Aero-engine Rotating Disk Cavity Flow And Heat Transfer Numerical Simulation

In this paper the flow and heat transfer inside a rotating disc cavity with different inflow and outflow was studied numerically. This cavity is composed of an upstream disc, a downstream disc, a hub and a shroud.The region of computation is made up of 9 sub-regions. In this study a semi-staggered grid arrangements was adopted. Non-uniform grid distributions which are more dense in all the near wall regions were used. The standard k-e turbulence model was employed in the core region of the cavity. Two low Reynolds number turbulence models, single equation model and Launder and Sharma low-Reynolds number k - e model, were used in the near wall regions. Conjugate heat transfer calculation was carried out, with SIMPLE algorithm, studied up on boundary condition and modified pressure adapting algorithm, to give prediction on velocity field inside the disk cavity, the whole temperature field including fluid region and solid region, and heat transfer coefficient at fluid-solid interface. The simulation results indicate,(1) In rotor-stator disc cavity, the secondary flows near rotating disc stronger than which near state disc, keeps temperature of rotating disc lower than state disc's. The circumfluence region near shroud makes for the heat transfer in that region.(2) Axial pre-swirling inflow on high radius holds back the further transmission of heat effectively, to inner part of cavity.(3) In co-revolution disc cavity, heat transfer coefficient which is high on most region of disc surface show that the co-revolution avails the heat transfer on disc surface.(4) There are different predictions on velocity field, temperature field and the heat transfer coefficient when single equation model and Launder and Sharma low-Reynolds number k - e model were used respectively in the near wall regions.