Experimental Investigation of the Flow Mechanisms and the Performance Change of a Highly Loaded Axial Compressor Stage with/without Stator Hub Clearance

Liu, Baojie; Qiu, Ying; An, Guangfeng; Yu, Xin

doi:10.3390/app9235134

Cited by 11 publications

(8 citation statements)

References 29 publications

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“…Compared to uniform gaps and contraction gaps, expansion gaps had a greater weakening effect on leakage flow and were more effective in suppressing leakage vortices. Liu et al 20 explored the flow mechanism of different gaps in cantilever stators. They analyzed the influence of four different gaps: 0%, 0.25%, 0.5%, and 1.0% of the blade height on the aerodynamic performance of the compressor.…”

Section: Introductionmentioning

confidence: 99%

Characteristics of the axial compressor with different stator gaps in compressed air energy storage system

Li,

Zuo,

Zhou

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part A:

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The axial compressor in compressed air energy storage (CAES) system needs to operate stably and efficiently within a wide working range. The stator gap plays a critical role in suppressing corner separation and enhancing blade throughflow. The primary objective of this study is to determine the optimal combination of stator gaps to further expand the stable working range of the compressor while ensuring high efficiency. In this study, the flow characteristics of different stator gaps of the five-stage axial compressor in a specific CAES system are researched numerically. Firstly, the impact of different stator gaps on the aerodynamic performance is analyzed. The stator gap effectively broadens the stable working range of the compressor, with the hub gap exhibiting greater potential for expansion compared to the shroud gap. Subsequently, a comparative analysis is conducted on the internal flow of the third stage stator under near-stall conditions. Different gap leakage forms different vortex structures, and the gap leakage can effectively eliminate the accumulation of low-energy fluid in the corner area, optimize the limit streamlines on the blade suction surface and the temperature distribution. The low-velocity area caused by different stator gaps is also different. Finally, energy loss and energy dissipation with different stator gaps are explored. The gap leakage flow results in high energy loss, and different stator gaps exhibit notable differences in distribution of the high energy loss regions. Different types of stator gaps exhibit consistent high energy dissipation areas, which include the leading-edge stagnation area, boundary layer area on blade surface, and wake area. It is important to note that the high energy loss area does not necessarily coincide with the high energy dissipation area. The combined application of two loss evaluation methods contributes to a more comprehensive investigation of the loss distribution characteristics of the compressor.

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Section: Introductionmentioning

confidence: 99%

Characteristics of the axial compressor with different stator gaps in compressed air energy storage system

Li,

Zuo,

Zhou

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…The radial clearance of the stator has been optimized to the appropriate size to ensure that only traditional hub leakage flow exists in the region. Meanwhile, no corner separation occurs from choke to stall according to the study by Liu et al [30]. The entire stage also contains an inlet guide vane (IGV), which is omitted in this study to reduce calculations.…”

Section: Geometric Parametersmentioning

confidence: 99%

Effect of Rotor-Stator Spacing on Compressor Performance at Variable Operating Conditions

2022

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This paper investigates the effect of rotor-stator spacing and operating conditions on compressor performance and the rotor-stator interaction mechanism. We focus on the interaction between the rotor wake and the stator’s flow field through several unsteady numerical simulations aiming at a transonic compressor stage in the equal radius flow path with two-axial spacing at three operating conditions. The simulation results indicate that the time-averaged efficiency almost declined by 0.6 points due to mixing loss in the spacing ranging from close to far at nominal and low load operating conditions. The deep upstream wake leads to corner separation at high load conditions due to close spacing, imposing a fluctuating efficiency at the frequency where the stator wake near the shroud oscillates, as found by the dominant frequency screening method. Under all conditions, the wake transport can reduce the static pressure on the pressure surface and weaken the hub leakage flow afterward.

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“…Analogous work on blade tip clearance is being carried out for stators. It has shown by Liu et al [24] that, although stators are not rotating components, the phenomena occurring in the area of the blade tip of the stators are the same as those for rotor blades. Experimental testing has shown that clearances smaller than approximately 0.5% of the blade chord is also not optimal for compressor stability.…”

Section: Compressor Researchmentioning

confidence: 99%

Areas of Investigation into Air Intake Systems for the Impact on Compressor Performance Stability in Aircraft Turbine Engines

Wróblewski¹,

Adamczyk²,

Kozakiewicz³

2022

Adv. Sci. Technol. Res. J.

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The high demands placed on aircraft turbine engines necessitate the use of the latest engine compressors which must be increasingly effi cient and more robust due to the increased loads. The key safety issue in this context is to ensure compressor stability over all engine speed ranges and aircraft fl ight regimes. This paper presents selected areas of research into surge and stall of axial compressors used in aircraft turbine engines based on scientifi c publications in recent years. On the basis of the analysed literature the authors defi ned the main research areas into compressor surge, namely: air intake research, compressor research and combined air intake and compressor system research. On the background of the conducted analysis the authors has presented their own areas of research. The aim of this work is to search for an intake-compressor design more passively resistant to stall or surge phenomena without necessity of implementation of complex control systems to prevent compressor stall.

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Experimental Investigation of the Flow Mechanisms and the Performance Change of a Highly Loaded Axial Compressor Stage with/without Stator Hub Clearance

Cited by 11 publications

References 29 publications

Characteristics of the axial compressor with different stator gaps in compressed air energy storage system

Characteristics of the axial compressor with different stator gaps in compressed air energy storage system

Effect of Rotor-Stator Spacing on Compressor Performance at Variable Operating Conditions

Areas of Investigation into Air Intake Systems for the Impact on Compressor Performance Stability in Aircraft Turbine Engines

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