A superliga policristalina à base de níquel MAR-M247 foi desenvolvida na década de 70. Sua ótima composição, estabilidade microestrutural, excelente resistência à fluência e à oxidação e boa resistência à corrosão a quente faz dessa superliga uma das mais utilizadas em rotores durante os últimos 20 anos. Os objetivos do presente trabalho são a produção e caracterização microestrutural e mecânica de rotores da superliga MARM247 (10% peso Co, 10W, 8.25Cr, 5.5Al, 3Ta, 1.5Hf, 1Ti, 0.7Mo, 0.15C, 0.05Zr, 0.015B, Ni balanço). Os rotores foram obtidos pela técnica de microfusão por cera perdida na empresa Açotécnica S.A. (Jandira/SP) em diferentes temperaturas de vazamento e isolamento do molde cerâmico. Os materiais foram analisados por microscopia ótica e eletrônica de varredura (MEV/EDS), análise térmica diferencial (DTA), macro/microdureza e ensaios de tração convencional a 25oC e a 760oC. Além disso, os materiais passaram por tratamentos térmicos de solubilização e envelhecimento em diferentes temperaturas e tempos a fim de avaliar as mudanças microestruturais. Com a ajuda do software de cálculo termodinâmico Thermocalc foram feitas simulações das relações de fases utilizando a composição média da superliga MAR-M247. Os resultados permitiram obter uma condição de processamento (temperatura de vazamento e condição de isolamento) com maior quantidade de peças sem defeitos. Além disso, os experimentos permitiram definir uma condição ideal para o tratamento térmico de solubilização da superliga MAR-M247. / The polycrystalline nickel-based superalloy MAR-M247 was developed in the 1970s. Its optimal alloy composition, microstructural stability, excellent resistance to creep and oxidation and good resistance to hot corrosion make the MAR-M247 superalloy one of the alloys widely used in turbine rotors during the last 20 years. The aims of the present work are the production and the microstructural and mechanical characterization of rotors made of MAR-M247 superalloy (10 wt. % Co, 10W, 8.25Cr, 5.5Al, 3Ta, 1.5Hf, 1Ti, 0.7Mo, 0.15C, 0.05Zr, 0.015B, Ni balance). The rotors were produced by using the lost-wax technique at different pouring temperatures and isolation of the shell mold at the Açotécnica S.A. company (Jandira/SP). The materials were analyzed by optical and scanning electron microscopy (SEM/EDS), differential thermal analysis (DTA), macro/microhardness and tensile tests at 25oC and 760oC. Besides, the materials were submitted to solution and ageing treatments at different temperatures and times in order to evaluate de microstructural changes. With the aid of the thermodynamic calculation software Thermocalc, simulations of phase relations were made using the average composition of the MAR-M247 superalloy. The results allowed to obtain a processing condition (pouring temperature and isolation condition) with larger amount of rotors without defects. Moreover, the experiments allowed to define an ideal solution heat treatment condition of MAR-M247 superalloy.

A superliga policristalina à base de níquel MAR-M247 foi desenvolvida na década de 70. Sua ótima composição, estabilidade microestrutural, excelente resistência à fluência e à oxidação e boa resistência à corrosão a quente faz dessa superliga uma das mais utilizadas em rotores durante os últimos 20 anos. Os objetivos do presente trabalho são a produção e caracterização microestrutural e mecânica de rotores da superliga MARM247 (10% peso Co, 10W, 8.25Cr, 5.5Al, 3Ta, 1.5Hf, 1Ti, 0.7Mo, 0.15C, 0.05Zr, 0.015B, Ni balanço). Os rotores foram obtidos pela técnica de microfusão por cera perdida na empresa Açotécnica S.A. (Jandira/SP) em diferentes temperaturas de vazamento e isolamento do molde cerâmico. Os materiais foram analisados por microscopia ótica e eletrônica de varredura (MEV/EDS), análise térmica diferencial (DTA), macro/microdureza e ensaios de tração convencional a 25oC e a 760oC. Além disso, os materiais passaram por tratamentos térmicos de solubilização e envelhecimento em diferentes temperaturas e tempos a fim de avaliar as mudanças microestruturais. Com a ajuda do software de cálculo termodinâmico Thermocalc foram feitas simulações das relações de fases utilizando a composição média da superliga MAR-M247. Os resultados permitiram obter uma condição de processamento (temperatura de vazamento e condição de isolamento) com maior quantidade de peças sem defeitos. Além disso, os experimentos permitiram definir uma condição ideal para o tratamento térmico de solubilização da superliga MAR-M247. / The polycrystalline nickel-based superalloy MAR-M247 was developed in the 1970s. Its optimal alloy composition, microstructural stability, excellent resistance to creep and oxidation and good resistance to hot corrosion make the MAR-M247 superalloy one of the alloys widely used in turbine rotors during the last 20 years. The aims of the present work are the production and the microstructural and mechanical characterization of rotors made of MAR-M247 superalloy (10 wt. % Co, 10W, 8.25Cr, 5.5Al, 3Ta, 1.5Hf, 1Ti, 0.7Mo, 0.15C, 0.05Zr, 0.015B, Ni balance). The rotors were produced by using the lost-wax technique at different pouring temperatures and isolation of the shell mold at the Açotécnica S.A. company (Jandira/SP). The materials were analyzed by optical and scanning electron microscopy (SEM/EDS), differential thermal analysis (DTA), macro/microhardness and tensile tests at 25oC and 760oC. Besides, the materials were submitted to solution and ageing treatments at different temperatures and times in order to evaluate de microstructural changes. With the aid of the thermodynamic calculation software Thermocalc, simulations of phase relations were made using the average composition of the MAR-M247 superalloy. The results allowed to obtain a processing condition (pouring temperature and isolation condition) with larger amount of rotors without defects. Moreover, the experiments allowed to define an ideal solution heat treatment condition of MAR-M247 superalloy.

