A scaled-up gas turbine vane model was constructed in such a way to achieve a Biot number (Bi) representative of an actual engine component, and experiments were performed to collect temperature data which may be used to validate computational fluid dynamics (CFD) codes used in the design of gas turbine cooling schemes. The physical model incorporated an internal impingement plate to provide cooling on the inner wall surface, and film cooling over the external surface was provided by a single row of holes located on the suction side of the vane. A single row of holes was chosen to simplify the operating condition and test geometry for the purpose of evaluating CFD predictions. Thermocouples were used to measure internal gas temperatures and internal surface temperatures over a range of coolant flow rates, while infra-red thermography was used to measure external surface temperatures. When Bi is matched to an actual engine component, these measured temperatures may be normalized relative to the coolant temperature and mainstream gas temperature to determine the overall cooling effectiveness, which will be representative of the real engine component. Measurements were made to evaluate the overall effectiveness resulting from internal impingement cooling alone, and then with both internal impingement cooling and external film cooling as the coolant flow rate was increased. As expected, with internal impingement cooling alone, both internal and external wall surfaces became colder as the coolant flow rate was increased. The addition of film cooling further increased the overall effectiveness, particularly at the lower and intermediate flow rates tested, but provided little benefit at the highest flow rates. An optimal jet momentum flux ratio of I=1.69 resulted in a peak overall effectiveness, although the film effectiveness was shown to be low under these conditions. The effect of increasing the coolant-to-mainstream density ratio was evaluated at one coolant flow rate and resulted in higher values of overall cooling effectiveness and normalized internal temperatures, throughout the model. Finally, a 1-dimensional heat transfer analysis was performed (using a resistance analogy) in which overall effectiveness with film cooling was predicted from measurements of film effectiveness and overall effectiveness without film cooling. This analysis tended to over-predict overall effectiveness, at the lowest values of the jet momentum flux ratio, while under-predicting it at the highest values. / text

Two sets of experiments were performed on a simulated turbine nozzle guide vane. First, adiabatic and overall effectiveness measurements were taken in the showerhead region of the vane using adiabatic and matched Biot vane models, respectively. Measurements of overall effectiveness in the showerhead region are not found in the literature, and are a useful baseline for validating the results of computational fluid dynamics (CFD) simulations. Overall effectiveness is useful because it shows the results of combining film cooling, internal convection, and surface conduction to provide a more complete picture of vane cooling than adiabatic effectiveness. An impingement plate was utilized to generate internal jet cooling. Momentum flux ratios were matched between the models and ranged from I*SH = 0.76 to 6.70, based on showerhead upstream approach velocity. The second set of experiments used a different model to examine the effects of surface curvature on adiabatic effectiveness. Results in open literature are found by varying the radius of curvature of a fixed setup, so the current approach was novel in that it looked at adiabatic effectiveness at locations of various curvature around the same vane. Blowing ratios from M = 0.4 to M = 1.6 were tested at a density ratio of DR = 1.20 for two locations on the suction side of the vane. Results were presented in terms of laterally averaged adiabatic effectiveness and contour plots of adiabatic effectiveness, and were compared to literature. / text

This study focused on experimentally measuring the performance of a fully cooled, scaled up C3X turbine vane. Experimental measurements focused on investigating row-to-row interactions of coolant jets and the contributions of external film cooling and internal impingement cooling to overall cooling effectiveness. Overall effectiveness was experimentally measured using a thermally scaled, matched Biot number vane model featuring a realistic internal impingement scheme and had normalized surface temperatures that were representative of those found on engine components. A geometrically identical vane was also constructed out of low conductivity polystyrene foam to measure the normalized adiabatic wall temperature, or adiabatic effectiveness of the film cooling configuration. The vanes featured a full coverage film-cooling scheme with a five-row showerhead and 13 total rows of holes containing 149 total coolant holes. This study was the first study to make highly detailed measurements of overall effectiveness on a fully-cooled vane model and expands on previous studies of adiabatic and overall effectiveness on the showerhead and single rows of holes on a matched Biot vane by considering a fully cooled configuration to determine if the results from these previous studies also hold for a fully cooled configuration. Additionally, velocity and thermal fields were measured just upstream of two different suction side rows of holes in order to study the effect of introducing upstream coolant injection. The effects of mainstream turbulence and span-wise location were examined and at the downstream row of holes, the contributions of different rows of holes to the approach flow were compared. This study was the first to measure mean and fluctuating velocity data on the suction side of a turbine vane with upstream coolant injection. Understanding the effects of how upstream injection affects the performance of downstream rows of holes is critical to understanding the film cooling performance on a fully cooled turbine airfoil. / text

