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Abstract A detailed knowledge of the flow structure and the heat transfer within blade-disc cavities is required for designing safe and efficient aero-engine compressors with a useful operating range. This paper presents the results from temperature field measurements obtained from the Multiple Cavity test facility at the University of Sussex. This emulates part of the secondary air system in an aircraft engine high-pressure compressor. It comprises four externally heated disc-cavities and is supplied by a cool bore flow. The heat transfer is studied with the help of a finite-element method using measured temperatures as boundary conditions. A validated 2D steady-state heat conduction analysis methodology is presented. Results are presented for a range of values of Rossby number, rotational and axial Reynolds numbers and the buoyancy parameter. The curve-fit type that is best suited for the temperature boundary condition specification is established using an independent Ansys APDL based study. The sensitivity of the overall cavity heat transfer to major driving mechanisms has been described. The Monte-Carlo analysis is used to reveal how a ±0.5 K uncertainty in temperature affected the Nu estimation.
Fazeli et al. (Mon,) studied this question.