Aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with upstream generic rim seal cavity
نویسندگان
چکیده
In turbine disk cavity, rim seals are fitted between the stator and its adjacent rotor disk. A coolant air injected through cavity to prevent ingress of mainstream hot gases. The purpose this paper is investigate numerically effect upstream purge flow on aero thermal performances a high pressure rotor. investigations conducted generic seal inspired from realistic turbofan engine. Four fractions (PF) equal 0.2%, 0.5%, 1.0% 1.5% considered. simulations done by solving three-dimensional Reynolds averaged Navier-Stokes energy transport equations. results include PF cooling effectiveness, sealing secondary flows with losses heat transfer behavior, within across passage. low 0.2% provided moderate effectiveness minimum losses. gave best maximum medium supplied compromise aerodynamic design needs good efficiencies tolerable level
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ژورنال
عنوان ژورنال: Propulsion and Power Research
سال: 2021
ISSN: ['2212-540X']
DOI: https://doi.org/10.1016/j.jppr.2021.11.003