In this study, the cooling of a simulated blade under increasing pitch between holes was examined. The change in non-dimensional surface temperature, phi, was measured experimentally to quantify this performance loss. This critical quantification of the sensitivity of cooling to pitch between holes has not been studied previously. A range of blowing ratios and angles of attack were tested. Data are presented in terms of the laterally averaged phi, and in terms of the minimum phi, arguably more important from a design perspective. Increasing the pitch 13% produced no measureable change using either parameter. An increase of 26% in pitch produced only a 4% loss in lateral averages, while some hot points dropped by 10%. These small changes are due to compensating effects of increased internal and through-hole convective cooling. A limit to these effects was shown when increasing pitch 53%. While performance loss in the average was still relatively small at 15%, the minimum phi decreased by 27%. Heat flux gauges were used to gather data on the internal and external surface. The internal impingement used in this study represents a more accurate representation of internal cooling for an actual engine part than has been previously studied, providing a starting point for exploring the differences between engine configurations and those generally investigated in the literature. External heat flux measurements were used to measure the ratio of heat flux with and without film cooling. These results call into question the use of the net heat flux reduction parameter, which is commonly used to quantify overall film cooling performance. / text

The efficiency of natural gas turbines is directly linked to the turbine inlet temperature, or the combustor exit temperature. Further increasing the turbine inlet temperature damages the turbine components and limits their durability. Advances in turbine vane cooling schemes protect the turbine components. This thesis studies the conjugate effects of internal cooling, film cooling and thermal barrier coatings (TBC) on turbine vane metal temperatures. Two-dimensional thermal profiles were experimentally measured downstream of a single row of film cooling holes on both an adiabatic and a matched Biot number model turbine vane. The measurements were taken as a comparison to computational simulations of the same model and flow conditions. To improve computational models of the evolution of a film cooling jet as it propagates downstream, the thermal field above the vane, not just the footprint on the vane surface must be analyzed. This study expands these data to include 2-D thermal fields above the vane at 0, 5 and 10 hole diameters downstream of the film cooling holes. In each case the computational jets remained colder than the experimental jets because they did not disperse into the mainstream as quickly. Finally, in comparing results above adiabatic and matched Biot number models, these thermal field measurements allow for an accurate analysis of whether or not the adiabatic wall temperature was a reasonable estimate of the driving temperature for heat transfer. In some cases the adiabatic wall temperature did give a good indication of the driving temperature for heat transfer while in other cases it did not. Previous tests simulating the effects of TBC on an internally and film cooled model turbine vane showed that the insulating effects of TBC dominate over variations in film cooling geometry and blowing ratio. In this study overall and external effectiveness were measured using a matched Biot number model vane simulating a TBC of thickness 0.6d, where d is the film cooing hole diameter. This new model was a 35% reduction in thermal resistance from previous tests. Overall effectiveness measurements were taken for an internal cooling only configuration, as well as for three rows of showerhead holes with a single row of holes on the pressure side of the vane. This pressure side row of holes was tested both as round holes and as round holes embedded in a realistic trench with a depth of 0.6 hole diameters. Even in the case of this thinner TBC, the insulating effects dominate over film cooling. In addition, using measurements of the convective heat transfer coefficient above the vane surface, and the thermal conductivities of the vane wall and simulated TBC material, a prediction technique of the overall effectiveness with TBC was evaluated. / text

