Experimental investigation of stepped tip gap effects on the performance of a transonic axial-flow compressor rotor

Journal Article · Wed Jul 01 04:00:00 EDT 1998 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2841743· OSTI ID:290038

Thompson, D W; King, P I ^[1]; Rabe, D C ^[2]

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1. Air Force Inst. of Tech., Wright-Patterson AFB, OH (United States). Dept. of Aeronautics and Astronautics
2. Compressor Research Facility, Wright-Patterson AFB, OH (United States)

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 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.

• Sponsoring Organization: USDOE
• OSTI ID: 290038
• Report Number(s): CONF-970604--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 3 Vol. 120; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION
33 ADVANCED PROPULSION SYSTEMS
ENERGY EFFICIENCY
GAS COMPRESSORS
GAS TURBINE ENGINES
TRANSONIC FLOW