Este trabalho estabelece critérios para avaliar a resistência ao fogo de tubulações fabricadas com compostos vinílicos, com diferentes teores de cloro, para os sistemas prediais de chuveiros automáticos, verificando o relacionamento entre os resultados obtidos nos ensaios realizados em trechos de tubulações pressurizados e submetidos a uma elevação de temperatura e os resultados observados nos ensaios realizados em tubulações em escala real exposta diretamente às chamas, simulando uma situação de incêndio. Assim, nos ensaios em trechos de tubulações ocorreu um aumento da resistência ao fogo proporcional ao aumento do teor de cloro dos compostos; nos ensaios em tubulações em escala real observou-se que corpos-deprova com tubos vinílicos grau a partir de 64 (grau este relacionado ao teor de cloro) suportam as condições de exposição ao fogo; a relação entre os ensaios mostrou que tubulações fabricadas com um composto vinílico com resistência a partir de 110 segundos de exposição ao fogo, no ensaio em trechos de tubulações, suportam também as condições estabelecidas no ensaio em escala real. Isto indicou a possibilidade de se utilizar o ensaio em trechos de tubulações para avaliar, preliminarmente, a capacidade dos materiais em resistir ao fogo, antes de serem submetidos ao ensaio em escala real, pois este apresenta maiores custos envolvidos e maiores dificuldades na sua execução. / This work establishes standards to evaluate the fire resistance of the piping manufactured with vinyl compounds, with different chlorine contents, for buildings sprinklers systems, verifying the relation amongst the results obtained with pressured small sections of piping and submitted to a temperature rise, and the results obtained from the real scale tests, simulating a fire situation with the samples in real scale were exposed to the flames. Therefore, in the small sections of piping tests an increase of the fire resistance proportional to the chlorine content of the compositions increases occurred; in the real scale tests observed that the piping with degree starting from 64 (degree related with to the chlorine contents) per cent supports the exposition to the flames; the relation between the tests showed that piping manufactured with vinyl compounds with fire resistance starting from 110 seconds of the small sections of piping tests, also supports the established conditions in the real scale tests. It was shown the possibility to employ the reduced scale test to evaluate, previously, the fire resistance of the materials previous to the real scale tests, which is more expensive and shows bigger difficulties to be done.

Modeling the atmospheric entry of spacecraft is challenging because of the large number of physical phenomena that occur during the process. In order to study thermal protection systems, engineers rely on high fidelity solvers to provide accurate predictions of both the thermochemical environment surrounding the heat shield, and its material response. Therefore, it is necessary to guarantee that the numerical models are correctly implemented and thoroughly validated. In recent years, a high-fidelity modeling tool has been developed at the University of Kentucky for the purpose of studying atmospheric entry. The objective of this work is to verify and validate this code. The verification consists of the development of an automated regression testing utility. It is intended to both aid code developers in the debugging process, as well as verify the correct implementation of the numerical models as these are developed. The validation process will be performed through comparison to relevant ablation experiments, namely arc-jet tests. Two modules of the code are used: fluid dynamics, and material response. First the fluid dynamics module is verified against both computational and experimental data on two distinct arc-jet tests. The material response module is then validated against arc-jet test data using PICA.

Heatshield design and analysis has traditionally been a decoupled process, the designer creates the geometry generally without knowledge about how the design variables affect the thermostructural response or how the system will perform under off nominal conditions. Heatshield thermal and structural response analyses are generally performed as separate tasks where the analysts size their respective components and feedback their results to the designer who is left to interpret them. The analysts are generally unable to provide guidance in terms of how the design variables can be modified to meet geometric constraints and not exceed the thermal or structural design specifications. In general, the thermal response analysis of ablative thermal protection systems has traditionally been performed using a one-dimensional finite difference calculation. The structural analyses are generally one, two, or three-dimensional finite element calculations. In this dissertation, the governing differential equations for ablative thermal response are solved in three-dimensions using the finite element method. Darcy' Law is used to model the flow of pyrolysis gas through the ablative material. The three-dimensional governing differential equations for Darcy flow are solved using the finite element method as well. Additionally, the equations for linear elasticity are solved by the finite element method for the thermal stress using temperatures directly from the thermal response calculations. This dissertation also links the analysis of thermal protection systems to their design. The link to design comes from understanding the variation in the thermostructural response over the range of the design variables. Material property sensitivities are performed and an optimum design is determined based on a deterministic analysis minimizing the design specification of bondline temperature subject to appropriate constraints. A Monte Carlo simulation is performed on the optimum design to determine the probability of exceeding the design specifications. The design methodology is demonstrated on the Orion Crew Exploration Vehicle's compression pad design.

