In modern gas turbine engines, up to 20% of the core airflow is bled off from various compressor stages to facilitate internal cooling, bearing chamber, and rim sealing, as well as axial load management. As this secondary airflow makes no direct contribution to engine thrust, there are strong economic incentives to reduce the quantity and quality of offtake air and maximize its effective use. Secondary airflows are commonly bled off via circular drillings in the compressor rotor, thereby augmenting their swirl velocity. This results in the creation of vortices within the rotor cavity and strong radial pressure gradients opposing inflow. In the present work the relative performance of a series of noncircular offtake passages has been assessed using CFD techniques. The results of this work demonstrate the degree of control that may be exercized over swirl uptake, which can be used to suppress the creation of vortices in rotor cavities.
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April 2003
Technical Papers
CFD Optimization of Cooling Air Offtake Passages Within Rotor Cavities
Colin Young,
Colin Young
Rolls-Royce plc, Derby, DE24 8BJ England
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Guy D. Snowsill
Guy D. Snowsill
Rolls-Royce plc, Derby, DE24 8BJ England
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Colin Young
Rolls-Royce plc, Derby, DE24 8BJ England
Guy D. Snowsill
Rolls-Royce plc, Derby, DE24 8BJ England
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Amsterdam, The Netherlands, June 3–6, 2002. Manuscript received by the IGTI January 23, 2002. Paper No. 2002-GT-30480. Review Chair: E. Benvenuti.
J. Turbomach. Apr 2003, 125(2): 380-386 (7 pages)
Published Online: April 23, 2003
Article history
Received:
January 23, 2002
Online:
April 23, 2003
Citation
Young , C., and Snowsill, G. D. (April 23, 2003). "CFD Optimization of Cooling Air Offtake Passages Within Rotor Cavities ." ASME. J. Turbomach. April 2003; 125(2): 380–386. https://doi.org/10.1115/1.1556405
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