A detailed knowledge of the flow structure and heat transfer within disc cavities is required for designing safe and efficient aero-engine compressors with a useful operating range. This paper presents Laser-Doppler Anemometry (LDA) measurements obtained from the Sussex Multiple Cavity test facility. This facility comprises four heated disc-cavities with a cool bore flow and is intended to emulate the secondary air system flow in an aircraft engine H.P compressor. Measurements were made of the axial and tangential components of velocity over the respective range of Rossby number (Ro), Rotational and Axial Reynolds numbers (Re*ϕ* and Re*z*): 0*.*08≤ *Ro* ≤0*.*65, 7×10^5^ ≤ *Reϕ* ≤2*.*83×10^6^, 2*.*3×10^4^ ≤ *Rez* ≤4*.*8×10^4^, and for the values of the buoyancy parameter (*β*∆T): 0*.*28 ≤ *β*∆*T* ≤ 0*.*46. The results show that the swirl number *Xk \<* 1 at the lower radii up to mid radius (*r/b \<* 0*.*5) and *Xk* approaches solid body rotation at the outer radius of the cavity. Analysis of the frequency spectra indicates the existence of pairs of vortices. The results from an Unsteady Reynolds-Averaged Navier-Stokes (URANS) calculation study are also presented and these are consistent with the experimental data.


Experimental and Computational Investigation of Flow Structure in Buoyancy Dominated Rotating Cavities

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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