The objective of this work is to examine the flow structure and heat transfer distribution of a squealer tip rotor blade with purge flow cooling and provide a comparison with a basic flat tip rotor blade without purge flow cooling, under transonic conditions and high inlet free stream turbulence intensity. The blade design was provided by Solar Turbines Inc., and consists of a double squealer around the pressure and suction sides, two purge flow blowing holes located downstream of the leading edge and mid-chord, four ribs in the mid-chord region and a trailing edge bleeder exiting on the pressure side. Blade cavity depth is 2.29 mm (0.09 in.) and the total blade turning angle is 107.5°. Tests were performed in a blow-down facility at a turbulence intensity of 12%, in a seven bladed 2-D linear cascade at transonic conditions. Experiments were conducted at isentropic exit Mach numbers of 0.85 and 1.05, corresponding to Reynolds numbers based on axial chord of 9.75x10^5 and 1.15x10^6, respectively, and tip clearance gaps of 1% and 2% of the scaled engine blade span. A blowing ratio of 1.0 was used in the squealer tip experiments. Detailed heat transfer coefficient and film cooling effectiveness distributions were obtained using an infrared thermography technique, while oil flow visualization was used to investigate the flow patterns in the blade tip region. With the addition of a squealer tip, leakage flow was found to decrease, as compared to a flat tip blade. With increasing tip clearance gap, the heat transfer coefficients within the cavity and along the squealer rim were found to decrease and increase, respectively. Film cooling effectiveness decreased with increasing tip clearance gap and was mainly observed within the squealer cavity. The maximum heat transfer coefficient was observed on the leading edge, however, comparatively large values were observed on the mid-chord ribs. The presence of the ribs, greatly affected the flow structure and heat transfer distributions within the cavity and downstream towards the trailing edge. / Master of Science

This thesis contributes an in-depth comparative study of u-tube and coaxial borehole heat exchangers. While it is widely accepted that the lower resistance of the coaxial heat exchanger should result in a performance advantage, the findings of several studies comparing the heat exchanger configurations did not definitively establish the mechanisms causing differences in performance. This study employs numerical modelling to consider heat exchangers over a broad range of time scales and under carefully controlled geometry and flow conditions, resulting in the identification of the key parameters influencing borehole heat exchanger performance. The first part of this study consists of a comparison of u-tube and coaxial heat exchangers under continuous loading. A detailed conjugate heat transfer numerical model was developed in OpenFOAM, designed to capture both short and long time scales of heat exchange, necessary to understand the nuanced differences between designs. A novel transient resistance analysis was employed to understand the dominant factors influencing performance. This study established that marginal differences exist between u-tube and coaxial borehole heat exchangers (BHEs) when operated continuously long term but that greater differences occur early in operation. The second phase of this investigation provided a framework for analysing borehole heat exchanger performance during intermittent operation, while also comparing u-tube and coaxial designs. During this study, it was found that reducing operating time, improving the the rate of the ground's recovery to its original temperature, and lowering the duty cycle improved BHE performance. Transit time was identified as a influential time scale, below which heating at the outlet was limited. Further, the benefits of operating below the transit time were mitigated by design-specific interaction between inlet and outlet flows. Finally, this study found that non-dimensionalizing operating time by transit time causes the differences between u-tube and coaxial performance to vanish, leading to the conclusion that differences in BHE performance are caused by variations in flow rather than thermal mass. / Thesis / Doctor of Philosophy (PhD) / This thesis provides an in-depth comparative study of two different designs of borehole heat exchanger, the u-tube and coaxial, which are used in geothermal applications to transfer heat to and from the ground. While many researchers anticipated that the coaxial design would perform better, several studies comparing the heat exchangers were not able to provide a clear answer about which heat exchanger performed best. This study addressed this gap by using detailed numerical simulations which showed that there was a marginal difference in performance between the two heat exchangers when operated for periods longer than a few hours, but that larger differences occurred early in operation (under 15 minutes). The results also showed that operating intermittently resulted in improvements in performance of the heat exchanger, particularly when operated for periods less than the time it takes fluid to travel the length of the piping.

