A Preliminary Design for Multistage Axial Flow Compressors Part 11: Case study | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 12, Volume 10, 10th International Conference On Aerospace Sciences & Aviation Technology, May 2003, Page 169-184 PDF (2.28 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2013.24418 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| Ahmed F. Abdel Azim1; Ahmed Hamed2; Wael Shehata2 | ||||
| 1Professor and head, Mechanical Power Engineering Dept, Zagazig University. | ||||
| 2Research engineer, Egypt Air co. | ||||
| Abstract | ||||
| The computer package developed for the preliminary design of multistage axial compressor described in part (I) is applied here for the design of compressor of a typical aeroengine.This compressor is in close proximity to compressor in the CF6-60 turbofan engine. For the same design conditions, the calculated compressor has the same number of stages and layout as that of the CF6 engine. Detailed results concerning both aerodynamic and mechanical designs are presented here. | ||||
| Keywords | ||||
| Multistage Axial Compressor; Two Dimensional; hub-to-tip variation; Blade geometry; CF6 turbofan | ||||
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