Au cours des deux dernières décennies, l'essai d'indentation à haute température a été développé progressivement afin de satisfaire aux exigences industrielles de plus en plus importantes. Pour garantir un bon niveau de précision des mesures, il faut résoudre les problèmes notamment associés à la température élevée tels que le choix du matériau de la pointe, la stabilité thermique du système, la conception du chauffage, etc. Cette thèse s'inscrit dans la problématique du développement de la méthodologie de l'essai d'indentation à haute température pour caractériser les matériaux métalliques. Une attention particulière a été accordée à la recherche des matériaux candidats pour la pointe et à la détermination des plages de forces et de pénétrations utilisées au bon fonctionnement d'un indenteur. Les analyses éléments finis nous aident d'étudier l'influence de défauts tels que la présence d'un revêtement mince et celle d'un défaut d'alignement entre l'axe d'indentation et la surface d'échantillon. Pour trouver un bon matériau de pointe, il est nécessaire de tester la stabilité géométrique et chimique de différents matériaux candidats pouvant remplacer le diamant à haute température. La collaboration avec la société suisse Anton Paar, qui se spécialise dans la fabrication des machines de mesure pour la caractérisation mécanique d'une grande variété de matériaux, permet de développer un nouvel équipement de micro- et nano-indentation à haute température. En utilisant le nouvel dispositif, nous avons pu réaliser des essais d'indentation pour caractériser des propriétés mécaniques de différents matériaux et vérifier la stabilité thermique de cet instrument. / Over the past two decades, the high-temperature indentation experiment has been developed gradually to meet increasingly high industrial demand. ln order to guarantee a good level of accuracy of the measurements, it is necessary to solve the problems associated with high temperature, such as the choice of the indenter material, the thermal stability of the system, heating design, etc. This thesis aims to develop the methodology of the high-temperature indentation experiment to characterize metallic materials. Particular attention has been given to the search for candidate materials for the tip and to the determination of the force and penetration ranges used for the correct operation of an indenter. The finite element analysis helps us to study the influence of defects such as the presence of a thin film and that of a misalignment between the indentation axis and the sample surface. To find a better indenter material, it is necessary to test the geometric and chemical stability of different candidate materials that can replace the diamond at elevated temperature. The collaboration with the Swiss company Anton Paar, which specializes in the manufacture of measuring machines for the mechanical characterization of a wide variety of materials, enables the development of new high-temperature micro- and nano­-indentation equipment. By using the new device, we were able to carry out the indentation tests to characterize the mechanical properties of different materials and to check the thermal stability of this new instrument.

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Convection set up in a fluid due to the presence of two components of differing diffusivities is known as double diffusive convection. Double diffusive convection is observed in nature, in oceans, in the formation of certain columnar rock structures and in stellar interiors. The major engineering applications of double diffusive convection are in the fields metallurgy and alloy solidification in casting processes. The two components may be any two substances which affect the density of the fluid, heat and salt being the pair found most commonly in nature. Depending upon the initial stratifications of the two components, double diffusive convection can be set up in either the diffusive mode or the finger mode. In this thesis, the linear stability of a double diffusive system prone to finger instability has been studied in the presence of temporally varying non-linear background profiles of temperature and salinity. The motivation for the present study is to bridge the gap between existing theories, which mainly concentrate on linear background profiles independent of time, on the one hand and experiments and numerical simulations, which have time dependent step-like non-linear background profiles, on the other. The general stability characteristics of a double diffusive system with step-like background profiles have been studied using the standard normal mode method. The background temperature and salinity profiles are assumed to follow the hyperbolic tangent function, since it has a step-like character. The sharpness of the step can be altered by changing a suitable parameter in the hyperbolic tangent function. It is found that changing the degree of non-linearity of the background profile of one of the components keeping the background profile of the other component linear affects the growth rate, Wave number and the form of the disturbances. In general, increasing the degree of nonlinearity of background salinity profile makes the system more unstable and results in a reduction in the vertical extent of the disturbances. On the other hand, increasing the degree of non-linearity of the background temperature profile with the salinity profile kept linear results in a reduction in the growth rate and increase in the wave number. The form of the disturbance may change due to enhanced modal competition between the gravest odd and even modes in this case. The method of normal modes inherently assumes that the background profiles of temperature and salinity are independent of time