Yes / In polymer melt processing, the heat transfer coefficient (HTC) determines the heat flux across the interface of the polymer melt and the mould wall. The HTC is a dominant parameter in cooling simulations especially for microinjection moulding, where the high surface to volume ratio of the part results in very rapid cooling. Moreover, the cooling rate can have a significant influence on internal structure, morphology and resulting physical properties. HTC values are therefore important and yet are not well quantified. To measure HTC in micromoulding, we have developed an experimental setup consisting of a special mould, and an ultra-high speed thermal camera in combination with a range of windows. The windows were laser machined on their inside surfaces to produce a range of surface topographies. Cooling curves were obtained for two materials at different processing conditions, the processing variables explored being melt and mould temperature, injection speed, packing pressure and surface topography. The finite element package Moldflow was used to simulate the experiments and to find the HTC values that best fitted the cooling curves, so that HTC is known as a function of the process variables explored. These results are presented and statistically analysed. An increase in HTC from the standard value of 2500 W/m2C to values in the region 7700 W/m2C was required to accurately model the observations. / EPSRC

The study of flow fields and heat transfer characteristics inside a gas turbine combustor provides one of the most serious challenges for gas turbine researchers because of the harsh environment at high temperatures. Design improvements of gas turbine combustors for higher efficiency, reduced pollutant emissions, safety and durability require better understanding of combustion in swirl flows and thermal energy transfer from the turbulent reacting flows to solid surfaces. Therefore, accurate measurement and prediction of the flows and heat loads are indispensable. This dissertation presents flow details and wall heat flux measurements for reacting flow conditions in a model gas turbine combustor. The objective is to experimentally investigate the effects of combustor operating conditions on the reacting swirl flows and heat transfer on the liner wall. The results shows the behavior of swirling flows inside a combustor generated by an industrial lean pre-mixed, axial swirl fuel nozzle and associated heat loads. Planar particle image velocimetry (PIV) data were analyzed to understand the characteristics of the flow field. Experiments were conducted with various air flow rates, equivalence ratios, pilot fuel split ratios, and inlet air temperatures. Methane and propane were used as fuel. Characterizing the impingement location on the liner, and the turbulent kinetic energy (TKE) distribution were a main part of the investigation. Proper orthogonal decomposition (POD) further analyzed the data to compare coherent structures in the reacting and non-reacting flows. Comparison between reacting and non-reacting flows yielded very striking differences. Self-similarity of the flow were observed at different operating conditions. Flow temperature measurements with a thermocouple scanning probe setup revealed the temperature distribution and flow structure. Features of premixed swirl flame were observed in the measurement. Non-uniformity of flow temperature near liner wall was observed ranging from 1000 K to 1400 K. The results provide insights on the driving mechanism of convection heat transfer. As a novel non-intrusive measurement technique for reacting flows, flame infrared radiation was measured with a thermographic camera. Features of the flame and swirl flow were observed from reconstructed map of measured IR radiation projection using Abel transformation. Flow structures in the infrared measurement agreed with observations of flame luminosity images and the temperature map. The effect of equivalence ratio on the IR radiation was observed. Liner wall temperature and heat transfer were measured with infrared thermographic camera. The combustor was operated under reacting condition to test realistic heat load inside the industrial combustors. Using quartz glass liner and KG2 filter glass, the IR camera could measure inner wall surface temperature through the glass at high temperature. Time resolved axial distributions of inner/outer wall temperature were obtained, and hot side heat flux distribution was also calculated from time accurate solution of finite difference method. The information about flows and wall heat transfer found in this work are beneficial for numerical simulations for optimized combustor cooling design. Measurement data of flow temperature, velocity field, infrared radiation, and heat transfer can be used as validation purpose or for direct inputs as boundary conditions. Time-independent location of peak location of liner wall temperature was found from time resolved wall temperature measurements and PIV flow measurements. This indicates the location where the cooling design should be able to compensate for the temperature increase in lean premixed swirl combustors. The characteristics on the swirl flows found in this study points out that the reacting changes the flow structure significantly, while the operating conditions has minor effect on the structure. The limitation of non-reacting testing must be well considered for experimental combustor studies. However, reacting testing can be performed cost-effectively for reduced number of conditions, utilizing self-similar characteristics of the flows found in this study. / Ph. D. / The study of flow fields and heat transfer characteristics inside a gas turbine combustor provides one of the most serious challenges for gas turbine researchers because of the harsh environment at high temperatures. Design improvements of gas turbine combustors for higher efficiency, reduced pollutant emissions, safety and durability require better understanding of combustion in swirl flows and thermal energy transfer from the turbulent reacting flows to solid surfaces. Therefore, accurate measurement and prediction of the flows and heat loads are indispensable. This dissertation presents flow details and wall heat flux measurements for reacting flow conditions in a model gas turbine combustor. The information about flows and wall heat transfer found in this work are beneficial for numerical simulations for optimized combustor cooling design. Measurement data of flow temperature, velocity field, infrared radiation, and heat transfer can be used as validation purpose or for direct inputs as boundary conditions. Time-independent location of peak location of liner wall temperature was found from time resolved wall temperature measurements and PIV flow measurements. This indicates the location where the cooling design should be able to compensate for the temperature increase in lean premixed swirl combustors. The characteristics on the swirl flows found in this study points out that the reacting changes the flow structure significantly, while the operating conditions has minor effect on the structure. The limitation of non-reacting testing must be well considered for experimental combustor studies. However, reacting testing can be performed cost-effectively for reduced number of conditions, utilizing self-similar characteristics of the flows found in this study.

