Endwall blockage in axial compressors
- Allison Advanced Development Co., Indianapolis, IN (United States)
- Khalsa International Industries, Espanola, NM (United States)
- Massachusetts Inst. of Tech., Cambridge, MA (United States). Gas Turbine Lab.
- Cambridge Univ. (United Kingdom). Whittle Lab.
- NASA Lewis Research Center, Cleveland, OH (United States)
- California Inst. of Technology, Pasadena, CA (United States)
This paper presents a new methodology for quantifying compressor endwall blockage and an approach, using this quantification, for defining the links between design parameters, flow conditions, and the growth of blockage due to tip clearance flow. Numerical simulations, measurements in a low-speed compressor, and measurements in a wind tunnel designed to simulate a compressor clearance flow are used to assess the approach. The analysis thus developed allows predictions of endwall blockage associated with variations in tip clearance, blade stagger angle, inlet boundary layer thickness, loading level, loading profile, solidity, and clearance jet total pressure. The estimates provided by this simplified method capture the trends in blockage with changes in design parameters to within 10 percent. More importantly, however, the method provides physical insight into, and thus guidance for control of, the flow features and phenomena responsible for compressor endwall blockage generation.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 679291
- Report Number(s):
- CONF-980615--
- Journal Information:
- Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 3 Vol. 121; ISSN JOTUEI; ISSN 0889-504X
- Country of Publication:
- United States
- Language:
- English
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