The thermal response analysis of an ablative material on a two dimensional external surface is performed. The method is applied to both rectangular and cylindrical coordinate systems, where rectangular coordinate system is used for comparison with results available in literature. The current study solves the decomposition of the material at high temperatures by using the nth order Arrhenius equation but excludes the removal of char from the surface due to mechanical erosion or phase change and considers that the ablation process takes place in a finite zone. The method considers the whole domain as one computational domain, eliminating the necessity to check the positions of the start and end of decomposition zone. The decomposition of pyrolysis gases and/or char that may occur at high temperatures and the chemical reaction between pyrolysis gases and char is neglected while pyrolysis gases are assumed to behave as ideal gas. The pressure is taken as a constant value on a whole physical domain. The formulation for one-dimensional case is validated by experimental results obtained from literature. The two-dimensional case in a Cartesian geometry is formulated and an algebraic transformation is used to normalize the region in both directions and transformed at same time into a square computational domain in order to get a solution for the variable thickness domains. The formulation for two-dimensional case is revised for the cylindrical coordinates with finite length in the axial direction. To solve geometries where the outer surface deviates from cylindrical, the formulation is scaled and transformed into a non-dimensional square computational domain. The method is also applied to a two layer material problem in axisymmetric geometry. In all problems, the radiation and constant heat flux boundary conditions exist on the outer surface while whole domain is initially at a constant temperature. Case studies are performed to demonstrate the application of the solution method in optimizing the insulation material thickness.

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Este trabalho estabelece critérios para avaliar a resistência ao fogo de tubulações fabricadas com compostos vinílicos, com diferentes teores de cloro, para os sistemas prediais de chuveiros automáticos, verificando o relacionamento entre os resultados obtidos nos ensaios realizados em trechos de tubulações pressurizados e submetidos a uma elevação de temperatura e os resultados observados nos ensaios realizados em tubulações em escala real exposta diretamente às chamas, simulando uma situação de incêndio. Assim, nos ensaios em trechos de tubulações ocorreu um aumento da resistência ao fogo proporcional ao aumento do teor de cloro dos compostos; nos ensaios em tubulações em escala real observou-se que corpos-deprova com tubos vinílicos grau a partir de 64 (grau este relacionado ao teor de cloro) suportam as condições de exposição ao fogo; a relação entre os ensaios mostrou que tubulações fabricadas com um composto vinílico com resistência a partir de 110 segundos de exposição ao fogo, no ensaio em trechos de tubulações, suportam também as condições estabelecidas no ensaio em escala real. Isto indicou a possibilidade de se utilizar o ensaio em trechos de tubulações para avaliar, preliminarmente, a capacidade dos materiais em resistir ao fogo, antes de serem submetidos ao ensaio em escala real, pois este apresenta maiores custos envolvidos e maiores dificuldades na sua execução. / This work establishes standards to evaluate the fire resistance of the piping manufactured with vinyl compounds, with different chlorine contents, for buildings sprinklers systems, verifying the relation amongst the results obtained with pressured small sections of piping and submitted to a temperature rise, and the results obtained from the real scale tests, simulating a fire situation with the samples in real scale were exposed to the flames. Therefore, in the small sections of piping tests an increase of the fire resistance proportional to the chlorine content of the compositions increases occurred; in the real scale tests observed that the piping with degree starting from 64 (degree related with to the chlorine contents) per cent supports the exposition to the flames; the relation between the tests showed that piping manufactured with vinyl compounds with fire resistance starting from 110 seconds of the small sections of piping tests, also supports the established conditions in the real scale tests. It was shown the possibility to employ the reduced scale test to evaluate, previously, the fire resistance of the materials previous to the real scale tests, which is more expensive and shows bigger difficulties to be done.