A necessidade de trabalhos em altas temperaturas exige o desenvolvimento de materiais com elevada resistência química e mecânica em temperaturas que podem chegar próximas ao seu ponto de fusão. Em especial, os materiais empregados devem apresentar bom comportamento em fluência, de modo a suportar a combinação de altas tensões e altas temperaturas com o mínimo de deformação. O presente trabalho visa caracterizar a superliga MAR-M247, fornecida pela empresa Açotécnica, em condições de fluência para a produção de rotores empregados em turbocompressores automotivos. Os trabalhos são divididos em duas etapas. Na primeira estuda-se a melhor combinação de tratamentos térmicos de solubilização e envelhecimento, chegando à condição de solubilização por 5 horas a 1250?C e envelhecimento por 20 horas a 980?C. Um trabalho de outro aluno (SILVA, 2011) realiza o mesmo estudo para uma variação da superliga MAR-M247 em que o tântalo é totalmente substituído por nióbio. Neste caso, a melhor condição de tratamento é solubilização a 1260?C por 8 h seguida de envelhecimento duplo por 5 h a 880?C e 20 h a 780?C. Na segunda etapa, os materiais dos dois trabalhos, nas melhores condições de tratamento para cada um, são testados em condições de fluência a 850?C a 370, 390, 410 e 430 MPa. A superliga convencional apresenta os maiores valores de vida em fluência enquanto a modificada apresenta os maiores valores de ductilidade. A análise de fratura dos materiais ensaiados a 390 e 430 MPa mostra a presença massiva de carbonetos em toda a extensão da microestrutura, apresentando, em muitos casos, uma morfologia de \"escrita chinesa\". Apesar disso, todas as amostras apresentam grande quantidade de vazios, indicando que sua nucleação e crescimento são os responsáveis pela fratura do material. / The needing for high temperature work claim for new materials capable of maintain high strength and good corrosion resistance at temperatures that could reach values near their melting point. Such materials must be creep resistant to withstand high levels of tension and temperature. The aim of this work is the characterization of MAR-M247 under creep conditions for the production of automotive turbocharger rotors made by Açotécnica. The work is split in two steps. In the first one, the material is studied to find the best conditions for solution and ageing heat treatments. The result is a solution treatment at 1250?C for 5 h followed by aging at 980?C for 20 h. A work made by another student (SILVA, 2011) makes the same with a modification of MAR-M247 in which tantalum is completely substituted for niobium. The best condition for this case is a solution treatment at 1260?C for 8 h and a double aging treatment at 880?C for 5 h and 780?C for 20 h. At the second part of the work, both the materials are tested under creep conditions at 850?C with 370, 390, 410 and 430 MPa. The conventional superalloy shows the highest values for creep strength and the modified superalloy shows the highest ductility. Fracture surfaces for 390 and 430 MPa showed brittle carbides with \"chinese script\" morphology. Conversely, holes are present on all four materials what shall mean that its nucleation and growth was the most probably fracture path.

