CFD Investigation of an Axial Compressor with Casing Treatment for the Enhancement of the Stall Margin

Ahmad, Naseem; Zheng, Qun; Fawzy, Hamza; Lin, Aqaing; Jiang, Bin

doi:10.24200/sci.2021.56486.4742

Cited by 3 publications

(2 citation statements)

References 31 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The results are listed and compared in Table 3. To the authors' acknowledgment, the most commonly used two ways to calculate the stall margin improvement are listed in this paper and represented by formulas (9) [31][32][33] and (10) 34 . The former one takes both the performance variation at the peak efficiency (or design) and the near-stall operating point into consideration, while the latter one concentrates on the near-stall point.…”

Section: Effect Of the Cfcdmentioning

confidence: 99%

Combined application of passive and active boundary layer aspiration in a transonic compressor rotor for shock wave/boundary layer interaction control

Zhou

Zhao

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Shock wave/boundary layer interaction (SWBLI) is one of the key factors that limits the improvement of aerodynamic performance and stability for supersonic/transonic compressors. In this research, a combined flow control device (CFCD) was designed for controlling SWBLI in the NASA transonic compressor Rotor 35. The original flow fields for Rotor 35 were numerically analyzed first. The results show that the SWBLI is severe, resulting in much flow loss and partly leading to the compressor instability. Based on this phenomenon, the CFCD was designed with a novel three-dimensional passive self-recirculation flow channel and an active suction slot. The flow channel is mounted on the rotor blade suction surface to connect the low- and high-pressure regions ahead of and behind the shock, respectively. The effect of the CFCD on the rotor performance and corresponding working mechanism are then researched as well. With the help of CFCD, the rotor-achieved total pressure ratio (TPR) is maximally increased by 3.0%, and the stall margin (SM) is improved by 4.1% as well. But the rotor isentropic efficiency (IE) considering additional energy expenditure caused by active suction flow has the maximum increment at choke point of 0.27% and highest reduction at near-stall point of 0.54%. The working mechanisms of CFCD include two aspects: one is forming a stable and low-entropy generated lambda shock wave and the other one is reducing the magnitude of flow separation. The dominant mechanism varies with the rotor working condition and depends on whether the leading-edge shock moves upstream of the passive bleed slot.

show abstract

Section: Effect Of the Cfcdmentioning

confidence: 99%

Combined application of passive and active boundary layer aspiration in a transonic compressor rotor for shock wave/boundary layer interaction control

Zhou

Zhao

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…They stated that they reduced the deviation angle by using a diffuser with splitter blades for the high-pressure radial compressor and thus increased its performance [28]. Various numerical analysis studies have been carried out to improve the stall margin of the axial compressor [29][30][31].…”

Section: Introductionmentioning

confidence: 99%

Analysis and Optimization of the Performances of the Tandem Blade Radial Compressor Using the CFD

Soylemez,

Behçet,

Parlak

2024

Applied Sciences

View full text Add to dashboard Cite

Centrifugal compressors are frequently used in both military and commercial areas because they can be easily manufactured and reach high-pressure compression ratios. The factor that limits the performance and operating range of compressors is flow instability. Many ideas have been put forward for performance improvement, but tandem blade radial compressors, which do not require an extra air system, have attracted the most interest. In this study, computational fluid dynamics (CFD) analyses were carried out on various parameters of the tandem blade (TB) radial compressor, and an optimization study was carried out to find the best design using a genetic algorithm on a whole operating curve. It was investigated how these parameters affected the efficiency and total pressure ratio between the determined lower and upper limits. The numerical analyses of the optimum design obtained as a result of the iterations were carried out. As a result of the iterations, three optimum designs were obtained and numerical analysis was carried out according to one of them, and then they were compared with the results in the literature. The general agreement of computational fluid dynamics and the literature data served as a validation for the computational approach. The error rates between the numerical analysis results and the experimental results in the literature were calculated for different flow rates and were found to be 1.98% as the highest and 0.35 as the lowest. The work carried out in this article will provide a valuable reference for future advanced tandem blade compressor designs.

show abstract

Aerodynamic performance improvement of the centrifugal compressor employing the elastic deformation theory

Liu,

Fan

2023

J Braz. Soc. Mech. Sci. Eng.

View full text Add to dashboard Cite

CFD Investigation of an Axial Compressor with Casing Treatment for the Enhancement of the Stall Margin

Cited by 3 publications

References 31 publications

Combined application of passive and active boundary layer aspiration in a transonic compressor rotor for shock wave/boundary layer interaction control

Combined application of passive and active boundary layer aspiration in a transonic compressor rotor for shock wave/boundary layer interaction control

Analysis and Optimization of the Performances of the Tandem Blade Radial Compressor Using the CFD

Aerodynamic performance improvement of the centrifugal compressor employing the elastic deformation theory

Contact Info

Product

Resources

About