Effect of Casing and Tip Modifications on the Performance of an Axial Flow Stage

This paper is a presentation of a computational study focused on modifications to the rotor blade tip and casing end wall for the purpose of enhancing the performance and increasing the stall margin of a model turbofan stage. Grooves in the casing outboard of the rotor blade tips, as well as a very small ring protruding inward from the casing just upstream of the leading edge and downstream of the trailing edge of the rotor blade constitute the modifications that will be examined. The results will be compared to experiment as well as simulations of the baseline configuration in order to demonstrate the degree of effectiveness of the respective modifications. It is felt that this work serves as a good starting point for further investigations into possible improvements of performance and stability for both fan and compressor stages.

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