A necessidade de trabalhos em altas temperaturas exige o desenvolvimento de materiais com elevada resistência química e mecânica em temperaturas que podem chegar próximas ao seu ponto de fusão. Em especial, os materiais empregados devem apresentar bom comportamento em fluência, de modo a suportar a combinação de altas tensões e altas temperaturas com o mínimo de deformação. O presente trabalho visa caracterizar a superliga MAR-M247, fornecida pela empresa Açotécnica, em condições de fluência para a produção de rotores empregados em turbocompressores automotivos. Os trabalhos são divididos em duas etapas. Na primeira estuda-se a melhor combinação de tratamentos térmicos de solubilização e envelhecimento, chegando à condição de solubilização por 5 horas a 1250?C e envelhecimento por 20 horas a 980?C. Um trabalho de outro aluno (SILVA, 2011) realiza o mesmo estudo para uma variação da superliga MAR-M247 em que o tântalo é totalmente substituído por nióbio. Neste caso, a melhor condição de tratamento é solubilização a 1260?C por 8 h seguida de envelhecimento duplo por 5 h a 880?C e 20 h a 780?C. Na segunda etapa, os materiais dos dois trabalhos, nas melhores condições de tratamento para cada um, são testados em condições de fluência a 850?C a 370, 390, 410 e 430 MPa. A superliga convencional apresenta os maiores valores de vida em fluência enquanto a modificada apresenta os maiores valores de ductilidade. A análise de fratura dos materiais ensaiados a 390 e 430 MPa mostra a presença massiva de carbonetos em toda a extensão da microestrutura, apresentando, em muitos casos, uma morfologia de \"escrita chinesa\". Apesar disso, todas as amostras apresentam grande quantidade de vazios, indicando que sua nucleação e crescimento são os responsáveis pela fratura do material. / The needing for high temperature work claim for new materials capable of maintain high strength and good corrosion resistance at temperatures that could reach values near their melting point. Such materials must be creep resistant to withstand high levels of tension and temperature. The aim of this work is the characterization of MAR-M247 under creep conditions for the production of automotive turbocharger rotors made by Açotécnica. The work is split in two steps. In the first one, the material is studied to find the best conditions for solution and ageing heat treatments. The result is a solution treatment at 1250?C for 5 h followed by aging at 980?C for 20 h. A work made by another student (SILVA, 2011) makes the same with a modification of MAR-M247 in which tantalum is completely substituted for niobium. The best condition for this case is a solution treatment at 1260?C for 8 h and a double aging treatment at 880?C for 5 h and 780?C for 20 h. At the second part of the work, both the materials are tested under creep conditions at 850?C with 370, 390, 410 and 430 MPa. The conventional superalloy shows the highest values for creep strength and the modified superalloy shows the highest ductility. Fracture surfaces for 390 and 430 MPa showed brittle carbides with \"chinese script\" morphology. Conversely, holes are present on all four materials what shall mean that its nucleation and growth was the most probably fracture path.

A proposta da modificação química da superliga MAR-M247 através da substituição do Ta pelo Nb (em átomos) foi baseada nas seguintes informações: (1) O Nb desempenha funções muita parecidas com as do Ta nas superligas à base de Ni, como endurecedor via solução sólida da fase ? e elemento formador de fases secundárias (?? e carbonetos); (2) O Brasil tem as maiores reservas de Nb do mundo e (3) O Nb já é adicionado em diversas classes de superligas à base de Ni - fundidas convencionalmente e solidificadas direcionalmente e monocristalinas. Neste trabalho o objetivo principal foi de avaliar a viabilidade da substituição do Ta pelo Nb na superliga à base de Ni MAR-M247. As amostras da MAR-M247 e da liga modificada - MAR-M247[Nb] utilizadas na caracterização microestrutural foram obtidas por solidificação direcional no forno a vácuo do tipo forno Bridgman (Lab. de Solidificação/FEM-UNICAMP) nas seguintes condições de processamento: v = 5, 10 e 18 cm/h e G = 80°C/cm. As simulações de cálculo termodinâmico utilizando o programa Thermo-Calc foram realizadas com o objetivo de se avaliar se as temperaturas de transformação mudariam com a substituição do Ta pelo Nb. Para avaliação das propriedades mecânicas em alta temperatura e a estabilidade estrutural da superliga MAR-M247[Nb] foram realizados ensaios de fluência a 750 e 850 °C nas tensões de 840, 780 e 440 MPa. A estabilidade microestrutural da MAR-M247[Nb] foi testada por meio de ensaios de oxidação isotérmica a 1000 °C no intervalo de tempo de 30 minutos a 100 h. A substituição do Ta pelo Nb promoveu mudanças significativas principalmente nas temperaturas de formação do eutético ?