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Investigation of the compressible flow through the tip-section turbine blade cascade with supersonic inlet

Abstract

The contribution deals with the experimental and numerical investigation of compressible flow through the tip-section turbine blade cascade with the blade 54″ long. Experimental investigations by means of optical (interferometry and schlieren method) and pneumatic measurements provide more information about the behaviour and nature of basic phenomena occurring in the profile cascade flow field.

The numerical simulation was carried out by means of the EARSM turbulence model according to Hellsten [5] completed by the bypass transition model with the algebraic equation for the intermittency coefficient proposed by Straka and Příhoda [6] and implemented into the in-house numerical code. The investigation was focused particularly on the effect of shock waves on the shear layer development including the laminar/turbulent transition. Interactions of shock waves with shear layers on both sides of the blade result usually in the transition in attached and/ or separated flow and so to the considerable impact to the flow structure and energy losses in the blade cascade.

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Correspondence to Martin Luxa.

Additional information

The work was supported by the Technology Agency of the Czech Republic under the grant TA03020277 and by the Czech Science Foundation under grant P101/12/ 1271.

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Luxa, M., Příhoda, J., Šimurda, D. et al. Investigation of the compressible flow through the tip-section turbine blade cascade with supersonic inlet. J. Therm. Sci. 25, 138–144 (2016). https://doi.org/10.1007/s11630-016-0844-0

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Keywords

  • long turbine rotor blade
  • supersonic tip section
  • optical methods
  • transition modelling
  • CFD