Abstract
A single stage ultra micro centrifugal compressor constituting ultra micro gas turbine is required to operate at high rotational speed in order to achieve the pressure ratio which establishes the gas turbine cycle. As a consequence, the aerodynamic losses can be increased by the interaction of a shock wave with the boundary layer on the blade surface. Moreover, the centrifugal force which exceeds the allowable stress of the impeller material can act on the root of blades. On the other hand, the restrictions of processing technology for the downsizing of impeller not only relatively enlarge the size of tip clearance but also make it difficult to shape the impeller with the three-dimensional blade. Therefore, it is important to establish the design technology for the impeller with the two-dimensional blade which possesses the sufficient aerodynamic performance and enough strength to bear the centrifugal force caused by the high rotational speed. In this study, the flow in two types of impeller with the two-dimensional blade which have different meridional configuration was analyzed numerically. The computed results clarified the influence of the meridional configuration on the loss generations in the impeller passage.
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Abbreviations
- C ps :
-
static pressure coefficient
- C pt :
-
total pressure loss coefficient
- LE:
-
leading edge
- MS:
-
mid-span
- p s :
-
static pressure (Pa)
- PS:
-
pressure surface
- Pt :
-
total pressure (Pa)
- SS:
-
suction surface
- TE :
-
trailing edge
- U :
-
circumferential velocity (m/s)
- ρ :
-
density (kg/m3)
- 1:
-
impeller inlet
- 2:
-
impeller outlet
References
Epstein, A. H. et al.: Micro-Heat Engines, Gas turbines and Rocket Engines, -The MIT Micro-engine Project-, AIAA 97-1773, Snowmass Village, Colorado, (1997).
Mizuki, S. et al.: Design and Prototyping of Micro Centrifugal Compressor for Ultra Micro Gas Turbine, Journal of Thermal Science, Vol.14, No.4, pp.308–313, (2005).
Isomura, K. et al.: The performance evaluation of 10 mm micro-centrifugal compressor, 11th Power & Energy Technology Symposium Report No.06-8, JSME, Tokyo, pp.151–154, (2006).
Hirano, T. et al.: Prototyping of Ultra Micro Centrifugal Compressor, -Influence of Meridional Configuration-, Journal of Thermal Science, Vol.20, No.4, pp.312–317, (2011).
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Kaneko, M., Tsujita, H. & Hirano, T. Numerical analysis of flow in ultra micro centrifugal compressor -influence of meridional configuration. J. Therm. Sci. 22, 111–116 (2013). https://doi.org/10.1007/s11630-013-0600-7
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DOI: https://doi.org/10.1007/s11630-013-0600-7