and hence, it cannot be used for studying the stability of systems with time varying background profiles. A pseudo-similarity method has been used to handle such background profiles. Initial steps of temperature and salinity diffuse according to the error function form, and hence, the case of error function background profiles has been studied in detail. Taking into account the time-dependence of background profiles has been shown to significantly change the wave number and the incipient flux ratio. The dependence of the critical wave number (kc) on the thermal Rayleigh number (RaT ) can be determined analytically and is found to change from kc ~ Ra T1/4 for linear background profiles to kc ~ Ra T1/3 for error function profiles. The region of instability in the Rp (density stability ratio) space is found to increase from 1 ≤ R ρ ≤ r−1 for linear background profiles to 1 ≤ Rρ < r−3/2 for error function background profiles, where T denotes the ratio of the diffusivity of the slower diffusing component to that of the faster diffusing one. A parametric study covering a wide range of parameter values has been carried out to determine the effect of the parameters density stability ratio (Rp), diffusivity ratio (ρ ) and Prandtl number (Pr) on the onset time, critical wavenumber and the incipient flux ratio. The wide range of governing parameters covered here is beyond the scope of experimental and numerical studies. Such a wide range can be covered by theoretical approaches alone. It has been shown that the time of onset of convection determines the thicknesses of the temperature and salinity boundary layers, which in turn determine the width of salt fingers. Finally, the theoretical predictions of salt finger widths have been shown to be in agreement with the results of two dimensional numerical simulations of thermohaline system.

Producer gas derived from biomass is one of the most environment friendly substitutes to the fossil fuels. Usage of producer gas for power generation has effect of zero net addition of CO2 in atmosphere. The engines working on producer gas have potential to decrease the dependence on conventional fuels for power generation. However, the combustion process is governed by complex interactions between chemistry and fluid dynamics, some of which are not completely understood. Improved knowledge of combustion is, therefore, of vital importance for both direct use in the design of engines, and for the evolution of reliable simulation tools for engine development. The present work is related to the turbulent combustion of producer gas in closed vessels and engine cylinders. The main objective of the work was multi-dimensional simulation of turbulent combustion in the bowl-in-piston engine operating on producer gas fuel and to observe the flame and flow field interaction. First, the combustion model was validated in constant volume combustion chamber with experimental results. Experimental turbulent combustion data of producer gas (composition matching with engine operating conditions) was presented. The required data of laminar burning velocity of producer gas was computed and used in the simulation of turbulent combustion in closed vessel. The effect of squish and reverse squish flow on flame propagation in the bowl-in-piston engine cylinder was described. Laminar burning velocity of unstretched flame was computed using flame code which was developed earlier in this laboratory. One dimensional computations of unstretched planar flame were made to calculate laminar burning velocity of the producer gas-air mixture at pressures (1-10 bar) and temperatures (300-600 K). A correlation of laminar burning velocity of producer gas as a function of pressure and temperature was fitted and compared with experiments. A fixed composition and equivalence ratio of producer gas-air mixture, typical of the engine operating conditions, was considered. The correlation was used in simulation of turbulent combustion in closed vessel. The turbulent combustion experiments with producer gas-air mixture were conducted in a closed vessel. The aim of experiments was to generate pressure-time data, in closed vessel during turbulent flame propagation, which was required to validate turbulent combustion models. Determination of (ST /SL) was made from pressure-time data which requires corresponding laminar combustion data with same initial conditions. For this purpose a set of laminar combustion experiments was conducted. Experimental setup consists of a constant volume combustion chamber of cubical shape and size 80 x 80 x 80 mm3 . The initial mixtures pressure and temperature were 1 bar and 300 K respectively. A fixed composition and equivalence ratio of producer gas-air mixture, typical of the engine operating conditions, was used. The composition of producer gas was H2 -19.61%, CO2 -19.68%, CH4 -2.52%, CO2 -12.55% and N2 -45.64% on volume basis. Fuel-air mixture was ignited with electric spark at the center of the cube. Initial turbulence in the chamber was created by moving a perforated plate with specified velocity. Perforated plate was placed in chamber so that the central hole in the plate passes over the spark electrodes as it sweeps across the chamber. Two geometrically similar plates with hole diameter of 5 and 10 mm were used. The new experimental setup constructed as a part of this work was first tested with one set of experiments each with methane and propane data of SL and ST /SL from the literature. Maximum turbulent intensity (u’) achieved was 1.092 ms−1 . The ratios of turbulent to laminar burning velocity (ST /SL) values were determined at six different turbulence intensity levels. Laminar combustion experiments were extended to elevated initial pressures 2-5 bar and temperature 300 K. The