This study performed detailed measurements on and around scaled up conducting and adiabatic airfoils with and without film cooling. The conducting vane was a matched Bi airfoil, which accurately scaled the convective heat transfer and conduction through the solid, in order to produce non-dimensional surface temperatures and thermal boundary layers that were representative of an actual engine. Measurements made on all vane models included surface temperature measurements and thermal profiles above the walls. Separate measurements on non-film cooled and film cooled conducting models allowed for the individual contributions of the internal convective cooling and external film cooling to the overall cooling scheme to be quantified. Surface temperature and thermal field measurements above the wall were also performed on a film cooled adiabatic model. For the conducting model with internal cooling only, strong streamwise temperature variations were seen. The surface temperature variations were highly dependent on the local external and internal heat transfer coefficients. Spanwise temperature variations also existed, but were modest in comparison to streamwise variations. Comparing the thermal fields above the film cooled adiabatic and conducting walls allowed for the assumption that the conducting wall would not significantly affect the thermal field in the film cooling jet to be tested. Near the edge of the film cooling jet the developing thermal boundary layer had a clear effect on the overlying gas temperature, suggesting that the common assumption that the adiabatic wall temperature is the appropriate driving temperature for heat transfer to a film cooled wall was invalid. On the jet centerline thermal boundary layer effects were less influential, due to the development of a new, thin boundary layer. This suggested that the adiabatic wall temperature as driving temperature for heat transfer was a reasonable assumption on the jet centerline for most cases tested. As film cooling momentum flux ratio increase, thermal boundary layer effects became more influential on the jet centerline. Additionally, the high resolution surface temperature measurements and thermal field measurements above the wall presented in the current study represent a significant improvement in the data available for validation of computational simulations of conducting turbine airfoils. / text