/??, solvus - ?? e de fusão incipiente. As microestruturas das ligas após os experimentos de solidificação direcional a v = 5, 10 e 18 cm/h eram constituídas por dendritas da fase gama - ? e precipitados coerentes da fase gama linha - ?? (morfologia cuboidal). Na região interdendrítica da MAR-M247 e MAR-M247[Nb] solidificadas a v = 5 e 10 cm/h foram encontrados os eutéticos ?/?? e ?/Ni5(Hf,Zr). Na v = 18 cm/h a região interdendrítica era constituída apenas do eutético ?/??. A exposição a 1250 °C por 15 e 30 dias promoveu a decomposição total e a re-precipitação de carbonetos do tipo MC. No entanto, devido à contaminação por oxigênio e nitrogênio durante os tratamento térmicos, não foi atingido o equilíbrio termodinâmico em decorrência de mudanças das composições dos carbonetos MC. Nos ensaios de fluência a 750 °C, os tempos de ruptura foram de 49 h para MAR-M247 e de 39,4 h para MAR-M247[Nb] apesar dos elevados valores das tensões terem sido superestimados. A 850 °C o tempo de ruptura da MAR-M247[Nb] (trup = 359 horas) foi reduzido em 32 % em relação ao valor observado para MAR-M247 (trup = 476 horas). Os resultados dos ensaios de oxidação a 1000 °C da superliga MAR-M247[Nb] mostraram que o período transiente foi de 20 h com ganho de massa expressivo. A partir de 50 h o efeito do descolamento das camadas oxidadas durante o resfriamento das amostras foi significativo e promoveu uma variação de massa importante no intervalo de tempo de 50 a 100 h. Ensaios de oxidação em tempos mais longo deverão ser feitos para determinação da estrutura de formação das camadas e seus respectivos constituintes. / The chemistry modification in the Ni-based superalloy MAR-M247 through the replacing all Ta by Nb was based on in these statements: (1) Nb does the same function in Ni-based superalloys as Ta does, solid solution strenghtening and ?? e carbides element formers, (2) Brazil has the major ores of Nb in the world and (3) Nb has been added in all classes of Ni superalloy conventional casting, columnar and single crystal processed by directional solidification. In this study the main focus was to evaluate the feasibility of replacing Ta by Nb in the Ni - based superalloy MAR-M247. The samples of MAR-M247 and the Nb modified MAR-M247[Nb] were produced by directional solidification in a Bridgman vacuum furnace at the Solidification Research Lab/FEM - UNICAMP) in the following processing conditions: v = 5, 10 and 18 cm/h and G = 80 °C/cm. The thermodynamic simulations using Thermo-Calc program were performed to evaluate whether or not the transformation temperatures would change with the replacing of Ta by Nb. For the evaluation of mechanical properties at high temperature were performed creep rupture tests at 750 and 850 °C under the stress values of 840, 780 and 440 MPa. The isotermal oxidation tests at 1000 °C were done during the time interval of 30 min to 100 h. The replacing of Ta by Nb promoted some changes in eutectic-?/??, ??-solvus and incipient melting temperatures. After the directional solidification experiments at the v = 5, 10 and 18 cm/h the microstructural characterization has shown that for all condition the microstructures were composed by dendrites - ? and ?? - cuboidal precipitates in it. In the interdendritic region was observe the ?/?? and ?/Ni5(Hf,Zr) eutectics for v = 5 and 10 cm/h and only the ?/?? eutectics for v = 18 cm/h. The exposure at 1250 °C for the extended times promoted the formation of fine MC carbides but the equilibrium compositions have not been achieved due to the oxygen and nitrogen contamination. In the creep rupture tests at 750 °C the MAR-M247[Nb] have shown more shorter lifetime than the MAR-M247 even with overestimated tensile stress. At 850 °C the lifetime for MAR-M247[Nb] (trup = 359 h) was reduced by 32 % compared to the MAR-M247 (trup = 476 h). It was discussed that the changes in the composition of the ? phase induced Ta by Nb replacing which would led to the weakness of matrix in the MAR-M247[Nb]. The samples were oxidized at 1000 °C showed 20 h to the transient period and significant weight gain in that time. However at the extended period the weight gain had changed significantly and was precluded to predict the structure formation of oxides layer properly.