value of SL was calculated from the pressure-time history recorded during laminar stretching flame propagation inside closed vessel. These SL values were compared with computed SL,∞ after accounting for stretch. Turbulent combustion simulations were carried out to validate combustion models suitable for multi-dimensional CFD simulation of combustion in constant volume closed chamber. Two models proposed by Choi and Huh, based on Flame Surface Density (FSD) were tested with the present experimental results. User FORTRAN code for the source terms in transport equation of FSD was implemented in ANSYS-CFX 10.0 software. First model called CFM1, grossly under-predicted the rate of combustion. The second model called CFM2, predicted the results satisfactorily after replacing the arbitrary length scale with turbulent integral length scale (lt) having a limiting value near the wall. The modified CFM2 model was able to predict the propagation phase of the developed flame satisfactorily, though the duration for initial flame development was over-predicted by the model. CFD simulation of producer gas engine combustion process was carried out using ANSYSCFX software. Mesh deformation option was used to take care of moving boundaries such as piston and valve surfaces. The fluid domain expands during suction process and contracts during compression process. In order to avoid excessive distortion of the mesh elements, a series of meshes at different crank angle positions were generated and checked for their quality during mesh motion in the solver. For suction process simulation, unstructured meshes having 0.1 to 0.3 million cells were used. During the compression and combustion process simulations, structured meshes having 40,000 to 0.1 million cells were used. k-ε model was used for turbulence simulation. The suction, compression and combustion processes of an SI engine were simulated. Initial flame kernel was given by providing high flame surface density in a small volume comparable to the spark size at the time of ignition. The flame surface density model, CFM-2, was adapted with the modification of length scale tested against constant volume experiments. A suitable limiting value was used to avoid abnormal flame propagation near the wall. The limiting value of integral length scale (lt) near the wall was determined by linear extrapolation of the integral length scale in the domain to the wall. Engine p - θ curves of three different ignition timings 26°, 12° and 6°before top dead center (TDC) were simulated and compared with earlier experimental results. The effects of flow field on flame propagation have been observed. A comparison of the simulated and experimental p - θ diagram of the engine for all above cases gave mixed results. For the ignition timing at 26° before TDC case, predicted peak pressure value was 17% higher and at 3° earlier than those of the experimental peak. For the other two cases, the predicted peak pressure value was 28% lower and 5° later than those of the experimental peak. The reason for under-prediction of the pressure values could be due to the delay in development of initial flame kernel. Simulated pressure curves have offset about 3-4° compared to the experimental pressure curves. It was observed that in all predicted p - θ cases, there was a delay in the initial flame development. It is evident from the under-prediction of pressure values, especially in the initial flame kernel development phase and it also affects the p - θ curve at later stage. The delay was about 3-4° of crank angle rotation in various cases. The delay in predicting the initial flame development needs to be corrected in order to predict the combustion process properly. The proposed FSD model seems to have capability to predict p - θ values fairly in the propagation phase of developed flame. Reasonably good match was obtained by advancing the ignition timing in the computation by about 3-4° compared to the experimental setting. In the bowl-in-piston engine cylinders, the flow in the cylinder is characterised by squish and reverse squish when the piston is moving towards and away from the top dead center (TDC) respectively. The effect of squish and reverse squish flow on flame propagation has been assessed. For the more advanced ignition case, i.e., 26° before TDC, The flame propagation did not have favorable effect by the flow field. The direction of flame propagation was against the squish and reverse squish flow. This resulted in suppressed peak velocities in the cylinder compared the motoring process. Hence the burning rate was not augmented by the turbulence inside the cylinder. For the ignition 12° before TDC case, the flame propagation did have favorable effect by the flow field. During the reverse squish period, the flame had reached the bowl wall. At this stage, the flame was pushing the reactants out and this augments the reverse-squish flow, and hence the maximum reverse-squish velocity was increased to 2.03 times the peak reverse-squish velocity of motoring case. The reverse-squish flow was distorting the flame from spherical shape and the flame gets stretched. Flame surface enters the cylindrical region faster compared to the previous case. The stretched flame in the reverse-squish flow may be considered as reverse squish flame, as was proposed earlier by Sridhar G. The burn rate during the reverse squish period may be 2 to 2.5 times the normal burn rate. For the ignition 6° before TDC case, the flame was very small in size and it did not affect the flow in squish period. During the reverse squish period, the flame radius was moderate compared to the bowl radius. The flame was pushing the reactants out and it increased the maximum reverse-squish velocity to 1.3 times by the flame. In this case, the