Made available in DSpace on 2014-12-17T14:27:27Z (GMT). No. of bitstreams: 1 SealtielDO_DISSERT.pdf: 3399268 bytes, checksum: 1a83565dd029a077e85e5685d4a39607 (MD5) Previous issue date: 2013-08-30 / The independence of the United States and the revolutions that emerged in Europe in the eighteenth century led to the birth of the written constitution, with a mission to limit the power of the State and to ensure fundamental rights to citizens. Thus, the Constitution has become the norm and ultimate founding of the State. Because of this superiority felt the need to protect her, emerging from that constitutional jurisdiction, taking control of constitutionality of provisions his main instrument. In Brazil, the constitutionality control began with the Constitution of 1891, when "imported" the American model, which is named after incidental diffuse model of judicial review. Indeed, allowed that any judge or court could declare the unconstitutionality of the law or normative act in a concrete case. However, the Brazilian Constituent did not bring the U.S. Institute of stare decisis, by which the precedents of higher courts eventually link the below. Because of this lack, each tribunal Brazilian freely decide about the constitutionality of a rule, so that the decision took effect only between the parties to the dispute. This prompted the emergence of conflicting decisions between judicantes organs, which ultimately undermine legal certainty and the image of the judiciary. As a solution to the problem, was incorporated from the 1934 Constitution to rule that the Senate would suspend the law declared unconstitutional by the Supreme Court. With the introduction of abstract control of constitutionality, since 1965, the Supreme Court went on to also have the power to declare the invalidity of the provision unconstitutional, effectively against all without the need for the participation of the Senate. However, it remained the view that in case the Supreme Court declared the unconstitutionality of the fuzzy control law by the Senate would continue with the competence to suspend the law unconstitutional, thus the decision of the Praetorium Exalted restricted parties. The 1988 Constitution strengthened the abstract control expanding legitimized the Declaratory Action of Unconstitutionality and creating new mechanisms of abstract control. Adding to this, the Constitutional Amendment. No. 45/2004 brought the requirement of general repercussion and created the Office of Binding Precedent, both to be applied by the Supreme Court judgments in individual cases, thus causing an approximation between the control abstract and concrete constitutional. Saw themselves so that the Supreme Court, to be the guardian of the Constitution, its action should be directed to the trial of issues of public interest. In this new reality, it becomes more necessary the participation of the Senate to the law declared unconstitutional in fuzzy control by the Supreme Court can reach everyone, because such an interpretation has become obsolete. So, to adapt it to this reality, such a rule must be read in the sense that the Senate give publicity to the law declared unconstitutional by the Supreme Court, since mutated constitutional / A independ?ncia dos Estados Unidos e as revolu??es surgidas na Europa no s?culo XVIII propiciaram o nascimento da Constitui??o escrita, com a miss?o de limitar o poder do Estado e assegurar direitos fundamentais aos cidad?os. Assim, a Constitui??o tornou-se a norma fundante e suprema do Estado. Em raz?o dessa superioridade sentiu-se a necessidade de proteg?-la, surgindo a partir da? a jurisdi??o constitucional, tendo no controle de constitucionalidade de normas o seu principal instrumento. No Brasil, o controle de constitucionalidade iniciou-se com a Constitui??o de 1891, quando se importou o modelo americano, que recebeu o nome de modelo difuso incidental de controle de constitucionalidade. Com efeito, permitiu-se que qualquer juiz ou tribunal poderia declarar a inconstitucionalidade de lei ou ato normativo em um caso concreto. Entretanto, o constituinte brasileiro n?o trouxe dos Estados Unidos o instituto do stare decisis, atrav?s do qual os precedentes dos ?rg?os judiciais superiores acabam por vincular os inferiores. Em raz?o dessa aus?ncia, cada juiz ou tribunal brasileiro decidia livremente a respeito da constitucionalidade de norma, de tal maneira que a decis?o s? produzia efeitos entre as parte do lit?gio. Isso levou o surgimento de decis?es contradit?rias entre os ?rg?os judicantes, o que acabou por abalar a seguran?a jur?dica e a imagem do Judici?rio. Como sa?da para o problema, incorporou-se a partir da Constitui??o de 1934 a regra segundo a qual o Senado poderia suspender a lei declarada inconstitucional pelo Supremo Tribunal Federal. Com a introdu??o do controle abstrato de constitucionalidade, a partir de 1965, o Supremo Tribunal Federal passou a ter, tamb?m, o poder de declarar a invalidade da norma inconstitucional, com efic?cia contra todos, sem a necessidade de participa??o do Senado. Por?m, permaneceu a concep??o de que na hip?tese de o Supremo Tribunal Federal declarar a inconstitucionalidade de lei atrav?s do controle difuso o Senado continuaria com a compet?ncia de suspender a lei inconstitucional, ficando a decis?o do Pret?rio Excelso restrito ?s partes. A Constitui??o de 1988 fortaleceu o controle abstrato ampliando os legitimados da A??o Direta de Inconstitucionalidade e criando novos mecanismos de controle abstrato. Somando-se a isso, a Emenda Constitucional n.? 45/2004 trouxe o requisito da repercuss?o geral e introduziu o instituto da S?mula Vinculante, ambos para serem aplicados pelo Supremo Tribunal Federal nos julgamentos dos casos concretos, provocando consequentemente uma aproxima??o entre os controles abstrato e concreto de constitucionalidade. Enxergou-se destarte que o Supremo Tribunal Federal, como guardi?o da Constitui??o, deveria ter a sua atua??o pautada para o julgamento de quest?es de interesse p?blico. Nesta nova realidade ? desnecess?ria a participa??o do Senado para que a lei declarada inconstitucional no controle difuso pelo Supremo Tribunal Federal possa alcan?ar a todos, pois, tal interpreta??o tornou-se obsoleta. Por conseguinte, para adequ?-la a essa realidade, tal regra deve ser lida no sentido de que o Senado dar? publicidade ? lei declarada inconstitucional pelo Supremo Tribunal Federal, vez que sofreu muta??o constitucional

This study focused on experimentally determining the cooling performance of a fully cooled, scaled-up model of a C3X turbine vane. The primary objective was to determine the differences in overall effectiveness in the presence and absence of a hot mainstream flowing over the vane. Overall effectiveness was measured using a thermally scaled matched Biot number vane with an impingement plate providing the internal cooling. This is the first study focused on investigating the effect of removing the mainstream flow and comparing the contour and laterally-averaged effectiveness data in support of the development of an assembly line thermal testing method. It was found that the proposed method of factory floor testing of turbine component cooling performance did not provide comparable information to traditional overall effectiveness test methods. A second experiment was performed in which the effect of altering the angle of attack of a flow into a passive turbulence generator was investigated. Measurements in the approach flow were taken using a single wire hot-wire anemometer. This study was the first to investigate the effects such a setup would have on fluctuating flow quantitates such as turbulence intensity and integral length scale rather than simply the mean quantities. It was found that both the downstream turbulence intensity and the turbulence integral length scale increase monotonically with approach flow incidence angle at a specified distance downstream of the turbulence generator. / text