Abstract
Three blading designs of high pressure ratio axial flow fan with hub/tip ratio of 0.7 were carried out with the use of compressor design technology. The flow coefficient and/or pressure coefficient moved in the range of 0.4 to 0.65 and/or 0.65 to 0.85. In the design computations own secondary losses data were applied. The blading tests proved maximum efficiency over 90% in all variants. The measured values of fan stage pressure coefficient were higher than the theoretical ones at design conditions. It consists in a lower rotor deviation angles in contrast to the design. Therefore some ampirical dependencies were derived.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
Brodersen, S.: Experimentelle Untersuchungen an hochbelasteten Axialventilatoren mit kleinem Nabenverhältnis. Dissertation, TU Braunschweig 1986.
Lieblein, S.: Experimental flow in two dimensional cascades. NASA SP 36 (1986) pp. 183–226.
Cyrus, V.: Aerodynamic Performance of Rear Axial Compressor Stages with Aspect Ratio of 0.75–1.25. Internal Report (in Czech) 1990.
Cyrus, V.: Prediction of Secondary Losses in Axial Compressors. ASME Paper 92-GT-298, Cologne 1992.
Dring, R.P.; Joslyn, H. D. andHardin, L. W.: An Investigation of an Axial Compressor Rotor Aerodynamics. ASME Journal of Eng. for Power (1982) pp. 84–96.
Cyrus, V.: Experimental Study of Three-dimensional Flow in an Axial Compressor Stage. ASME Paper 86-GT-118, Düsseldorf 1986.
Cyrus, V.: The Effect of the Inlet Velocity Profile in the Three-dimensional Flow in a Rear Axial Compressor Stage. ASME Journal of Turbomachinery. Vol. 110 (1988) pp. 434–440.
Author information
Authors and Affiliations
Rights and permissions
About this article
Cite this article
Cyrus, V. Design of axial flow fans with high aerodynamic loading. Forsch Ing-Wes 62, 58–64 (1996). https://doi.org/10.1007/BF02609370
Received:
Issue Date:
DOI: https://doi.org/10.1007/BF02609370