A proposta da modificação química da superliga MAR-M247 através da substituição do Ta pelo Nb (em átomos) foi baseada nas seguintes informações: (1) O Nb desempenha funções muita parecidas com as do Ta nas superligas à base de Ni, como endurecedor via solução sólida da fase ? e elemento formador de fases secundárias (?? e carbonetos); (2) O Brasil tem as maiores reservas de Nb do mundo e (3) O Nb já é adicionado em diversas classes de superligas à base de Ni - fundidas convencionalmente e solidificadas direcionalmente e monocristalinas. Neste trabalho o objetivo principal foi de avaliar a viabilidade da substituição do Ta pelo Nb na superliga à base de Ni MAR-M247. As amostras da MAR-M247 e da liga modificada - MAR-M247[Nb] utilizadas na caracterização microestrutural foram obtidas por solidificação direcional no forno a vácuo do tipo forno Bridgman (Lab. de Solidificação/FEM-UNICAMP) nas seguintes condições de processamento: v = 5, 10 e 18 cm/h e G = 80°C/cm. As simulações de cálculo termodinâmico utilizando o programa Thermo-Calc foram realizadas com o objetivo de se avaliar se as temperaturas de transformação mudariam com a substituição do Ta pelo Nb. Para avaliação das propriedades mecânicas em alta temperatura e a estabilidade estrutural da superliga MAR-M247[Nb] foram realizados ensaios de fluência a 750 e 850 °C nas tensões de 840, 780 e 440 MPa. A estabilidade microestrutural da MAR-M247[Nb] foi testada por meio de ensaios de oxidação isotérmica a 1000 °C no intervalo de tempo de 30 minutos a 100 h. A substituição do Ta pelo Nb promoveu mudanças significativas principalmente nas temperaturas de formação do eutético ?/??, solvus - ?? e de fusão incipiente. As microestruturas das ligas após os experimentos de solidificação direcional a v = 5, 10 e 18 cm/h eram constituídas por dendritas da fase gama - ? e precipitados coerentes da fase gama linha - ?? (morfologia cuboidal). Na região interdendrítica da MAR-M247 e MAR-M247[Nb] solidificadas a v = 5 e 10 cm/h foram encontrados os eutéticos ?/?? e ?/Ni5(Hf,Zr). Na v = 18 cm/h a região interdendrítica era constituída apenas do eutético ?/??. A exposição a 1250 °C por 15 e 30 dias promoveu a decomposição total e a re-precipitação de carbonetos do tipo MC. No entanto, devido à contaminação por oxigênio e nitrogênio durante os tratamento térmicos, não foi atingido o equilíbrio termodinâmico em decorrência de mudanças das composições dos carbonetos MC. Nos ensaios de fluência a 750 °C, os tempos de ruptura foram de 49 h para MAR-M247 e de 39,4 h para MAR-M247[Nb] apesar dos elevados valores das tensões terem sido superestimados. A 850 °C o tempo de ruptura da MAR-M247[Nb] (trup = 359 horas) foi reduzido em 32 % em relação ao valor observado para MAR-M247 (trup = 476 horas). Os resultados dos ensaios de oxidação a 1000 °C da superliga MAR-M247[Nb] mostraram que o período transiente foi de 20 h com ganho de massa expressivo. A partir de 50 h o efeito do descolamento das camadas oxidadas durante o resfriamento das amostras foi significativo e promoveu uma variação de massa importante no intervalo de tempo de 50 a 100 h. Ensaios de oxidação em tempos mais longo deverão ser feitos para determinação da estrutura de formação das camadas e seus respectivos constituintes. / The chemistry modification in the Ni-based superalloy MAR-M247 through the replacing all Ta by Nb was based on in these statements: (1) Nb does the same function in Ni-based superalloys as Ta does, solid solution strenghtening and ?? e carbides element formers, (2) Brazil has the major ores of Nb in the world and (3) Nb has been added in all classes of Ni superalloy conventional casting, columnar and single crystal processed by directional solidification. In this study the main focus was to evaluate the feasibility of replacing Ta by Nb in the Ni - based superalloy MAR-M247. The samples of MAR-M247 and the Nb modified MAR-M247[Nb] were produced by directional solidification in a Bridgman vacuum furnace at the Solidification Research Lab/FEM - UNICAMP) in the following processing conditions: v = 5, 10 and 18 cm/h and G = 80 °C/cm. The thermodynamic simulations using Thermo-Calc program were performed to evaluate whether or not the transformation temperatures would change with the replacing of Ta by Nb. For the evaluation of mechanical properties at high temperature were performed creep rupture tests at 750 and 850 °C under the stress values of 840, 780 and 440 MPa. The isotermal oxidation tests at 1000 °C were done during the time interval of 30 min to 100 h. The replacing of Ta by Nb promoted some changes in eutectic-?/??, ??-solvus and incipient melting temperatures. After the directional solidification experiments at the v = 5, 10 and 18 cm/h the microstructural characterization has shown that for all condition the microstructures were composed by dendrites - ? and ?? - cuboidal precipitates in it. In the interdendritic region was observe the ?/?? and ?/Ni5(Hf,Zr) eutectics for v = 5 and 10 cm/h and only the ?/?? eutectics for v = 18 cm/h. The exposure at 1250 °C for the extended times promoted the formation of fine MC carbides but the equilibrium compositions have not been achieved due to the oxygen and nitrogen contamination. In the creep rupture tests at 750 °C the MAR-M247[Nb] have shown more shorter lifetime than the MAR-M247 even with overestimated tensile stress. At 850 °C the lifetime for MAR-M247[Nb] (trup = 359 h) was reduced by 32 % compared to the MAR-M247 (trup = 476 h). It was discussed that the changes in the composition of the ? phase induced Ta by Nb replacing which would led to the weakness of matrix in the MAR-M247[Nb]. The samples were oxidized at 1000 °C showed 20 h to the transient period and significant weight gain in that time. However at the extended period the weight gain had changed significantly and was precluded to predict the structure formation of oxides layer properly.