Made available in DSpace on 2014-10-09T12:42:57Z (GMT). No. of bitstreams: 0 / Made available in DSpace on 2014-10-09T14:08:02Z (GMT). No. of bitstreams: 1 05358.pdf: 6193324 bytes, checksum: c9b68865b6cec7bb9c83ee65a4e97865 (MD5) / Dissertacao (Mestrado) / IPEN/D / Instituto de Pesquisas Energeticas e Nucleares - IPEN/CNEN-SP

Made available in DSpace on 2014-10-09T12:26:16Z (GMT). No. of bitstreams: 0 / Made available in DSpace on 2014-10-09T14:09:46Z (GMT). No. of bitstreams: 0 / Dissertacao (Mestrado) / IPEN/D / Instituto de Pesquisas Energeticas e Nucleares - IPEN-CNEN/SP

This thesis examines the modeling of the shock-layer radiative heating associated with hypersonic vehicles entering the atmospheres of Earth and Titan. For Earth entry, flight conditions characteristic of lunar-return are considered, while for Titan entry, the Huygens probe trajectory is considered. For both cases, the stagnation region flowfield is modeled using a two-temperature chemical nonequilibrium viscous shock layer (VSL) approach. This model is shown to provide results that are in agreement with the more computationally expensive Navier-Stokes solutions. A new radiation model is developed that applies the most up-to-date atomic and molecular data for both the spectrum and non-Boltzmann modeling. This model includes a new set of atomic-lines, which are shown to provide a significant increase in the radiation (relative to previous models) resulting from the 1 - 2 eV spectral range. A new set of electronic-impact excitation rates was compiled for the non-Boltzmann modeling of the atomic and molecular electronic states. Based on these new rates, a novel approach of curve-fitting the non-Boltzmann population of the radiating atomic and molecular states was developed. This new approach provides a simple and accurate method for calculating the atomic and molecular non-Boltzmann populations. The newly-developed nonequilibrium VSL flowfield and nonequilibrium radiation models were applied to the Fire II and Apollo 4 cases, and the resulting radiation predictions were compared with the flight data. For the Fire II case, the present radiation-coupled flowfield model provides intensity values at the wall that predicted the flight data better than any other previous study, on average, throughout the trajectory for the both the 0.2 - 6.0 eV and 2.2 - 4.1 eV spectral ranges. The present results over-predicted the calorimeter measurements of total heat flux over most of the trajectory. This was shown to possibly be a result of the super-catalytic assumption for the wall boundary condition, which caused the predicted convective heating to be too high. For the Apollo 4 case, over most of the trajectory the present model over-predicted the flight data for the wall radiative intensity values between 0.2 - 6.2 eV. For the analysis of Huygens entry into Titan, the focus of the radiation model was the CN violet band. An efficient and accurate method of modeling the radiation from this band system was developed based on a simple modification to the smeared rotational band (SRB) model. This modified approach, labeled herein as SRBC, was compared with a detailed line-by-line (LBL) calculation and shown to compare within 5% in all cases. The SRBC method requires many orders-of-magnitude less computational time than the LBL method, which makes it ideal for coupling to the flowfield. The non-Boltzmann modeling of the CN electronic states, which govern the radiation for Huygens entry, is discussed and applied. The radiation prediction resulting from the non-Boltzmann model is up to 70% lower than the Boltzmann result. A new method for treating the escape factor in detail, rather than assuming a value equal to one, was developed. This treatment is shown to increase the radiation from the non-Boltzmann model by about 10%. / Ph. D.