Impacts of Inlet Circumferential Distortions on the Aerodynamic Performance of a Transonic Axial Compressor

Yang, Bo; Zhu, Guoming

doi:10.3390/pr11072175

Cited by 1 publication

(1 citation statement)

References 24 publications

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“…With the development of CFD algorithms and computational power, Vahdati [7] and Ghimire [8] used their algorithms to simulate the 3D flow field of the axial compressors, obtaining detailed flow processes and explain some of the flow instability mechanism. 3D CFD plays an important role in analyzing some special cases, such as inlet distortions [9]. Vo [10] also summarized two conditions for blade instability through three-dimensional CFD simulation: the interface between the inlet flow and the tip leakage flow overflows the leading edge of the blade, and the backflow occurs at the trailing edge to the pressure surface of the adjacent blade.…”

Section: Introductionmentioning

confidence: 99%

Surge Process of a High-Speed Axial–Centrifugal Compressor

Li,

Wang,

Zheng

2023

Processes

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The surge is a typical aerodynamic instability phenomenon in the compression system, which can lead to serious consequences such as engine performance degradation and structural damage. A deep understanding of the surge process can support the development of a compressor with a wider operating range. In this paper, an experimental study was carried out and high-responding pressure sensors were used to obtain the aerodynamic instability process and the post-surge characteristics of an axial–centrifugal compressor at design and off-design speeds. The evolution of the flow field and instability behavior before and after the surge were analyzed. The results showed that the inlet temperature change can reflect the aerodynamic instability to some extent, and as the operating condition moves from the choke to surge boundary, the inlet temperature undergoes a sudden increase at a certain condition and further increases with the decrease in mass flow rate. At the design speed, the instability of the combined compressor featured a deep surge with an obvious rotating stall behavior before its inception, and the amplitude of the stall cell was gradually enhanced, finally leading to the surge. At the off-design speed, affected by the stage mismatching, the axial stage mainly worked near the unstable operating condition. Therefore, the compressor successively experiences two modes of mild surge and deep surge, and the rotating stall can also be observed during the surge cycle.

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