Supercritical CO2 (sCO2) has been proposed for many applications, such as power generation, air conditioning, and thermal management of electronic equipment. In proximity to critical conditions, the thermal and transport properties of the CO2 vary abruptly, promoting a significant heat transfer enhancement. Revealing the heat transfer processes associated with CO2 flows requires measuring fluid temperature, pressure, heat transfer coefficients, velocities, etc. However, fundamental knowledge about the heat transfer processes at near-critical conditions is not fully understood. Advanced optical techniques should be considered to measure these properties of sCO2. These techniques include Schlieren Imaging to capture the density gradient, LIF ( Laser Induced Fluorescence) for temperature measurement, and PIV ( Particle Image Velocimetry) for measurement of the velocity flow field. Different experimental setups have been built to apply the advanced optical technique. The Schlieren imaging has been used to capture the density gradient of the methane injection into the chamber filled with CO2 at supercritical thermodynamic conditions. The density gradient in the flow helped to define the jet cone angle. The micro-channel setup was implemented through which a mixture of CO2 and Rh6G dye was flowed. The dye particles will act as a thermal probe and measure the temperature of the CO2 flow at near supercritical conditions by applying the LIF ( Laser Induced Fluorescence). Initially, the feasibility of the backlight micro-PIV technique was demonstrated by performing experiments with the methanol and non-fluorescent tracers. Then the author applied the the same technique for the first time to measure the velocity of the liquid CO2 flow through a T-channel. Furthermore, the bottom of the channel was painted with fluorescence color to excite, which helps to observe the shadows of the non-fluorescent particles used to measure the velocity of the flow.

The object of this investigation will be to obtain curves which will permit easy calculation of the heat transfer through insulation uniformly applied to cylindrical enclosures with flat ends. The curves are to cove the usual range of ratios of cylinder diameter to length and of insulation thickness to cylinder diameter. It is to be assumed that the insulation is homogeneous, that the inside and outside surfaces of the insulation are isothermal, and that the thermal conductivity is constant. The investigation will be confined to a calculated solution for the steady state. Since no calculus solution has been found for this case, the relaxation method will be employed. / M.S.

A thin-film gage was used to measure the fluctuating component of heat transfer from a cylinder placed in a steady crossflow at Reynolds numbers, based on cylinder diameter, of approximately 19,000 and 30,000. Further, a one-dimensional flow pulsation at 13 Hz was added to the mean flow at a Reynolds number of 19,000, and the case of natural shedding locked on to exactly one-half the driving frequency was studied. A Gardon gage was also used to measure the time-averaged heat transfer under the same conditions. Both gages were mounted flush with the cylinder surface. The thin-film gage was maintained at a constant temperature by a constant temperature anemometer unit. A temperature controller actively matched the surrounding cylinder surface to the gage temperature to maintain a constant temperature boundary condition. The frequency response of the thin-film gage system was approximately 60 Hz. Representative time records of the instantaneous heat flux and the local fluid velocity were obtained at different locations by rotating the cylinder through 180°. Correlations between these signals in the time and frequency domain were also measured. Phase relationships between the unsteady heat transfer fluctuations and the local velocity were then obtained over the entire cylinder. In the attached boundary layer region, the heat flux signal was sinusoidal at the shedding frequency for the steady cases and at the driving frequency for the pulsating case. In the wake, however, the fluctuations were less organized in all cases. Here the magnitude of the fluctuations were higher than in the boundary layer region with peak-to-peak fluctuating amplitudes greater than 50% of the mean heat flux levels (as measured by the thin-film gage) over most of the wake. The phase relationship of the signals was nearly constant in the boundary layer region but varied with angular position in the wake indicating the existence of different flow regions in the wake. The local time-averaged heat transfer results reflect a 24% increase in heat transfer in the wake due to pulsation. This is a result of higher fluid velocities in the outer flow at 0 = 90° and in the wake regions when pulsations were added to the flow. A simple analytical model, based on the concept of an impinging jet that was oscillated back-and-forth across the wake, was developed to predict the heat transfer fluctuations in the wake. A parametric study was performed to determine the effect of changing the jet parameters on the predicted heat transfer fluctuations. Time records of the heat transfer fluctuations were obtained around the cylinder based on this model. The fluctuating amplitudes and phases of heat transfer (relative to the velocity) predicted by the model agreed well with the experimental values for the steady flow case. The increase of the local time-averaged heat transfer in the wake region due to flow pulsation was also predicted. / Ph.D.