reverse-squish flow moderately affecting the flame shapes. The results of this study could give an idea of what ignition timing must be kept for favorable use of flow field inside the engine cylinder. Main contributions from the present work are: Multi-dimensional simulation of combustion process inside the engine cylinder operating on producer gas was carried out to examine flame/flow field interactions. Two models based on FSD were first tested against present experimental results in constant volume combustion chamber. In CFM2 model; a modification of replacing the arbitrary length scale by integral length scale with a limiting value near the wall was suggested to avoid prediction of abnormally large turbulent burning velocity near the wall. This combustion model has been implemented in ANSYS-CFX10. The required data of laminar and turbulent burning velocities of producer gas-air mixture has been determined by experiments and computations at varied initial pressures and turbulent intensities. Finally, the simulated engine pressure data has been compared with earlier experimental data of the engine operating on producer gas. The proposed FSD model has the capability to match well with the experimental results except for the initial flame kernel development phase. Even though this issue needs to be resolved, the work has brought out the important interaction between the flame propagation and flow field within the bowl-in-piston engine cylinder.

For flights beyond Mach 6 ramjets are inefficient engines due to huge total pressure loss in the normal shock systems, combustion conditions that lose a large fraction of the available chemical energy due to dissociation and high structural loads. However if the flow remains supersonic inside the combustion chamber, the above problems could be alleviated and here the concept of SCRAMJET(supersonic combustion ramjet) comes into existence. The scramjets could reduce launching cost of satellites by carrying only fuel and ingesting oxygen from atmospheric air. Further applications could involve defense and transcontinental hypersonic transport. In the current study an effort is made to achieve supersonic combustion in a ground based short duration test facility(combustion driven shock-tunnel), which in addition to flight Mach number can simulate flight Reynolds number as well. In this study a simple method of injection i.e. wall injection of the fuel into the combustion chamber is used. The work starts with threedimensional numerical simulation of a non-reacting gas(air) injection into a hypersonic cross-flow of air to determine the conditions in which air penetrates reasonably well into the cross-flow. Care is taken so that the process does not induce huge pressure loss due to the bow shock which appears in front of the jet column. The code is developed in-house and parallelized using OpenMp model. This is followed by experiments on air injection into a hypersonic cross-flow of air in a conventional shock-tunnel HST2 existing in IISc. The most tricky part is synchronization of injection with start of test-flow in such a short duration(test time 1 millisecond) facility. Next part focuses on numerical simulations to determine the free-stream conditions, mainly the temperature and pressure of air, so that combustion takes place when hydrogen is injected into a supersonic cross-flow of air. The simulations are two-dimensional and includes species conservation equations and source terms due to chemical reactions in addition to the Navier-Stokes equations. This code is also built in-house and parallelized because of more number of operations with the inclusion of species conservation equations and chemical non-equilibrium. However, the predicted conditions were not achievable by HST2 due to low stagnation conditions of HST2. Therefore, a new shock-tunnel which could produce the required conditions is built. The new tunnel is a combustion driven shock-tunnel in which the driver gas is at higher temperature than conventional shock-tunnel. The driver gas is basically a mixture of hydrogen, oxygen and helium at a mole ratio of 2:1:10 initially. The mixture is ignited by spark plugs and the hydrogen and oxygen reacts releasing heat. The heat released raises the temperature of the mixture which is now predominantly helium and small fractions of water vapour and some radicals. The composition of the driver gas and initial pressure are determined through numerical simulations. Experiments follow in the new tunnel on hydrogen injection into a region of supersonic cross-flow between two parallel plates with a wedge attached to the bottom plate. The wedge reduces the hypersonic free-stream to Mach 2. A high-speed camera monitors the flow domain around injection point and sharp rise in luminosity is observed. To ascertain whether the luminosity is due to combustion or not, two more driven gases namely nitrogen and oxygen-rich air are used and the luminosity is compared. In the first case, the free-stream contains no oxygen and luminosity is not observed whereas in the second case higher luminosity than air driver case is visible. Additionally heat-transfer rates are measured at the downstream end of the model and at a height midway between the plates. Similar trend is observed in the relative heat-transfer rates. Wall static pressure at a location downstream of injection port is also measured and compared with numerical simulations. Results of numerical simulations which are carried out at the same conditions as of experiments confirm combustion at supersonic speed. Experiments and numerical simulations show presence of supersonic combustion in the setup. However, further study is necessary to optimize the parameters so that thrust force could be generated efficiently.

