Aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with upstream generic rim seal cavity

作     者：Zakaria Mansouri 

作者机构：Faculty of EngineeringThe University of NottinghamNottinghamUnited Kingdom ABYLSEN Sciences&Technologies Rhône-AlpesGrenoble38000France 

出 版 物：《Propulsion and Power Research》 (推进与动力（英文）)

年 卷 期：2021年第10卷第4期

页      面：317-331页

核心收录：

学科分类：080704[工学-流体机械及工程] 080103[工学-流体力学] 08[工学] 0807[工学-动力工程及工程热物理] 0801[工学-力学（可授工学、理学学位）] 

基　　金：French National Institute of Applied Sciences INSA Centre Val de Loire 

主　　题：Axial turbine Thermal characteristics Aerodynamic losses Generic cavity Purge flow Rim seal Numerical simulation 

摘      要：In turbine disk cavity,rim seals are fitted between the stator and its adjacent rotor disk.A coolant air injected through the turbine disk cavity to prevent the ingress of mainstream hot *** purpose of this paper is to investigate numerically the effect of the upstream purge flow on the aero and thermal performances of a high pressure turbine *** investigations are conducted on a generic rim seal cavity inspired from a realistic turbofan *** purge fractions(PF)equal to 0.2%,0.5%,1.0%and 1.5%of the mainstream are *** simulations are done by solving the three-dimensional Reynolds averaged Navier-Stokes and energy transport *** results include the effect of the PF on the cooling effectiveness,the sealing effectiveness,the secondary flows with losses and the heat transfer behavior,within the cavity and across the rotor *** low PF of 0.2%provided a low cooling effectiveness,a moderate sealing effectiveness and minimum *** high PF of 1.5%gave a high cooling effectiveness,a best sealing effectiveness and maximum *** medium PF of 1.0%supplied a compromise between the aerodynamic and thermal design needs with good cooling and sealing efficiencies and a tolerable level of losses.