Experimental measurements were made in a rotating-cavity rig with an axial throughflow of cooling air at the center of the cavity, simulating the conditions that occur between corotating compressor disks of a gas-turbine engine. One of the disks in the rig was heated, and the other rotating surfaces were quasi-adiabatic; the temperature difference between the heated disk and the cooling air was between 40 and 100°C. Tests were conducted for axial Reynolds numbers, , of the cooling air between and , and for rotational Reynolds numbers, , between and . Velocity measurements inside the rotating cavity were made using laser Doppler anemometry, and temperatures and heat flux measurements on the heated disk were made using thermocouples and fluxmeters. The velocity measurements were consistent with a three-dimensional, unsteady, buoyancy-induced flow in which there was a multicell structure comprising one, two, or three pairs of cyclonic and anticyclonic vortices. The core of fluid between the boundary layers on the disks rotated at a slower speed than the disks, as found by other experimenters. At the smaller values of , the radial distribution and magnitude of the local Nusselt numbers, Nu, were consistent with buoyancy-induced flow. At the larger values of , the distribution of Nu changed, and its magnitude increased, suggesting the dominance of the axial throughflow.
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January 2006
Technical Papers
Buoyancy-Induced Flow in a Heated Rotating Cavity
J. Michael Owen,
J. Michael Owen
Department of Mechanical Engineering,
University of Bath
, Bath, UK
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Jonathan Powell
Jonathan Powell
Malvern Instruments Ltd.
, Malvern, UK
Search for other works by this author on:
J. Michael Owen
Department of Mechanical Engineering,
University of Bath
, Bath, UK
Jonathan Powell
Malvern Instruments Ltd.
, Malvern, UKJ. Eng. Gas Turbines Power. Jan 2006, 128(1): 128-134 (7 pages)
Published Online: March 1, 2004
Article history
Received:
October 1, 2003
Revised:
March 1, 2004
Citation
Owen, J. M., and Powell, J. (March 1, 2004). "Buoyancy-Induced Flow in a Heated Rotating Cavity." ASME. J. Eng. Gas Turbines Power. January 2006; 128(1): 128–134. https://doi.org/10.1115/1.2032451
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