The heat transfer characteristics of counter-rotating disks with annulus flow were investigated numerically in this paper, in which the effects of coolant inlet conditions (inlet geometry, turbulent parameter and inlet preswirl) of the cavity were emphasized. The axial Reynolds number of annulus Rew was set to be 5.99×105 and rotating Reynolds number Reϕ was set to be 2.35×105. Two kinds of cooling air inlet, radial inlet from the middle of cavity and axial inlet from one side of cavity, were adopted and investigated. The turbulent parameter and preswil ratio varied from 0.028 to 0.197 and −1.5 to 1.5, respectively. According to the calculation results:a vortex pair that generated by the radial inlet and non-preswirling cooling air is somehow unstable which rendered a complex flow field and wall heat transfer pattern in the cavity. For the influence of pumping effect of rotating disks, preswirling of cooling air led to uneven division of cooling air for two counter-rotating disks in radial cooling air inlet type. More cooling air flows towards the disk with same rotating direction of preswirl cooling air and leads to higher Nu in that wall which was enhanced by the increase of preswirl ratio. Axial cooling air inlet results in a much more stable flow than that with radial inlet. The Nu of the wall that cooling air flow towards was higher than that of the other one and this difference increased with the increase of turbulent parameter λT.
Computational Investigation of Heat Transfer Characteristics of Counter-Rotating Turbine Disks With Annulus
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Liu, D, Luo, X, & Tao, Z. "Computational Investigation of Heat Transfer Characteristics of Counter-Rotating Turbine Disks With Annulus." Proceedings of the ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 5C: Heat Transfer. Montreal, Quebec, Canada. June 15–19, 2015. V05CT15A015. ASME. https://doi.org/10.1115/GT2015-42946
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