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Misalignment is probably the main cause for failure of the rotating machinery. Due to misalignment, excessive stresses and vibrations arise in the system which causes failure of different components of rotating system. The present work is therefore taken up to predict the unique vibration spectrum characteristics for diagnosing parallel misalignment at varying operating conditions and for different geometrical parameters. In the present study, the work has been carried out to establish relationship between parallel misalignment and harmonic frequency components of its vibration signature by experimental and numerical method. An innovative experimental set-up with provisions for changing geometrical as well as operational parameters has been developed for the study of parallel misalignment. To set precise predetermined parallel misalignment values the compound slide table with rotating calibrated wheels was used along with the latest laser alignment system.

The reduction of vibration and noise is a major requirement for performance of any vibratory system. Due to legislative pressures in terms of external pass by noise limit of vehicles and customer requirements for better noise and ride comfort in vehicle, NVH attribute has become an important parameter. Major sources for vehicle pass-by noise consist of powertrain, tire and wind. Damping treatment is important to reduce vibration and noise radiation. The passive constrained layer dampening (CLD) treatment can be used to reduce structure-borne noise of vibrating structure using viscoelastic damping material. The performance of the passive constrained layer damping treatment can further be enhanced by new segmentation technique. The concept of segmented CLD is based on edge effect. The efficiency of segmenting a constrained layer damping treatment relies on the fact that a high shear region is created in the viscoelastic layer.

Dimensional optimization has always been a time consuming process, especially for aerodynamic bodies, requiring much tuning of dimensions and testing for each sample. Aerodynamic auxiliaries, especially wings, are design dependent on the primary model attached, as they influence the amount of lift or reduction in drag which is beneficial to the model. In this study CFD analysis is performed to obtain pressure counter of wings. For a wing, the angle of attack is essential in creating proper splits to incoming winds, even under high velocities with larger distances from the separation point. In the case of a group of wings, each wing is then mentioned as a wing element, and each wing is strategically positioned behind the previous wing in terms of its vertical height and its self-angle of attack to create maximum lift. At the same time, its drag remains variable to its shape ultimately maximizing the C L /C D ratio.