论文信息 - A method for calculating inlet distortion effects on stability of split-flow fans

A method for calculating inlet distortion effects on stability of split-flow fans

This paper presents a methodology for calculating the operability and performance of split-flow fans with inlet distortion. A one-dimensional stage-by-stage model has been developed to include parallel compressor theory. The model is capable of providing a detailed definition of the circumferential and radial flow fields. The low-pressure fan is divided to three radial divisions, near-hub, near-tip, and mid-span. The characteristics of each radial segment are calculated by using fan radial profiles. The stable and unstable operations of a split-flow fan, with and without inlet distortion, have been investigated in this study. For the clean inflow surge was triggered by the core compressor, whereas the fan spoiled sector was found to cause the compression system to surge for the distorted case.

[1] Nicholas A. Cumpsty,et al. Prediction of Compressor Performance in Rotating Stall , 1978 .

[2] R. S. Mazzawy,et al. Multiple Segment Parallel Compressor Model for Circumferential Flow Distortion , 1977 .

[3] E. Greitzer. Review—Axial Compressor Stall Phenomena , 1980 .

[4] Pericles Pilidis,et al. Transient performance for high‐bypass ratio turbofan models , 2000 .

[5] Milt Davis,et al. Stage-by-stage poststall compression system modeling technique , 1991 .

[6] F. Moore,et al. A Theory of Post-Stall Transients in Axial Compression Systems: Part I—Development of Equations , 1986 .

[7] Edward M. Greitzer,et al. Surge and Rotating Stall in Axial Flow Compressors—Part I: Theoretical Compression System Model , 1976 .

[8] P. de Laval,et al. Response of an axial compressor to distorted inlet flow , 1984 .

[9] John D. Denton,et al. Towards long length scale unsteady modelling in turbomachines , 2003 .