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Mahmoodi, M., Pirkandi, J., Jahromi,, M. (2024). Aerodynamic design and optimization of a 10 stage compressor and a 3 stage fan of a low bypass ratio turbofan engine. Electronic and Cyber Defense, 13(1), 131-147.
Mostafa Mahmoodi; Jamasb Pirkandi; Mehdi Jahromi,. "Aerodynamic design and optimization of a 10 stage compressor and a 3 stage fan of a low bypass ratio turbofan engine". Electronic and Cyber Defense, 13, 1, 2024, 131-147.
Mahmoodi, M., Pirkandi, J., Jahromi,, M. (2024). 'Aerodynamic design and optimization of a 10 stage compressor and a 3 stage fan of a low bypass ratio turbofan engine', Electronic and Cyber Defense, 13(1), pp. 131-147.
Mahmoodi, M., Pirkandi, J., Jahromi,, M. Aerodynamic design and optimization of a 10 stage compressor and a 3 stage fan of a low bypass ratio turbofan engine. Electronic and Cyber Defense, 2024; 13(1): 131-147.

Aerodynamic design and optimization of a 10 stage compressor and a 3 stage fan of a low bypass ratio turbofan engine

مکانیک سیالات و آیرودینامیک
Article 10, Volume 13, Issue 1 - Serial Number 33, September 2024, Pages 131-147    PDF (1.94 M)
Document Type: Original Article
Authors
Mostafa Mahmoodi* 1; Jamasb Pirkandi1; Mehdi Jahromi,2
1Associate Professor, Malek Ashtar University of Technology, Tehran, Iran
2Assistant Professor, Malek Ashtar University of Technology, Tehran, Iran
Receive Date: 05 May 2024,  Revise Date: 07 June 2024,  Accept Date: 06 July 2024 
Abstract
 

 





This research focuses on the design and optimization of the compression section of a low bypass ratio turbofan engine. The engine employs a three-stage axial fan and a ten-stage axial compressor for compression. Initially, a commercial software was used to conduct a preliminary design of the engine’s compression section based on engine cycle analysis results. The design’s performance was then modeled using computational fluid dynamics. This allowed for the evaluation of the software’s design performance and the calculation of its deviation percentage from the desired cycle analysis. Subsequently, insights from previous studies were utilized to optimize the initial design. The goal was to achieve the desired flow rate and pressure ratio by minimizing performance deviations. The findings indicate that the commercial software can generate designs that are within 20-30% of the desired design point. Moreover, it is feasible to reduce the design error to less than 20% through optimization. During the optimization process, the fan’s flow rate increased from 74 to 86 kg/s, while the compressor’s flow rate rose from 57 to 59 kg/s. The pressure ratio of the fan also increased from 2.46 to 2.54, and the compressor’s pressure ratio rose from 5.24 to 6.34. By leveraging previous research for optimization, the study managed to enhance the fan’s efficiency by 0.7% and the compressor’s efficiency by 1.5%. This increase was attributed to the reduction in shock waves in the fan and compressor chamber.
Keywords
axial compressor; axial fan; turbofan engine; aerodynamic optimization
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