The effects of stepped tip gaps and clearance levels on the performance of a transonic axial-flow compressor rotor were experimentally determined. A two-stage compressor with no inlet guide vanes was tested in a modern transonic compressor research facility. The first-stage rotor was unswept and was tested for an optimum tip clearance with variations in stepped gaps machined into the casing near the aft tip region of the rotor. Nine casing geometries were investigated consisting of three step profiles at each of three clearance levels. For small and intermediate clearances, stepped tip gaps were found to improve pressure ratio, efficiency, and flow range for most operating conditions. At 100% design rotor speed, stepped tip gaps produced a doubling of mass flow range with as much as a 2.0% increase in mass flow and a 1.5% improvement in efficiency. This study provides guidelines for engineers to improve compressor performance for an existing design by applying an optimum casing profile.
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ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition
June 2–5, 1997
Orlando, Florida, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7868-2
PROCEEDINGS PAPER
Experimental Investigation of Stepped Tip Gap Effects on the Performance of a Transonic Axial-Flow Compressor Rotor
Donald W. Thompson,
Donald W. Thompson
Air Force Institute of Technology, Wright-Patterson AFB, OH
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Paul I. King,
Paul I. King
Air Force Institute of Technology, Wright-Patterson AFB, OH
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Douglas C. Rabe
Douglas C. Rabe
Wright Laboratories, Wright-Patterson AFB, OH
Search for other works by this author on:
Donald W. Thompson
Air Force Institute of Technology, Wright-Patterson AFB, OH
Paul I. King
Air Force Institute of Technology, Wright-Patterson AFB, OH
Douglas C. Rabe
Wright Laboratories, Wright-Patterson AFB, OH
Paper No:
97-GT-007, V001T03A002; 15 pages
Published Online:
December 24, 2014
Citation
Thompson, DW, King, PI, & Rabe, DC. "Experimental Investigation of Stepped Tip Gap Effects on the Performance of a Transonic Axial-Flow Compressor Rotor." Proceedings of the ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. Orlando, Florida, USA. June 2–5, 1997. V001T03A002. ASME. https://doi.org/10.1115/97-GT-007
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