Mechanisms of oscillating suction in controlling the tip leakage flow in a high-load compressor cascade

Zhang, Botao; Mao, Xiaochen; Liu, Bo; Wang, Hejian; Yang, Zonghao; Chen, Qidong

doi:10.1016/j.ast.2023.108118

Cited by 9 publications

(2 citation statements)

References 47 publications

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“…Building upon the aforementioned studies on bleed effects, numerous investigations [17][18][19][20][21][22][23] have demonstrated that effective control of compressor leakage flow through a well-designed bleed arrangement is crucial for enhancing compressor performance. Therefore, it is of great value to analyze overall performance parameters of the rotor, the distribution of key aerodynamic parameters, and structural changes in the flow field at the blade tip.…”

Section: Introductionmentioning

confidence: 99%

Non-uniform flow characteristics and rotating instability of a transonic high-pressure compressor rotor with cavity bleed

Xu,

Chen,

Gong

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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The presence of bleed in an aero engine’s compressor can significantly impact its flow characteristics and contribute to rotating instability. This study focuses on the impact of a typical cavity bleed structure on the internal flow characteristics of a compressor, specifically its circumferential non-uniformity and aerodynamic stability. A numerical simulation involving multiple flow passages was conducted on the transonic high-pressure rotor of the E3 compressor, considering its typical bleed structure. The study delves deep into the non-uniform flow characteristics and the mechanisms behind their generation in the compressor flow field. Furthermore, the influence of bleed on the rotating instability of the compressor is explored by comparing changes in compressor instability and adiabatic efficiency under uniform and non-uniform flow field conditions. The findings indicate that the axial position of the cavity bleed structure plays a crucial role in influencing key parameters such as rotor stall margin, peak efficiency, and total pressure ratio under near-stall conditions. The circumferential non-uniformity, resulting from the presence of the cavity bleed, intensifies with higher bleed air flow rates. For the upstream bleed configuration applied to the rotor, with a total bleed rate of 5%, the maximum variation in absolute flow angle at the inlet of different rotor channels can reach up to 1°. Additionally, the maximum difference in inlet flow coefficient can reach 0.0392. These findings demonstrate that the non-uniformity caused by the typical bleed structure leads to a loss in stall margin for the rotor when compared to a uniform flow field scheme.

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Section: Introductionmentioning

confidence: 99%

Non-uniform flow characteristics and rotating instability of a transonic high-pressure compressor rotor with cavity bleed

Xu,

Chen,

Gong

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Machines with low system resistance and higher mass flow rates can benefit from the geometric design of the axial fan blade, which has an inline air flow direction. The design and aerodynamic performance of axial fans are influenced by several factors which are diameter ratio (outer diameter / hub diameter), number and shape of the blades [3], the angle of attack of the blades [4], the blade pitch, and fan rotational speed. The performance and efficiency of the fan are also influenced by the angle of twist, which is the most significant design parameter that impacts differential pressure and mass flow rate.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamics performance evaluation for new twist angle design axial fan.

Sangsawangmatum

2024

J. Phys.: Conf. Ser.

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Axial fans are the most efficient air handling machines used in various industries. In contrast to centrifugal fans, axial fan blades rotate through the liquid to transfer their kinetic energy. With an inline air flow direction, the geometric design of the axial fan blade is suitable for machines with low system resistance and higher mass flow rates. Diameter ratio (outer diameter / hub diameter) and fan rotating speed are commonly used to determine design parameters and adjust aerodynamic performance. The differential pressure and mass flow rate of the fans can be significantly impacted by the angle of attack of the blade. The purpose of the research is to discover new methods to enhance the aerodynamic performance of the axial fan. The comparison involves comparing the effects of the twist angle while keeping the tip angle constant. In addition to having a uniform angle of attack, it also has various angles of attack from the hub to the tip. By utilizing Computational Fluid Dynamics (CFD), the three-dimensional velocity and pressure distribution within the control volume will be shown. The numerical solutions for each case are shown along with the velocity vector and pressure distribution.

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Influence of rotor-stator axial clearance on compressor rotating stall characteristics

Zheng

Jiang

2023

Aerospace Science and Technology

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Mechanisms of oscillating suction in controlling the tip leakage flow in a high-load compressor cascade

Cited by 9 publications

References 47 publications

Non-uniform flow characteristics and rotating instability of a transonic high-pressure compressor rotor with cavity bleed

Non-uniform flow characteristics and rotating instability of a transonic high-pressure compressor rotor with cavity bleed

Aerodynamics performance evaluation for new twist angle design axial fan.

Influence of rotor-stator axial clearance on compressor rotating stall characteristics

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