Yttria-stabilized zirconia-based thermal barrier coating systems are the most widely used commercial coatings in the industry, with practical applications in aircraft engines and land-based power turbines. The purpose of thermal barriers is primarily to protect the substrate from high temperatures and also to increase its oxidation resistance. Currently, concerning the relatively frequent volcanic eruptions and increasing air traffic intensity in desert areas, increased attention is being paid to the development of new thermal and environmental coatings that will withstand the so-called CMAS attack and still successfully meeting the strictest requirements of the aerospace industry. Two newly developed experimental coatings consisting of three successive layers have been developed for this work. The upper two layers are thermal insulating ceramic coatings, where two different uppermost coatings were deposited. The first uppermost layer of the coating is a mixture of mullite and hexacelsian in a ratio of 70/30 wt. %. The second upper most type of coating consists of Al6Si2O13 + MgAl2O4 + BaCO3 in a ratio of 6:3:1 wt. %. The interlayer is made of the commercially utilized yttria-stabilized zirconia. The metallic CoNiCrAlY coating, which is directly deposited on the nickel-based superalloy MAR-M247, fulfils a compensatory function between the mechanical properties of the nickel superalloy and the ceramic coating. The thermal and environmental barrier system was deposited using air plasma spraying (APS) technology. The main objective of this work was to evaluate the effect of the newly developed thermal and environmental barrier coating, which has a high potential for the protection of component surfaces in an aggressive environment, on isothermical and thermomechanical fatigue behaviour of nickel-based superalloy MAR-M247. Low cycle fatigue tests were performed in strain control mode with constant strain amplitude on both uncoated and TEBC coated superalloy. Fatigue hardening/softening curves, cyclic stress-strain curves and fatigue life curves in the representation of total strain amplitude, plastic strain amplitude and stress amplitude on the number of cycles to failure were obtained. Microstructural analysis of MAR-M247 superalloy and a newly developed experimental coating was performed in a scanning electron microscope. The fatigue crack initiation sites were identified and the process of fatigue crack propagation was described. The dislocation arrangement after fatigue loading of MAR-M247 was investigated in a transmission electron microscope. The findings of isothermical and thermomechanical low cycle fatigue behaviour of uncoated and TEBC coated MAR-M247 superalloy and identification of damage mechanisms presented in this dissertation will improve the estimation of safe-life that is particularly relevant to aircraft engines components.

No description available.

Scanning Laser Epitaxy (SLE) is a new layer-by-layer additive manufacturing process being developed in the Direct Digital Manufacturing Laboratory at Georgia Tech. SLE allows for the fabrication of three-dimensional objects with specified microstructure through the controlled melting and re-solidification of a metal powder placed atop a base substrate. This dissertation discusses the work done to date on assessing the feasibility of using SLE to both repair single crystal (SX) turbine airfoils and manufacture functionally graded turbine components. Current processes such as selective laser melting (SLM) are not able to create structures with defined microstructure and often have issues with warping of underlying layers due to the high temperature gradients present when scanning a high power laser beam. Additionally, other methods of repair and buildup have typically been plagued by crack formation, equiaxed grains, stray grains, and grain multiplication that can occur when dendrite arms are separated from their main dendrites due to remelting. In this work, it is shown that the SLE process is capable of creating fully dense, crack-free equiaxed, directionally-solidified, and SX structures. The SLE process, though, is found to be currently constrained by the cumbersome method of choosing proper parameters and a relative lack of repeatability. Therefore, it is hypothesized that a real-time feedback control scheme based upon a robust offline model will be necessary both to create specified defect-free microstructures and to improve the repeatability of the process enough to allow for multi-layer growth. The proposed control schemes are based upon temperature data feedback provided at high frame rate by a thermal imaging camera. This data is used in both PID and model reference adaptive control (MRAC) schemes and drives the melt pool temperature during processing towards a reference melt pool temperature that has been found to give a desired microstructure in the robust offline model of the process. The real-time control schemes will enable the ground breaking capabilities of the SLE process to create engine-ready net shape turbine components from raw powder material.

