With tougher emission standards for heavy duty trucks, good control of the engine is of importance. By taking into consideration the torsional vibrations occurring in the crankshaft, the engine control can be improved. This could be done by implementing a torsion model that would give feedback to the engine control unit to reduce the cycle-to-cycle variations in the cylinders, which is partly due to the torsion in the crankshaft. It is therefore of interest to determine if a torsion model can be developed with a reduced computational complexity and still have sufficient accuracy. In this thesis a model was developed in Matlab for estimation of torsion in the crankshaft of an inline 6 cylinder diesel engine. By applying Newtons second law, the equations of motion that describe the torsional vibrations in the crankshaft were set up. The equations of motion were transformed using modal analysis and with the use of mode superposition it was investigated how reducing the number of vibrational modes in the model, affected the models accuracy in its estimation of torsion. Two model reductions were evaluated where the first three and four vibrational modes were used to calculate the torsional displacement between the flywheel and the cylinders. Using measured pressure curves for a number of operating points of the engineas input to the model, results were produced for different crank angle intervalsshowing deviations between the developed torsion models and a reference models estimation of torsion. Due to the damping approximation used in the model, high initial deviations could be found at certain operating points beforereducing the number of vibrational modes. These initial deviations weregreatest for the first two cylinders. Results from the model reductions showed that using the first three vibrational modes in the torsion model, is sufficient for estimating the torsional displacement between the flywheel and all cylinderswith an accuracy of within 0.1 degrees, with the exception of the first two cylinders for the early and late combustion interval.

Modern turbomachinery design is characterized by a tendency towards thinner, lighter and highly loaded blades, which in turn gives rise to increased sensitivity to flow induced vibration such as flutter. Flutter is a self-excited and self-sustained instability phenomenon that may lead to structural failure due to High Cycle Fatigue (HCF) or material overload. In order to be able to predict potential flutter situations, it is necessary to accurately assess the unsteady aerodynamics during flutter and to understand the physics behind its driving mechanisms. Current numerical tools used for predicting unsteady aerodynamics of vibrating turbomachinery components are capable of modeling the flow field at high level of detail, but may fail in predicting the correct unsteady aerodynamics under certain conditions. Continuous validation of numerical models against experimental data therefore plays significant role in improving the prediction accuracy and reliability of the models.   In flutter investigations, it is common to consider aerodynamically symmetric (tuned) setups. Due to manufacturing tolerances, assembly inaccuracies as well as in-service wear, the aerodynamic properties in a blade row may become asymmetric. Such asymmetries can be observed both in terms of steady as well as unsteady aerodynamic properties, and it is of great interest to understand the effects this may have on the aeroelastic stability of the system.   Under certain conditions vibratory modes of realistic blade profiles tend to be coupled i.e. the contents of a given mode of vibration include displacements perpendicular and parallel to the chord as well as torsion of the profile. Current design trends for compressor blades that are resulting in low aspect ratio blades potentially reduce the frequency spacing between certain modes (i.e. 2F &amp; 1T). Combined modes are also likely to occur in case of the vibration of a bladed disk with a comparatively soft disk and rigid blades or due to tying blades together in sectors (e.g. in turbines).   The present investigation focuses on two areas that are of importance for improving the understanding of aeroelastic behavior of oscillating blade rows. Firstly, aeroelastic properties of combined mode shapes in an oscillating Low Pressure Turbine (LPT) cascade were studied and validity of the mode superposition principle was assessed. Secondly, the effects of aerodynamic mistuning on the aeroelastic properties of the cascade were addressed. The aerodynamic mistuning considered here is caused by blade-to-blade stagger angle variations   The work has been carried out as compound experimental and numerical investigation, where numerical results are validated against test data. On the experimental side a test facility comprising an annular sector of seven free-standing LPT blades is used. The aeroelastic response phenomena were studied in the influence coefficient domain where one of the blades is made to oscillate in three-dimensional pure or combined modes, while the unsteady blade surface pressure is acquired on the oscillating blade itself and on the non-oscillating neighbor blades. On the numerical side, a series of numerical simulations were carried out using a commercial CFD code on a full-scale time-marching 3D viscous model. In accordance with the experimental part the simulations are performed using the influence coefficient approach, with only one blade oscillating.   The results of combined modes studies suggest the validity of combining the aeroelastic properties of two modes over the investigated range of operating parameters. Quality parameters, indicating differences in mean absolute and imaginary values of the unsteady response between combined mode data and superposed data, feature values that are well below measurement accuracy of the setup.   The findings of aerodynamic mistuning investigations indicate that the effect of de-staggering a single blade on steady aerodynamics in the cascade seem to be predominantly an effect of the change in passage throat. The changes in steady aerodynamics are thereby observed on the unsteady aerodynamics where distinctive effects on flow velocity lead to changes in the local unsteady pressure coefficients. In order to assess the overall aeroelastic stability of a randomly mistuned blade row, a Reduced Order Model (ROM) model is introduced, allowing for probabilistic analyses. From the analyses, an effect of destabilization due to aero-asymmetries was observed. However the observed effect was of moderate magnitude. / <p>QC 20130610</p> / Turbokraft

