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Please use this identifier to cite or link to this item: https://dspace.lboro.ac.uk/2134/26384

Title: Effects of blade damage on the performance of a transonic axial compressor rotor
Authors: Li, Yan-Ling
Sayma, Abdulnaser
Issue Date: 2012
Publisher: © ASME
Citation: LI, Y. and SAYMA, A., 2012. Effects of blade damage on the performance of a transonic axial compressor rotor. IN: Proceedings of 2012 ASME Turbine Technical Conference and Exposition (Turbo Expo 2012), Copenhagen, Denmark, 11-15 June 2012. Volume 8. Turbomachinery, Parts A, B, and C, pp.2427-2437.
Abstract: Gas turbine axial compressor blades may encounter damage during service for various reasons. Debris from casing or foreign objects may impact blades causing damage near the rotor’s tip. This may result in deterioration of performance and reduction in the surge margin. Ability to assess the effect of damaged blades on the compressor performance and stability is important at both the design stage and in service. The damage to compressor blades breaks the cyclic symmetry of the compressor assembly. Thus computations have to be performed using the whole annulus. Moreover, if rotating stall or surge occurs, the downstream boundary conditions are not known and simulations become difficult. This paper presents an unsteady CFD analysis of compressor performance with tip curl damage. Tip curl damage typically occurs when rotor blades hit a loose casing liner. The computations were performed up to the stall boundary, predicting rotating stall patterns. The aim is to assess the effect of blade damage on stall margin and provide better understanding of the flow behaviour during rotating stall. Computations for the undamaged rotor are also performed for comparison. A transonic axial compressor rotor is used for the time-accurate numerical unsteady flow simulations, with a variable choked nozzle downstream simulating an experimental throttle. One damaged blade was introduced in the rotor assembly and computations were performed at 60% of the design rotational speed. It was found that there is no significant effect on the compressor stall margin due to one damaged blade despite the differences in rotating stall patterns between the undamaged and damaged assemblies.
Version: Published
DOI: 10.1115/GT2012-68324
URI: https://dspace.lboro.ac.uk/2134/26384
Publisher Link: https://doi.org/10.1115/GT2012-68324
ISBN: 9780791844748
0791844749
Appears in Collections:Closed Access (Aeronautical and Automotive Engineering)

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