mistura de oxigênio-vapor de gaseificação e o caso IV que além da gaseificação em leito fluidizado circulante pressurizado com mistura de oxigênio-vapor estuda a queima suplementar de palha na caldeira de recuperação, apresentam-se como as melhores das opções propostas. / Bagasse and straw are residues from the industrial processing of sugarcane that constitute an important source for cogeneration of energy in the sugar-alcohol sector. The cogeneration systems in this sector generate mechanical or electrical power and steam, which are used in the process itself and the surplus is sold to energy distribution companies. However, these systems are well below real potential. One of the technological alternatives that may improve the supply of surplus electricity is the introduction of BIG-GT technology (biomass gasifier associated with gas turbine and Heat recovery steam generator). In this work, it is proposed to conduct thermoeconomic studies of the incorporation of this technology in the sugarcane ethanol plants as an alternative to increasing the supply of electricity generation. The energetic and exergetic analyses were performed for four possible configurations of a sugarcane ethanol plant with the integration of BIG-GT technology with the objective of evaluating the efficiency of electricity generation and process steam as well as the global energy utilization of each one of them. In the thermoeconomic analysis, it is determined the cost of production of producer gas, electricity and steam of the process in the proposed system, as well as the investment payback period. In the final part of the work, it is developed the multiobjective optimization of the system considering three objective functions: technological, thermoeconomic and environmental, for identifying the configuration with better behavior. According to the results obtained in the study, it is concluded that case III and case IV are presented as the best of the proposed options. / 1450304

Le développement et la certification de systèmes propulsifs aéronautiques nécessitent une phase d'essais sur banc moteur. Ces essais permettent entre autres de caractériser les limites d'allumage des foyers de combustion de turbomachines, mais sont extrêmement coûteux et générateurs de délais pour l'industriel. Afin de limiter leur recours, il est nécessaire de développer des méthodes permettant de prévoir de la façon la plus fiable possible les performances d'allumage d'un prototype de chambre de combustion, et ce aussi bien pour des conditions de décollage au niveau de la mer que pour le cas critique de la haute altitude.L'objectif de cette thèse est de contribuer au développement et à la validation d’outils numériques pour la prévision de l'allumage des foyers de combustion à partir de données expérimentales obtenues sur le banc MERCATO de l’ONERA. Ces travaux ont été conduits en étroite coopération avec TURBOMECA. Des améliorations ont été apportées à un modèle permettant de simuler l'allumage d'un brouillard de carburant suite à un dépôt d'énergie par bougie à arc électrique. Ce modèle a été couplé à un code de calcul multiphysique (code CEDRE) afin d'établir des cartographies d'allumage à partir d'un champ aérodiphasique moyenné, mais également de simuler la phase de propagation de la flamme à l’ensemble du foyer par approche RANS pseudo-stationnaire. Afin de valider ces deux approches, une caractérisation expérimentale d'une maquette de chambre mono-secteur a été réalisée sur le banc d'essai MERCATO. Ces essais ont permis de constituer une banque de données très fournie pour différents cas tests. La comparaison de la cartographie d’allumage expérimentale à celle fournie par la simulation numérique donne des résultats très satisfaisants et encourageants en vue d’une application à un foyer réel de turbomachine. En parallèle, des résultats très prometteurs ont été obtenus sur une nouvelle maquette de chambre de combustion trisecteur,dérivée d'un foyer industriel, permettant de comparer ses limites d’allumage à celles obtenues sur la chambre réelle. Cette configuration fera l’objet par la suite d’une étude détaillée de la propagation de la flamme intersecteurs, impossible à réaliser sur la géométrie d'un foyer annulaire complet. / Design of aircraft engines requires tests on engine benches. These tests allow characterizing combustor ignition limits, but are extremely expensive and time consuming. In order to limit their number, it is necessary to develop alternative methods enabling to predict the ignition performances of a combustor prototype, for both ground conditions and high altitude conditions, the latter being particularly critical.The purpose of this thesis is to contribute to the development and validation of numerical tools enabling to predict ignition performances of combustor. Validation will be possible using an experimental data base obtained on the MERCATO test bench, at ONERA. This work results from a close cooperation with TURBOMECA. A numerical model, previously developed to predict the ignition