Abstract

Shock control bumps can help to delay and weaken shocks, reducing loss generation and shock-induced separation and delaying stall inception for transonic turbomachinery components. The use of shock control bumps on turbomachinery blades is investigated here for the first time using 3D analysis. The aerodynamic optimisation of a modem research fan blade and a highly loaded compressor blade are carried out using shock control bumps to improve their performance. Both the efficiency and stall margin of transonic fan and compressor blades may be increased through the addition of shock control bumps to the geometry. It is shown how shock induced separation can be delayed and reduced for both cases. A significant efficiency improvement is shown for the compressor blade across its characteristic, and the stall margin of the fan blade is increased by designing bumps that reduce shock-induced separation near to stall. Adjoint surface sensitivities are used to highlight the critical regions of the blade geometries, and it is shown how adding bumps in these regions improves blade performance. Finally, the performance of the optimised geometries at conditions away from where they are designed is analysed in detail.

Highlights

  • MotivationShocks are a major source of loss for transonic fans and compressors

  • Shock control for turbomachinery Relatively little work on designing geometries directly to weaken the shock waves in transonic turbomachinery components can be found in the literature, though it has been known for some time that reducing the pre-shock Mach number of transonic compressors can improve their efficiency [1]

  • This work has demonstrated how shock control bumps can be used to improve the performance of transonic fan/compressor blades

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Summary

Introduction

MotivationShocks are a major source of loss for transonic fans and compressors. They cause entropy generation, boundary layer thickening and shock induced separation. The impact of shock control bumps on both blade efficiency and stall margin is investigated. It is at this design point that Rotor 37 will be optimised, as a reduction in this separation could significantly increase blade efficiency.

Results
Conclusion

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