Measurement of tip-clearance flow in a multistage, axial flow compressor

Journal Article · Mon Apr 01 04:00:00 EST 1996 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2836628· OSTI ID:250806

Foley, A C; Ivey, P C ^[1]

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1. Cranfield Univ., Bedfordshire (United Kingdom). School of Mechanical Engineering

Detailed measurements using pneumatic probe traverses, blade static pressure tappings, and laser anemometry are made in the third stage of a large-scale, low-speed, four-stage, axial flow, research compressor. Inlet conditions show well-ordered ``two-dimensional`` flow from approximately 40 to 85 percent annulus span. Outside of this region, reduced total pressure due to upstream leakage losses and endwall effects results in high incidence to the following blade row. As a result, peak suction surface static pressure moves forward along the blade chord for both the hub and tip of stators and rotors. At the blade tip, however, the peak suction pressure is maintained with chord due to radial flow on the suction surface being entrained into the tip leakage jet. The extent of rotor chord for which this ``entrainment`` occurs increases with increasing rotor tip clearance gap. The leakage jet from both stators and rotors is seen to ``roll up`` into a vortex downstream of their respective blade rows.

• Sponsoring Organization: USDOE
• OSTI ID: 250806
• Report Number(s): CONF-940626--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 2 Vol. 118; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
COMPRESSOR BLADES
GAS COMPRESSORS
LEAKS
PERFORMANCE
VORTEX FLOW