of fuel spray following a spark discharge, has been improved. This model has been combined to a multiphysics CFD code (CEDRE) in orderto build ignition map from a mean two-phase flow field, and also to compute the flame propagation stage using RANS approach. In order to validate both methods, experimental characterization of a one-sectorcombustor has been performed on the MERCATO test rig. A complete data base for validation of CFD code isnow available. Comparison of experimental and numerical ignition mapping showed good agreements for the different tests cases, and seems encouraging for an application on an industrial combustor. In the same time,promising results have been obtained with a new experimental three-sector combustor. Its geometry is basedon an industrial combustor, allowing a comparison of ignition performances between the simplified and the industrial combustors

Dans les turbomachines conventionnelles, l’estimation des performances (rendement, puissance et rapport de pression) se fait en général en admettant l’adiabaticité de l’écoulement. Mais, de nombreuses études ayant montré l’influence négative des échanges thermiques internes et externes sur les performances des petites turbomachines dans les faibles charges et aux bas régimes, cette hypothèse ne peut plus être recevable. L’objectif principal de cette thèse est de contribuer à lever l’hypothèse d’adiabaticité.Une étude préalable de l’état de l’art a permis de relever les différents types de transferts thermiques dans les turbomachines et de circonscrire notre étude.Puis, une analyse exergétique généralisée, ayant pour but la prise en compte des deux principes de la thermodynamique, a été effectuée et l’évolution de l’indice de performance caractérisant le niveau d’énergie récupérable en fonction des échanges thermiques est étudiée.Les performances des turbomachines à fluide compressible sont généralement représentées sous forme graphique dans des systèmes de coordonnées adimensionnelles établies avec l’hypothèse d’adiabaticité. Ces cartographies couramment utilisées par les exploitants et constructeurs ne conviennent pas aux machines fonctionnant avec transferts thermiques. L’étude de la similitude des turbomachines thermiques à fluide compressible présentée dans ce travail, propose de nouvelles coordonnées adimensionnelles pouvant être utilisées aussi bien en adiabatique que dans les écoulements avec transferts thermiques.Enfin, nous proposons un protocole de mesures et un modèle numérique pour l’évaluation des transferts thermiques dans un turbocompresseur.Certains résultats obtenus montrent que les performances calculées avec l’hypothèse d’adiabaticité de l’écoulement du fluide sont surestimées. Les nouvelles lois de la similitude proposées généralisent le théorème de Rateau au fluide compressible fonctionnant dans n’importe quelle condition et permettent de calculer les échanges thermiques à chaud à partir des résultats d’essai à froid. Une donnée supplémentaire (température de refoulement) est néanmoins nécessaire pour la prédiction complète des performances et des échanges thermiques.Le modèle numérique de calcul des échanges thermiques proposé donne des résultats en accord avec ceux attendus, mais nécessite des données réelles issues de mesure sur banc pour une validation complète. / In the conventional turbomachines, calculations are done assuming adiabatic flow. But, the negative influence of external and internal heat exchange on the performance of small turbomachines at low loads and low speeds have been shown by many studies in the literature. Then, this assumption is no longer admissible. The main objective of this thesis is to help remove the assumption of adiabaticity.A study of the state of art has identified the different kinds of heat transfer and defined the limits of our investigations.Afterwards, a generalized exergy analysis whose main goal is to take into account the two principles of thermodynamics has been made and the variation of exergy performance versus heat transfer has been studied.The maps currently used are made with the assumption of adiabaticity. The laws of similarity in turbomachines working with compressible fluid studied propose new dimensionless coordinates that can be used in any operating condition (adiabatic or not).Finally, we present a measurement protocol and a numerical model for calculating heat transfer in a turbocharger.Some results from our work indicate that the performance of thermal turbomachinery announced regardless of thermal heat exchanges are found to be overestimated.The new laws of similarity proposed generalize the Rateau’s theorem to compressible fluid flow in any operating condition and can be used to calculate heat transfer from adiabatic test results. Supplementary information is still required for the complete prediction of performance and heat transfer.The numerical model for calculating heat transfer gives some results that are in agreement with those expected. But actual data from test bench are required for complete validation.