Um die Leistung und Lebensdauer von energietechnischen Komponenten weiter zu steigern, sind höhere Leistungen, Leistungsdichten sowie Prozesswirkungsgrade zentrale Bestandteile künftiger Entwicklungen. Mit steigernden Leistungsdichten erhöhen sich auch stetig die Belastungen der einzelnen Komponenten. Zusammen mit neuen Werkstoffen und technologischem Fortschritt, wie beispielsweise verbesserten Kühltechnologien oder strömungstechnischen Optimierungen ermöglicht auch eine verbesserte Kenntnis der Belastungsbedingungen und des Schädigungsverhaltens höhere Leistungen und Leistungsdichten. Aktuelle Gasturbinen und oft auch Kraftwerkskomponenten unterliegen zusätzlich zu den mechanischen und zeitlich variablen thermischen Beanspruchungen auch großen örtlichen thermischen Gradienten, die die Lebensdauer der Komponenten stark beeinflussen. Diese thermischen Gradienten induzieren zum einen zusätzliche Beanspruchungen und die örtlich variablen Temperaturfelder führen zum anderen zu stark variierenden Werkstofffestigkeiten. In dieser Arbeit wird ein Prüfstand zur realistischen Prüfung eines typischen Gasturbinenschaufelmaterials Mar-M247 entwickelt und mit diesem eine systematische experimentelle Untersuchung des Einflusses thermischer Gradienten auf die niederzyklische Ermüdungsfestigkeit unter erhöhten Temperaturen durchgeführt. Im weiteren Teil der Arbeit wird ein visko-elasto-plastisches Materialmodell weiterentwickelt, um die lokal unsymmetrische Beanspruchung der Proben unter zyklischer Last realistisch abbilden zu können. Mit Hilfe von Experimenten aus der Literatur werden dabei zunächst die Grenzen und Möglichkeiten des Modells diskutiert, um es dann auf den konkreten Werkstoff anzupassen. Der wesentliche Vorteil des entwickelten Modells liegt in der verbesserten Beschreibung des zyklischen Kriechens und zyklischen Relaxierens (Ratcheting) insbesondere unter einachsiger Beanspruchung und in der nachträglichen Anpassungsmöglichkeit des spezifischen Ratchetingterms nach der Anpassung aller anderen Materialparameter. Die Analyse der experimentell ermittelten Lebensdauern erfolgt sowohl mit ingenieurmäßigen Methoden basierend auf der spannungsabhängigen Lebensdauerbeschreibung nach Basquinund Wöhler als auch mittels eines lokalen bruchmechanischen Ansatzes, der es ermöglicht,sowohl die Rissinitiierung als auch den Rissfortschritt unter variabler Temperatur und kombinierter Kriech- und Ermüdungsbeanspruchung zu beschreiben. Das Material- und Lebensdauermodell werden zusammen im letzten Teil der Arbeit eingesetzt, um das Verformungs- und Lebensdauerverhalten der untersuchten Proben zu berechnenund es kann gezeigt werden, dass sich die Versuche mit sehr guter Qualität wiedergeben lassen.:Versicherung i Abstract iii Kurzfassung v List of abbreviations and symbols xi 1 Introduction 1 2 Objective 5 3 State of the art 7 3.1 Thermal and mechanical loading of gas turbine components . . . . . . . . . . 7 3.2 Material characterisation of nickel-based superalloys . . . . . . . . . . . . . . 9 3.3 Deformation modelling based on constitutive material laws . . . . . . . . . . 13 3.3.1 Ramberg-Osgood material law . . . . . . . . . . . . . . . . . . . . . . 13 3.3.2 Strain and stress tensor . . . . . . . . . . . . . . . . . . . . . . . . . . 14 3.3.3 Thermodynamic principles . . . . . . . . . . . . . . . . . . . . . . . . 14 3.4 Elasto-visco-plastic material models . . . . . . . . . . . . . . . . . . . . . . . 15 3.4.1 Isotropic hardening . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 3.4.2 Kinematic hardening . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 3.4.3 Kinematic hardening for improved simulation of ratcheting . . . . . . 18 3.4.4 Viscosity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 3.5 Failure at elevated temperatures . . . . . . . . . . . . . . . . . . . . . . . . . 22 3.5.1 Fundamental fatigue life models . . . . . . . . . . . . . . . . . . . . . 24 3.5.2 Creep . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 3.5.3 Crack growth models for fatigue loading . . . . . . . . . . . . . . . . . 28 3.5.4 Creep crack growth based on C(t) and C ∗ . . . . . . . . . . . . . . . . 33 3.5.5 Temperature dependency and normalization methods . . . . . . . . . 35 3.5.6 Lifetime under temperature variation . . . . . . . . . . . . . . . . . . . 37 3.5.7 Influence of mean stresses on lifetime . . . . . . . . . . . . . . . . . . . 38 3.5.8 Influence of oxidation on failure at elevated temperatures . . . . . . . 42 3.5.9 Constitutive damage and crack growth models . . . . . . . . . . . . . 