O objetivo deste trabalho é verificar a aplicação do Dynamic Design Analysis Method DDAM na análise de estruturas submetidas a carregamentos de choque. Esse método foi desenvolvido pela Marinha Norte Americana e se propõe a estimar esforços inercias provenientes das respostas de equipamentos de bordo, sejam de navios ou submarinos, a cargas impulsivas, mais precisamente, ondas de choque submarinas. Para a compreensão plena dessa metodologia, foi necessário um estudo sobre vibrações e espectros de resposta, tópicos teóricos que fundamentam esse procedimento. Devido à escassez de informações divulgadas por se tratar de conteúdo militar, foi realizado um estudo de caso para uma estrutura simples, uma viga engastada e seus resultados foram comparados com um prévio trabalho publicado. Com isso, foi possível a aplicação do DDAM em uma estrutura mais complexa como o vaso do reator nuclear do tipo PWR de um submarino, ainda que em um modelo simplificado desse equipamento. No entanto, os resultados mostraram a validade do uso do DDAM na análise estrutural dinâmica de equipamentos de uma maneira qualitativa. / The main purpose of this dissertation is to verify the use of the Dynamic Design Analysis Method DDAM in the study of structures subjected to shock loadings. This method was developed by the U.S. Navy and is intended to estimate inertial forces resultant from the response of shipboard equipment, from surface ships or submarines, due to impulsive loads or, more precisely, underwater pressure shock waves. To fully comprehend this method, it was necessary to acknowledge fundamentals of dynamics of structures like free vibrations, response spectrum analysis correlated topics. And due to lack of public information since it is a military technology, a case study of a cantilever beam was done with its results compared to a previous published paper. Then, the DDAM was applied to a more complex structure a PWR nuclear reactor vase simplified model, in order to show the effectiveness of the method in dynamic structural analysis.

O objetivo deste trabalho é verificar a aplicação do Dynamic Design Analysis Method DDAM na análise de estruturas submetidas a carregamentos de choque. Esse método foi desenvolvido pela Marinha Norte Americana e se propõe a estimar esforços inercias provenientes das respostas de equipamentos de bordo, sejam de navios ou submarinos, a cargas impulsivas, mais precisamente, ondas de choque submarinas. Para a compreensão plena dessa metodologia, foi necessário um estudo sobre vibrações e espectros de resposta, tópicos teóricos que fundamentam esse procedimento. Devido à escassez de informações divulgadas por se tratar de conteúdo militar, foi realizado um estudo de caso para uma estrutura simples, uma viga engastada e seus resultados foram comparados com um prévio trabalho publicado. Com isso, foi possível a aplicação do DDAM em uma estrutura mais complexa como o vaso do reator nuclear do tipo PWR de um submarino, ainda que em um modelo simplificado desse equipamento. No entanto, os resultados mostraram a validade do uso do DDAM na análise estrutural dinâmica de equipamentos de uma maneira qualitativa. / The main purpose of this dissertation is to verify the use of the Dynamic Design Analysis Method DDAM in the study of structures subjected to shock loadings. This method was developed by the U.S. Navy and is intended to estimate inertial forces resultant from the response of shipboard equipment, from surface ships or submarines, due to impulsive loads or, more precisely, underwater pressure shock waves. To fully comprehend this method, it was necessary to acknowledge fundamentals of dynamics of structures like free vibrations, response spectrum analysis correlated topics. And due to lack of public information since it is a military technology, a case study of a cantilever beam was done with its results compared to a previous published paper. Then, the DDAM was applied to a more complex structure a PWR nuclear reactor vase simplified model, in order to show the effectiveness of the method in dynamic structural analysis.