Multilevel inverters have advantages over two-level inverters such as reduced THD, ability to operate at low switching frequencies, reduced switching losses etc. Moreover, higher voltage levels can be handled with devices of lower voltage rating. The main disadvantage with the multilevel configurations compared to the two-level inverter configuration is the increase in the number of power devices required and the circuit complexity, which necessitates complex control schemes that add to the cost. Also, the reliability of the converters comes down as the number of devices increases. Reduction in complexity and modularity are desirable characteristics for the multilevel inverters. Open-end winding Induction Motor (IM) drive configurations are shown to have advantages over the motor drive schemes with isolated neutral. The DC-link requirement in case of open-end winding structures comes down to half the voltage rating of the conventional NPC inverters. The DC- link requirement in case of open-end winding structures comes down to half compared to that of the conventional NPC inverters. The number of switching states is higher in the case of open-end winding configuration compared to multiplicity of switching states of conventional NPC inverters, which gives a control flexibility that can be used for optimizing the hardware requirements. Taking advantage of the flexibility given by open-end winding configuration, this thesis proposes schemes which have reduced power circuit complexity. Non-sinusoidal voltage fed IM drives suffer from the problems related to the common mode voltage (CMV) generated by the inverters. This CMV causes bearing currents and shaft voltages which in turn cause increased conducted EMI, ground loop currents and premature bearing failure. A three-level scheme was proposed for an open-end winding Induction machine in the literature, which completely eliminate the CMV variation from the pole voltages as well as the phase voltages. This configuration uses 24 controlled switches and two isolated DC-sources. In this thesis, three-level inverter schemes with CMV elimination and reduced power device count for an open-end winding IM drive are proposed. The first scheme gets the reduction in switch count by sharing the top inverter of the three-level scheme and the second scheme achieves the same by sharing the bottom inverter. This way, the number of controlled switches comes down to 18 from 24. Another problem with multilevel inverters is the large number of isolated DC-sources required to achieve the multilevel inversion. Reducing the number of isolated supplies and using capacitors to split the voltage levels poses the problem of capacitor voltage balancing. A four-level inverter with both CMV elimination and capacitor voltage balancing for an open-end winding IM drive is proposed in this thesis. The motor is fed by two four-level inverters from both the sides. A closed loop capacitor voltage balancing scheme is implemented and the redundancies in the switching states are used for achieving the capacitor voltage balancing and thereby reducing the total number of DC-link to two. The control scheme is independent of the load power factor and maintains the balance in the entire modulation range. A five-level inverter scheme is proposed for an open-end winding IM drive in this thesis. It requires only two isolated DC-sources to achieve the five-level inversion. The motor is fed by one NPC three-level inverter from one side and a two-level inverter from the other. The inverters on either side share the DC-sources. Common mode voltage in the phases are made zero in an average sense using sine-triangle modulation in the proposed scheme so that the common mode currents through the phases are suppressed. The maximum fundamental voltage that can be obtained at the phase is limited to 0.5Vdc. DC-link requirement of the inverter scheme is half of that of conventional five-level inverter scheme because of the open-end winding structure. The two-level inverter, which should withstand half the DC-link voltage, is always in square wave operation and hence the switching losses are very less. All the schemes are simulated extensively in MATLAB/Simulink and experimentally verified on laboratory prototypes under V/f control. TI Motor control DSP and Xilinx CPLD/FPGA are used for generation of the PWM signals for the schemes. The inverters are switched at around 1.25 kHz to keep the switching losses low. Due to laboratory constraints, the experimental verification is done on low power prototypes. Nonetheless, the generality of the schemes allow them to be used for medium voltage high power applications.