The heat transfer coefficient is a key parameter in modeling friction stir welding and has yet to be measured experimentally. The importance of this parameter was shown through validating friction stir models on both sides of the tool/workpiece interface. Both a transient plunge and a steady state model were validated by matching experimental temperatures. The steady state tool temperatures were matched (with in 2.5%), but the steady state workpiece temperatures were off by around 20%. The transient model of the FSW plunge showed the effect of varying the ℎ��/�� on workpiece temperatures and tool temperatures. Two methods were looked at to measure this parameter. Using frequency-domain thermoreflectance (FDTR) with a reflective sensor within the tool was initially looked at as a novel way to measure ℎ��/��, but the difficulty of integrating the system with the FSW machine led to its ultimate failure. The 3�� method was the second choice to perform this measurement. The method was not able to measure ℎ��/��, but the method shows promise that after further work it should be able to perform this measurement. Successful thermal conductivity measurements were performed. A initial experimental setup for measuring contact resistance was achieved. Integration of a 3�� sensor with the FSW environment was attempted. High temperature wire bonding was successful; several attempts at sensor integration with the tool failed; and plans for machine integration look promising.

<p>U disertaciji je razvijena nova eksperimentalna postavka za merenje<br />graničnih uslova pri livenju u peščanim kalupima. Utvrđeno je da se<br />uvođenjem pojma prividne toplotne difuzivnosti materijala kalupa<br />može poništiti greška pozicioniranja termoparova i time smanjiti<br />greška procene graničnih uslova. Dodatno, pokazano je da proces<br />izdvajanja intermetalnih jedinjenja tokom procesa očvršćavanja<br />kalupa može uticati na vrednosti graničnih uslova. Razvijena je i<br />nova empirijska korelaciona funkcija kojom se može opisati promena<br />vrednosti koeficijenta prenosa toplote između kalupa i odlivka.</p> / <p>In this study a new experimental technique and apparatus for estimation of<br />boundary conditions in sand casting process were developed. It is shown<br />that thermocouple positioning errors can be nullified by introducing a concept<br />of apparent heat diffusivity of the mold material. In this way, total error of the<br />heat transfer estimation can be reduced. Additionally, it was found that the<br />process of precipitation of intermetallic compounds can influence the value of<br />achieved metal-mold heat transfer. A novel empirical correlation function is<br />proposed. This function has the ability to accurately describe the change in<br />interfacial heat transfer with the casting surface temperature.</p>

Film cooling is a cooling technique widely used in high-performance gas turbines to protect turbine airfoils from being damaged by hot flue gases. Film injection holes are placed in the body of the airfoil to allow coolant to pass from the internal cavity to the external surface. The ejection of coolant gas results in a layer or “film” of coolant gas flowing along the external surface of the airfoil. In this study, a new cooling scheme, mist/air film cooling is proposed and investigated through experiments. Small amount of tiny water droplets with an average diameter about 7 μm (mist) is injected into the cooling air to enhance the cooling performance. A wind tunnel system and test facilities were build. A Phase Doppler Particle Analyzer (PDPA) system is employed to measure droplet size, velocity and turbulence. Infrared camera and thermocouples are both used for temperature measurements. Mist film cooling performance is evaluated and compared against air-only film cooling in terms of adiabatic film cooling effectiveness and film coverage. Experimental results show that for blowing ratio M=0.6, net enhancement in adiabatic cooling effectiveness can reach 190% locally and 128% overall along the centerline. The general pattern of adiabatic cooling effectiveness distribution of the mist case is similar to that of the air-only case with the peak at about the same location. The concept of Film Decay Length (FDL) is proposed to quantitatively evaluate how well the coolant film covers the blade surface. Application of mist in the M=0.6 condition is apparently superior to the M=1.0 and 1.4 cases due to the higher overall cooling enhancement, the much longer FDL, and wider and longer film cooling coverage area. Based on droplet measurements through PDPA, a profile describing how the airmist coolant jet flow spreads and eventually blends into the hot main flow is proposed. A sketch based on the proposed profile is provided. This profile is found to be well supported by the measurement results of Turbulent Reynolds Stress. The location where a higher magnitude of Turbulent Reynolds Stress exists, which indicates higher strength of turbulent mixing effect, is found to be in the close neighborhood of the edge of the coolant film envelope. Also the separation between the mist droplets layer and the coolant air film is identified through the measurements. In other words, large droplets penetrate through the air coolant film layer and travel further over into the main flow. Based on the proposed air-mist film profile, the heat transfer results are reexamined. It is found that the location of optimum cooling effect is coincident with the starting point where the air-mist coolant starts to bend towards the surface. Thus the data suggests that the “bending back” film pattern is critical in keeping the mist droplets close to the surface which improves the cooling effectiveness for mist cooling.