Effects of Inlet Boundary Layer Thickness on Characteristics of Rotating Stall in Subsonic Axial Compressor

Choi, Minsuk; Chung, Hee Taeg; Oh, Seong Hwan; Ko, Han Young; Baek, Je Hyun

doi:10.2322/tjsass.53.267

Cited by 3 publications

(1 citation statement)

References 21 publications

(20 reference statements)

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“…In the 1980s, Wagner et al (1985aWagner et al ( , 1985b carried out a study on the IBL influence on the interaction effect between the rotor blades of a axial compressor and the passage flow characteristics. Choi et al (2011) studied the influence of the IBL thickness on the rotating stall of a compressor rotor.…”

Section: Fig 1 Comparison Of Two-dimensional Flow Characteristics Bet...mentioning

confidence: 99%

Research on the Influence of Inflow Conditions on the Aerodynamic Performance of a Tandem Cascade

Yang

Liu

Mao

et al. 2022

JAFM

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We perform a thorough numerical analysis of the impact of inflow conditions on the aerodynamic performance of a tandem cascade. In particular, we investigate the effects of the incidence angle and the inlet boundary layer (IBL) thickness on the three-dimensional flow field structure and aerodynamic performance. Our results show that the gap flow strength of the tandem cascade decreases with the increase of incidence angle, and it can effectively reduce the mixing of the wakes of the forward blade (FB) and rear blade (RB). In turn, this prevents the passage vortex (PV) in the RB passage from developing along the circumferential direction. The occurrence of IBL does not modify the effects of the incidence angle on the tandem cascade, however, it reduces the load of the RB and the gap flow strength near the endwall. Under all incidence angles, IBL increases the total pressure loss of the tandem cascade, and decreases the static pressure rise (except for an incidence angle equal to -6°). The maximum loss increment is at 2° incidence angle, and the maximum static pressure rise decrement is at 6° incidence angle (Thick-IBL condition) or 7° incidence angle (Thin-IBL condition). Furthermore, we found that the presence of IBL changes the minimum loss condition from 0° (design condition) to -2° incidence angle. Our results thus indicate that in the practical engineering application of the tandem cascade, the reality that IBL degrades the tandem cascade performance in the full incidence angle range should be considered. And the strong endwall secondary flow effect caused by IBL should be considered in the tandem cascade threedimensional design, so that the tandem cascade two-dimensional performance advantage can be better played.

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Section: Fig 1 Comparison Of Two-dimensional Flow Characteristics Bet...mentioning

confidence: 99%

Research on the Influence of Inflow Conditions on the Aerodynamic Performance of a Tandem Cascade

Yang

Liu

Mao

et al. 2022

JAFM

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Interaction mechanism between the tip leakage flow and inlet boundary layer in a highly loaded compressor cascade based on scale-adaptive simulation

et al. 2022

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Based on the scale-adaptive simulation, the interaction mechanism between the tip leakage flow (TLF) and inlet boundary layer (IBL) and its effects on the tip flow field and aerodynamic performance of the compressor cascade was investigated. The time-averaged results show that the IBL reduces the blade tip load near the leading edge region, decreases the axial momentum of the TLF, and inhibits the development of the TLF to a certain extent. On the other hand, the IBL promotes the coupling of the tip leakage vortex, secondary vortex, and separation vortex and induces breakdown, resulting in a large area of severe flow separation in the corner region, greatly reducing the diffusion capacity and significantly increasing the flow loss in the tip region. The analysis of the unsteady transient flow fields indicates that the unsteady fluctuation in the tip region is mainly caused by the tip leakage vortex and flow separation near the blade trailing edge. The former is suppressed under the influence of the IBL, while the latter is amplified. The high-intensity oscillation due to the breakdown and decomposition of the tip vortex structures plays a critical role in the fluctuation of the cascade performance. By means of proper orthogonal decomposition, it is found that the IBL enhances the fluctuation of small-scale vortex structures related to flow separation and leakage flow, and makes the stability of the tip flow field worse.

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Design and testing of an acoustic-to-flow energy conversion device

Figueroa-Ibrahim

Ross

Bennett

et al. 2023

AIAA AVIATION 2023 Forum

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Effects of Inlet Boundary Layer Thickness on Characteristics of Rotating Stall in Subsonic Axial Compressor

Cited by 3 publications

References 21 publications

Research on the Influence of Inflow Conditions on the Aerodynamic Performance of a Tandem Cascade

Research on the Influence of Inflow Conditions on the Aerodynamic Performance of a Tandem Cascade

Interaction mechanism between the tip leakage flow and inlet boundary layer in a highly loaded compressor cascade based on scale-adaptive simulation

Design and testing of an acoustic-to-flow energy conversion device

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