Swirl Flow and Heat Transfer in a Rotor-Stator Cavity with Consideration of the Inlet Seal Thermal Deformation Effect
نویسندگان
چکیده
In the typical structure of a turboshaft aero-engine, mass flow cooling air in rotor-stator cavity is controlled by inlet seal labyrinth. This study focused on swirl and heat transfer characteristics with considerations thermal deformation effect. A numerical framework was established integrating conjugate (CHT) analysis structural finite element method (FEM) to clarify two-way aero-thermo-elasto coupling interaction among elastic deformation, leakage flow, transfer. Simulation results showed that actual hot-running clearance non-uniform along axial direction due temperature gradient inconsistent stiffness. Compared cold-built (CC), minimum tip (ANHC) reduced 37–40%, which caused an increase ratio at labyrinth outlet 5.3–6.9%, reduction Nusselt number up 69%. The nominal uniform (NUHC) defined as average clearance. rotating disk under ANHC 81% smaller than NUHC. Finally, compensation proposed coolant decrease metal temperature.
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ژورنال
عنوان ژورنال: Aerospace
سال: 2023
ISSN: ['2226-4310']
DOI: https://doi.org/10.3390/aerospace10020134