45 3.6 Experimental methods for the generation of large homogeneously distributed heat flux densities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 3.6.1 Resistance heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51 3.6.2 Inductive heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 3.6.3 Convective heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53 3.6.4 Laser based heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 3.6.5 Radiation heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 3.7 Conclusion on the state of the art . . . . . . . . . . . . . . . . . . . . . . . . . 56 4 Development of a test system for cyclic fatigue tests under homogeneous surface temperature conditions 59 4.1 Boundary conditions for the development . . . . . . . . . . . . . . . . . . . . 59 4.2 Concept for a test system with a new highly focusing heating . . . . . . . . . 60 4.2.1 Simulation of heat fluxes of different furnace geometries by ray-tracing 60 4.3 Definition of reflection and transmission coefficient . . . . . . . . . . . . . . . 64 4.3.1 Simulation of the radiation behaviour for the furnace concepts . . . . 66 4.4 Analytical calculation of heat transfer inside the hollow specimen . . . . . . . 71 4.5 Finite element calculation of temperature distribution in the specimen wall . 73 4.6 Design and evaluation of the specimen internal cooling system . . . . . . . . . 75 4.6.1 Installation of heating and development of the load train . . . . . . . 81 5 Experimental investigation 85 5.1 Measurement of surface temperatures and thermal gradients . . . . . . . . . . 87 5.1.1 Measurement of surface temperature . . . . . . . . . . . . . . . . . . . 87 5.1.2 Axial surface temperature distribution . . . . . . . . . . . . . . . . . . 90 5.1.3 Measurement of thermal gradients across specimen wall . . . . . . . . 92 5.2 Results of isothermal ratcheting tests . . . . . . . . . . . . . . . . . . . . . . . 96 5.3 Deformation behaviour of cyclic tests with superimposed thermal gradients . 98 5.3.1 Variation of mean strain and mean stress . . . . . . . . . . . . . . . . 98 5.4 Termination criteria for the tests . . . . . . . . . . . . . . . . . . . . . . . . . 100 5.4.1 Measurement of modulus of elasticity . . . . . . . . . . . . . . . . . . 101 5.5 Low cycle fatigue life of Mar-M247 with and without superimposed thermal gradient . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104 5.6 Results of hollow cylindrical specimen testing with thermal gradients . . . . . 108 6 Microstructural investigation 113 7 Deformation modeling with improved ratcheting simulation based on small scale strain theory 123 7.1 Modeling of ratcheting behaviour of Mar-M247 . . . . . . . . . . . . . . . . 123 7.1.1 Improvement of uniaxial ratcheting description for the Armstrong- Frederick-model . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 124 7.1.2 Evaluation of the proposed model for multiaxiality . . . . . . . . . . . 129 7.2 Application of the deformation model on Mar-M247 . . . . . . . . . . . . . 132 8 Lifetime calculation of the nickel-base-superalloy Mar-M247 based on engineering and crack growth methods 139 8.1 Modification of the Krämer crack growth model . . . . . . . . . . . . . . . . 139 8.2 Choice of basic variable for the fatigue crack growth and crack initiation . . . 140 8.3 Oxidation based crack growth model . . . . . . . . . . . . . . . . . . . . . . . 142 8.4 Creep crack growth . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 148 8.5 Creep . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 149 8.6 Fatigue life . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 152 8.6.1 Extension of the Paris crack growth model based on intrinsic defect size152 8.6.2 Crack length independent formulation of J-integral . . . . . . . . . . . 154 8.7 Combined model for comprehensive description of the crack-initiation and -growth . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 156 8.7.1 Comparison to crack growth experiments . . . . . . . . . . . . . . . . 161 8.7.2 Comparison to fatigue experiments . . . . . . . . . . . . . . . . . . . . 164 9 Application of material and crack growth model to the experiments with superimposed thermal gradient 167 9.1 Geometry function for the hollow specimen investigated . . . . . . . . . . . . 167 9.2 Application of the crack growth model on non-isothermal tests . . . . . . . . 170 9.2.1 Calculation of the stress strain field of hollow cylindrical specimen subjected to thermally induced stress gradients with the elasto-visco- plastic model . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 172 9.2.2 Calculated crack growth behaviour under locally non-isothermal con- ditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 176 10 Conclusion and outlook 181 Bibliography 185