Rolls-Royce Holdings

About: Rolls-Royce Holdings is a company organization based out in Derby, United Kingdom. It is known for research contribution in the topics: Turbine & Gas compressor. The organization has 4027 authors who have published 6305 publications receiving 80517 citations. The organization is also known as: Rolls-Royce Holdings plc.

How to measure the effectiveness of risk management in engineering design projects? Presentation of RMPASS: a new method for assessing risk management performance and the impact of knowledge management—including a few results

Abstract: This paper addresses the issue of assessing the performance of project risk management (RM) and knowledge management (KM) in engineering design projects. RMPASS, a new analysis method, which is easily applicable by practitioners, is presented. It uses not only subjective assessments but also objective project data in a description and an evaluation model. New RM and KM performance indicators are introduced. In a feasibility study, RMPASS was applied to three aerospace design projects. The results show that once a risk was identified, the RM ‘machinery’ worked well. Risk identification was the greatest challenge in the RM process, which can be supported by KM. Irrespective of avoidable problems (β-problems), a limit for risk identification appeared: 20% of the encountered problems could not have been anticipated in advance in the state-of-the-art aerospace new design projects examined (α-problems). This could be the uncharted ground that the company reclaims in new design projects.

Forced Response of Mistuned Bladed Discs in Gas Flow: A Comparative Study of Predictions and Full-Scale Experimental Results

Abstract: An integrated experimental-numerical study of forced response for a mistuned bladed disk has been performed. A full chain for the predictive forced response analysis has been developed including data exchange between the computational fluid dynamics code and a code for the prediction of the nonlinear forced response for a bladed disk. The experimental measurements are performed at a full-scale single stage test rig with excitation by aerodynamic forces from gas flow. The numerical modeling approaches and the test rig setup are discussed. Comparison of experimentally measured and predicted values of blade resonance frequencies and response levels for a mistuned bladed disk without dampers is performed. A good correspondence between frequencies at which individual blades have maximum response levels is achieved. The effects of structural damping and underplatform damper parameters on amplitudes and resonance frequencies of the bladed disk are explored. It is shown that the underplatform damper significantly reduces scatters in values of the individual blade frequencies and maximum forced response levels.