Experimental and computational investigation of the tip clearance flow in a transonic axial compressor rotor

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

DOI:https://doi.org/10.1115/1.2836629· OSTI ID:250807

Suder, K L ^[1]; Celestina, M L ^[2]

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1. NASA-Lewis Research Center, Cleveland, OH (United States)
2. Sverdrup Technology Inc., Cleveland, OH (United States). Lewis Research Center Group

Experimental and computational techniques are used to investigate tip clearance flows in a transonic axial compressor rotor at design and part-speed conditions. Laser anemometer data acquired in the endwall region are presented for operating conditions near peak efficiency and near stall at 100 percent design speed and at near peak efficiency at 60 percent design speed. The role of the passage shock/leakage vortex interaction at design speed, the radial influence of the tip clearance flow extends to 20 times the physical tip clearance height. At part speed, in the absence of the shock, the radial extent is only five times the tip clearance height. Both measurements and analysis indicate that under part-speed operating conditions a second vortex, which does not originate from the tip leakage flow, forms in the end-wall region within the blade passage and exits the passage near midpitch. Mixing of the leakage vortex with the primary flow downstream of the rotor at both design and part-speed conditions is also discussed.

• Sponsoring Organization: USDOE
• OSTI ID: 250807
• 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