Two-Regime Surge Mechanism in Centrifugal Compressors

Lin, Yun; Niu, Zitian; Zheng, Xinqian

doi:10.2514/1.b38663

Cited by 3 publications

(1 citation statement)

References 23 publications

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“…Emmons et al (1955) and Zheng and Liu (2015) found a special instability process called Two-Regime-Surge in the centrifugal compressor, which has never been reported in axial compressors. Lin (2023) further explained this phenomenon from the perspective of reverse flow and gave a quantitative analysis. The axial and centrifugal combined compressor is also commonly used and plays an important role in industrial facilities.…”

Section: Introductionmentioning

confidence: 99%

Flow physics during durge of an axial-centrifugal compressor

Li,

Kong,

Zou

et al. 2024

J. Glob. Power Propuls. Soc.

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Aerodynamic instability design is one of the crucial elements when designing a compressor. Unstable phenomenon such as surge harms the compressor in both performance and structure integrity. The complex unsteady flow process during instability strongly relates to the compressor design. This paper investigates the transient instability process using URANS on a three-stage-axial and one-stage-centrifugal combined compressor under its off-design conditions. Results show that the compressor suffers two surge patterns. The mild surge happens first, with a higher frequency than the traditional mild surge. Then, with the decrease of valve opening, the deep surge is initiated, and the axial stages work at the peak pressure ratio because the mass flow rate is limited by the choked radial diffuser. Moreover, analysis of aerodynamic loads reveals that IGV and the first rotor have the largest unsteady force among all blade rows. According to the flow field, the rotor root and stator tip suffer the most serious impulse caused by reversed flow during surge conditions.

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Section: Introductionmentioning

confidence: 99%

Flow physics during durge of an axial-centrifugal compressor

Li,

Kong,

Zou

et al. 2024

J. Glob. Power Propuls. Soc.

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Numerical model of predicting surge boundaries in high-speed centrifugal compressors

Zhang

Zhou

2023

Aerospace Science and Technology

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Investigation of the mild surge in an axial–centrifugal compressor

Li,

Wang,

Zeng

et al. 2024

Physics of Fluids

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The performance and structural integrity of compressors are critically impacted by aerodynamic instability. This study examines an unstable phenomenon, known as high-frequency mild surge (HFMS), in axial–centrifugal compressors through an experimental investigation and a low-order model. The results reveal that the pressure signal during HFMS is synchronized along the circumferential and streamwise directions. To elucidate the HFMS mechanism and further explore its influential law, a multi-actuator model is developed, successfully capturing the dynamic instability behavior. As the mass flow decreases, the front axial stage becomes unstable first, while the latter centrifugal stage remains stable with a negative slope near the operating point on the performance curve. The strong pressurization of the centrifugal stage maintains the stability of the entire compression system, increasing the mass flow rate. Subsequently, the pressure ratio of the latter centrifugal stage decreases with increasing mass flow, causing the front axial stage to become unstable again. The axial stage's Helmholtz frequency is consistent with the test HFMS frequency, further proving that it is a local systematic instability dominated by the axial stage. This matching feature is particularly common in combined compressors, making HFMS a typical instability phenomenon in such systems.

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Two-Regime Surge Mechanism in Centrifugal Compressors

Cited by 3 publications

References 23 publications

Flow physics during durge of an axial-centrifugal compressor

Flow physics during durge of an axial-centrifugal compressor

Numerical model of predicting surge boundaries in high-speed centrifugal compressors

Investigation of the mild surge in an axial–centrifugal compressor

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