Active Flow Control in a Radial Vaned Diffuser for Surge Margin Improvement: A Multislot Suction Strategy

Marsan, Aurélien; Trébinjac, Isabelle; Moreau, Stéphane; Coste, Sylvain

doi:10.1155/2017/4120862

Cited by 8 publications

(5 citation statements)

References 39 publications

(45 reference statements)

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“…In addition, with the effect of the injection, a decrease was observed in the efficiency and pressure ratio. Marsan et al [13] carried out one of the most detailed numerical suction control study in the literature. In their studies, suction actuators were defined on the hub surface of the diffuser blade and the simulations were conducted by defining 1% of the surge flow rate as suction from 3 actuators.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Suction Flow Control on Centrifugal Compressor with Vaned Diffuser

Çadırcı

2022

Energies

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In this study, the effect of suction flow control on a centrifugal compressor at operation and stall flow rates was investigated using computational fluid dynamics (CFD). The compressor geometry was reconstructed from available open source profile data and the CFD analyses have been performed on this geometry using the appropriate mesh. To validate the CFD results, the compressor performance line was acquired and compared with the experimental results obtained at the design rotational speed. Then, suction flow control was employed at various suction slot positions with different suction flow rates to improve the performance of the compressor at operation and stall flow rates. As a result of the suction flow control trials, 0.85% increase in pressure ratio and 0.8% increase in adiabatic efficiency were achieved while the compressor was running at operation flow rate. The performance improvements corresponding to the stall flow rate of the compressor were 2.5% increase in pressure ratio and 2% increase in adiabatic efficiency.

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Section: Introductionmentioning

confidence: 99%

Investigation of Suction Flow Control on Centrifugal Compressor with Vaned Diffuser

Çadırcı

2022

Energies

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“…Evidence showed that the control method must act upon the flow field within the vaneless space of diffuser to improve stability. Additionally, Marsan 12 proposed a multi‐slot boundary‐layer suction technique on the radial vaned diffuser of a centrifugal compressor, which achieved a remarkable increase in stable operating range by reducing the interaction between the hub‐corner separation vortex and the impeller trailing edge vortex shedding. As noted above, active control methods require additional energy input and need to be equipped with complex configurations.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of centrifugal compressor stability enhancement using vaned diffuser endwall contouring technology

Cui

Qin

Jia

et al. 2022

Energy Science & Engineering

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To improve the stable operating range of centrifugal compressor stage, endwall contouring technology is introduced on the hub-side wall of the vaned diffuser for NASA CC3 centrifugal compressor as a promising technique to redistribute the flow field near the endwall in this paper. The main contents of this paper are listed as follows. First, a specific parameterized endwall contouring guideline is developed based on sinusoidal function and Bézier curve, and three factors are considered, namely, peak height, peak radial position, and frequency coefficient. Then, centrifugal compressor stages with baseline diffuser and contoured endwall diffusers are numerically investigated to reveal the influence of endwall contouring on the stable operating range. Results show that endwall contouring is an effective method to achieve stability enhancement with no evident reduction in stage performance on the design point. CEW13-12 has the most successful combination of endwall contouring parameters, and stall margin is increased by up to 40% for CEW13-12. Finally, the influence mechanism of endwall contouring on the stable operating range is discussed. At the near stall condition, the contouring endwall forces the fluid within the semi vaneless space to deflect toward the suction side to increase the momentum of low-energy fluid in the suction surface boundary layer and reduce the adverse pressure gradient on the suction side, which delay the development of flow separation on the vane leading edge near the shroud side to suppress the onset of rotating stall. At the near choke condition, the contouring endwall has more potential to increase the throat area, resulting in a decrease of throat blockage to improve choke margin. The results show that the endwall contouring technology is a reliable method to achieve stability enhancement of centrifugal compressor stage.

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“…Onesided diffuser clearance showed no negative impact on the operation or loss behavior of the centrifugal compressor, while improving its pressure ratio and efficiency. Marsan et al 12 processed suction slots at different positions along the radial direction of a diffuser; the boundary-layer suction technique improved compressor stage performance and delayed hubcorner separation.…”

Section: Introductionmentioning

confidence: 99%

“…Marsan et al. 12 processed suction slots at different positions along the radial direction of a diffuser; the boundary-layer suction technique improved compressor stage performance and delayed hub-corner separation.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the diffuser throat length effect on a transonic centrifugal compressor

Zhang

Wang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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Vaned diffuser inlet flow uniform is challenging when the impeller is throttled to stall. In this study, we extend the stable operating range of the compressor by improving the uniform flow of the diffuser inlet. First, a numerical investigation of a transonic centrifugal compressor with a vaned diffuser is presented and compared against test data. Then, a new diffuser parameterization method is pro- posed, and the throat feature of a pipe diffuser is successfully applied to parameterized vane diffusers. The influence of the throat length and divergence angle of the diffuser on the performance of the centrifugal compressor is studied via steady and non-linear harmonic simulations. Throat length delays the time of fluid pressurization and accommodates large flow instabilities from upstream—this widens the stall margin but increases mixing loss. Divergence angle affects compressor performance. Stage peak efficiency increases by about 0.58% as the divergence angle increases from 3.79° to 5.79° but drops to about 2.46% as the divergence angle further increases from 5.79° to 11.79°. This is because the boundary layers in the diffuser channel thicken with increasing divergence angle; additionally, the fluid near the hub-pressure side first becomes unstable, then flow separation occurs along the flow direction, which results in a large flow loss. Detailed performance maps of centrifugal compressors with different throat lengths and divergence angles are given to provide a reference for designing transonic centrifugal compressors.

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Active Flow Control in a Radial Vaned Diffuser for Surge Margin Improvement: A Multislot Suction Strategy

Cited by 8 publications

References 39 publications

Investigation of Suction Flow Control on Centrifugal Compressor with Vaned Diffuser

Investigation of Suction Flow Control on Centrifugal Compressor with Vaned Diffuser

Numerical investigation of centrifugal compressor stability enhancement using vaned diffuser endwall contouring technology

Numerical investigation of the diffuser throat length effect on a transonic centrifugal compressor

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