The complex turbulent flow regimes encountered in many thermal-fluid engineering applications have proven resistant to the effective application of systematic design because of the computational expense of model evaluation and the inherent variability of turbulent systems. In this thesis the integration of the Proper Orthogonal Decomposition (POD) for reduced order modeling of turbulent convection with the application of robust design principles is proposed as a practical design approach. The POD has been used successfully to create low dimensional steady state flow models within a prescribed range of parameters. The underlying foundation of robust design is to determine superior solutions to design problems by minimizing the effects of variation on system performance, without eliminating their causes. The integration of these constructs utilizing the compromise Decision Support Problem (DSP) results in an efficient, effective robust design approach for complex turbulent convective systems. The efficacy of the approach is illustrated through application to the configuration of data center server cabinets. Data centers are computing infrastructures that house large quantities of data processing equipment. The data processing equipment is stored in 2 m high enclosures known as cabinets. The demand for increased computational performance has led to very high power density cabinet design, with a single cabinet dissipating up to 20 kW. The computer servers are cooled by turbulent convection and have unsteady heat generation and cooling air flows, yielding substantial inherent variability, yet require some of the most stringent operational requirements of any engineering system. Through variation of the power load distribution and flow parameters, such as the rate of cooling air supplied, thermally efficient configurations that are insensitive to variations in operating conditions are determined. This robust design approach is applied to three common data center server cabinet designs, in increasing levels of modeling detail and complexity. Results of the application of this approach to the example problems studied show that the resulting thermally efficient configurations are capable of dissipating up to a 50% greater heat load and 15% decrease in the temperature variability using the same cooling infrastructure. These results are validated rigorously, including comparison of detailed CFD simulations with experimentally gathered temperature data of a mock server cabinet. Finally, with the approach validated, augmentations to the approach are considered for multi-scale design, extending approaches domain of applicability.

Future generation of all-electric ships will be highly dependent on electric power, since every single system aboard such as the drive propulsion, the weapon system, the communication and navigation systems will be electrically powered. Power conversion modules (PCM) will be used to transform and distribute the power as desired in various zone within the ships. As power densities increase at both components and systems-levels, high-fidelity thermal models of those PCMs are indispensable to reach high performance and energy efficient designs. Efficient systems-level thermal management requires modeling and analysis of complex turbulent fluid flow and heat transfer processes across several decades of length scales. In this thesis, a methodology for thermal modeling of complex PCM cabinets used in naval applications is offered. High fidelity computational fluid dynamics and heat transfer (CFD/HT) models are created in order to analyze the heat dissipation from the chip to the multi-cabinet level and optimize turbulent convection cooling inside the cabinet enclosure. Conventional CFD/HT modeling techniques for such complex and multi-scale systems are severely limited as a design or optimization tool. The large size of such models and the complex physics involved result in extremely slow processing time. A multi-scale approach has been developed to predict accurately the overall airflow conditions at the cabinet level as well as the airflow around components which dictates the chip temperature in details. Various models of different length scales are linked together by matching the boundary conditions. The advantage is that it allows high fidelity models at each length scale and more detailed simulations are obtained than what could have been accomplished with a single model methodology. It was found that the power cabinets under the prescribed design parameters, experience operating point airflow rates that are much lower than the design requirements. The flow is unevenly distributed through the various bays. Approximately 90 % of the cold plenum inlet flow rate goes exclusively through Bay 1 and Bay 2. Re-circulation and reverse flow are observed in regions experiencing a lack of flow motion. As a result high temperature of the air flow and consequently high component temperatures are also experienced in the upper bays of the cabinet. A proper orthogonal decomposition (POD) methodology has been performed to develop reduced-order compact models of the PCM cabinets. The reduced-order modeling approach based on POD reduces the numerical models containing 35 x 109 DOF down to less than 20 DOF, while still retaining a great accuracy. The reduced-order models developed yields prediction of the full-field 3-D cabinet within 30 seconds as opposed to the CFD/HT simulations that take more than 3 hours using a high power computer cluster. The reduced-order modeling methodology developed could be a useful tool to quickly and accurately characterize the thermal behavior of any electronics system and provides a good basis for thermal design and optimization purposes.

