On the Influence of High Turbulence on the Convective Heat Flux on the High-Pressure Turbine Vane LS89
| Autor: | Emma Croner, Tony Arts, Tânia S. Cação Ferreira |
|---|---|
| Jazyk: | angličtina |
| Rok vydání: | 2019 |
| Předmět: |
Convective heat transfer
lcsh:Mechanical engineering and machinery convective heat transfer measurements Energy Engineering and Power Technology Aerospace Engineering 02 engineering and technology 01 natural sciences 010305 fluids & plasmas symbols.namesake 0203 mechanical engineering 0103 physical sciences lcsh:TJ1-1570 boundary layer transition boundary layer code Physics Turbulence Mechanical Engineering Reynolds number Mechanics Boundary layer 020303 mechanical engineering & transports Turbulence kinetic energy Heat transfer symbols Combustor linear cascade high-pressure turbines elevated turbulence intensity Reynolds-Averaged Navier Stokes (RANS) Freestream |
| Zdroj: | International Journal of Turbomachinery, Propulsion and Power Volume 4 Issue 4 International Journal of Turbomachinery, Propulsion and Power, Vol 4, Iss 4, p 37 (2019) |
| ISSN: | 2504-186X |
| DOI: | 10.3390/ijtpp4040037 |
| Popis: | High-pressure turbine vanes and blades are subjected to a turbulent combustor flow affecting the heat transfer and boundary layer transition, hence, the temperature distribution. The accurate prediction of the temperature distribution is crucial for a reliable design and cooling implementation. Engine-representative measurements are hence mandatory for improving design tools. Recently, convective heat transfer measurements were conducted on a high-pressure turbine inlet guide vane (VKI LS89 airfoil) in the Isentropic Compression Tube (CT-2) facility at the von Karman Institute. This contribution focuses on the effect of high freestream turbulence generated by a new turbulence grid allowing a range of turbulence intensities in excess of 10% with representative length scales of the order of 1&ndash 2 cm. Three cases with varying turbulence levels are discussed in this paper. The different flow conditions are exit isentropic Mach numbers of 0.70&ndash 0.97, Reynolds numbers of 0.53∙× 106 and 1.15∙× 106 and a constant temperature ratio equal to 1.36. The heat transfer distributions along the vane suction side indicate a clear link between boundary layer transition and the stream-wise pressure gradients even at high levels of freestream turbulence intensity. Differences are put in evidence in the dynamics of the transition development. Future developments will focus also on the contribution of the other flow parameters under high turbulence. Heat transfer predictions from the boundary layer code TEXSTAN and Reynolds-Averaged Navier&ndash Stokes code elsA (ensemble logiciel pour la simulation en Aé rodynamique) are additionally compared to the experiments. Inherent difficulties associated with high turbulence modelling are clear from this early numerical work. |
| Databáze: | OpenAIRE |
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