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Numerical Modelling of Flow and Heat Transfer in the Rotating Disc Cavities of a Turboprop Engine
Author(s) -
FARAGHER JOHN,
OOI ANDREW
Publication year - 2001
Publication title -
annals of the new york academy of sciences
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.712
H-Index - 248
eISSN - 1749-6632
pISSN - 0077-8923
DOI - 10.1111/j.1749-6632.2001.tb05888.x
Subject(s) - turboprop , mechanics , heat transfer , nusselt number , turbulence , turbine , flow (mathematics) , rotational symmetry , inlet , propeller , physics , mechanical engineering , thermodynamics , engineering , aerospace engineering , marine engineering , reynolds number
A bstract : A numerical analysis of the flow and heat transfer in the cavity between two co‐rotating discs with axial inlet and radial outflow of fluid, a configuration common in gas turbine engines, is described. The results are compared with the experimental data of Northrop and Owen1. The effectiveness of the k ‐ ε turbulence model with the two‐layer zonal model for near‐wall treatment of Chen and Patel2 is tested for this type of flow. Using three‐dimension models it is shown that modelling discrete holes at the outlet as opposed to a continuous slot, which is the approximation inherent in the two‐dimensional axisymmetric model, has little effect on the predicted Nusselt number distribution along the disc surface. Results of a conjugate heat transfer analysis of a spacer in the turbine section of a turboprop engine are then presented.