The work reported in this thesis is an attempt to enhance heat transfer in electronic devices with the use of impinging air jets on pin-finned heat sinks. The cooling per-formance of electronic devices has attracted increased attention owing to the demand of compact size, higher power densities and demands on system performance and re-liability. Although the technology of cooling has greatly advanced, the main cause of malfunction of the electronic devices remains overheating. The problem arises due to restriction of space and also due to high heat dissipation rates, which have increased from a fraction of a W/cm2to 100s of W /cm2. Although several researchers have at-tempted to address this at the design stage, unfortunately the speed of invention of cooling mechanism has not kept pace with the ever-increasing requirement of heat re- moval from electronic chips. As a result, efficient cooling of electronic chip remains a challenge in thermal engineering. Heat transfer can be enhanced by several ways like air cooling, liquid cooling, phase change cooling etc. However, in certain applications due to limitations on cost and weight, eg. air borne application, air cooling is imperative. The heat transfer can be increased by two ways. First, increasing the heat transfer coefficient (forced convec- tion), and second, increasing the surface area of heat transfer (finned heat sinks). From previous literature it was established that for a given volumetric air flow rate, jet im-pingement is the best option for enhancing heat transfer coefficient and for a given volume of heat sink material pin-finned heat sinks are the best option because of their high surface area to volume ratio. There are certain applications where very high jet velocities cannot be used because of limitations of noise and presence of delicate components. This process can further be improved by pulsating the jet. A steady jet often stabilizes the boundary layer on the surface to be cooled. Enhancement in the convective heat transfer can be achieved if the boundary layer is broken. Disruptions in the boundary layer can be caused by pulsating the impinging jet, i.e., making the jet unsteady. Besides, the pulsations lead to chaotic mixing, i.e., the fluid particles no more follow well defined streamlines but move unpredictably through the stagnation region. Thus the flow mimics turbulence at low Reynolds number. The pulsation should be done in such a way that the boundary layer can be disturbed periodically and yet adequate coolant is made available. So, that there is not much variation in temperature during one pulse cycle. From previous literature it was found that square waveform is most effective in enhancing heat transfer. In the present study the combined effect of pin-finned heat sink and impinging slot jet, both steady and unsteady, has been investigated for both laminar and turbulent flows. The effect of fin height and height of impingement has been studied. The jets have been pulsated in square waveform to study the effect of frequency and duty cycle. This thesis attempts to increase our understanding of the slot jet impingement on pin-finned heat sinks through numerical investigations. A systematic study is carried out using the finite-volume code FLUENT (Version 6.2) to solve the thermal and flow fields. The standard k-ε model for turbulence equations and two layer zonal model in wall function are used in the problem Pressure-velocity coupling is handled using the SIMPLE algorithm with a staggered grid. The parameters that affect the heat transfer coefficient are: height of the fins, total height of impingement, jet exit Reynolds number, frequency of the jet and duty cycle (percentage time the jet is flowing during one complete cycle of the pulse). From the studies carried out it was found that: a) beyond a certain height of the fin the rate of enhancement of heat transfer becomes very low with further increase in height, b) the heat transfer enhancement is much more sensitive to any changes at low Reynolds number than compared to high Reynolds number, c) for a given total height of impingement the use of fins and pulsated jet, increases the effective heat transfer coefficient by almost 200% for the same average Reynolds number, d) for all the cases it was observed that the optimum frequency of impingement is around 50 − 100 Hz and optimum duty cycle around 25-33.33%, e) in the case of turbulent jets the enhancement in heat transfer due to pulsations is very less compared to the enhancement in case of laminar jets.