Evolution of subsonic and supersonic corner vortices in a supersonic cascade

Wang, Ziao; Chang, Juntao; Zhang, Junlong; Yu, Daren

doi:10.1016/j.ast.2019.105509

Cited by 10 publications

(2 citation statements)

References 40 publications

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“…A pressure outlet boundary condition was used for the suction slots. Zhang et al (2019) found that the streamwise vortex is generated at the leading edge of the cowl in the inward-turning inlet, meaning that the grid should be denser near the leading edge of the cowl. The incoming flow parameters of different cases are presented in Table 1.…”

Section: Introduction and Validation Of The Numerical Approachmentioning

confidence: 99%

“…Studies of the three-dimensional inward-turning inlet generally indicate that the streamwise vortex originates from the notch in the V-shaped cowl and the curved profile of the compression surface. LI et al (2021) found that the strong baroclinic effect caused by the V-shaped cowl (Zhang et al, 2019) leads to the streamlines near the cowl moving toward the midspan plane before gradually lifting and mixing with the mainstream to form the streamwise vortex. Huang et al (March Huang et al, 2017) found that the boundary layer flow that developed on the compression surface was deflected and uplifted toward the mainstream under the compression of the curved profile of the inward-turning inlet, resulting in a pair of streamwise vortices.…”

Section: Introductionmentioning

confidence: 99%

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Development and evolution mechanism of streamwise vortex in an inward-turning inlet

Wang,

Xin,

Chen

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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The three-dimensional flows in an inward-turning inlet were numerically investigated at different incoming flow conditions. When the incoming flow conditions change, the shock angle and the shock interaction form of the external compression wave change, and the development of the near-wall low-energy fluid and the streamwise vortex is also affected. The impingement of the shock wave leads to a sharp increase in the vorticity of the low kinetic energy fluid. Under the pressure gradient caused by the shock wave, the high-vorticity fluid migrates from the cowl to the ramp and entrains the mainstream fluid to form a streamwise vortex, for which the velocity gradient ( ∂v/ ∂y + ∂w/ ∂z) along the vortex axis can accurately determine the rotation direction and the Hopf bifurcation position. By considering high Reynolds number flows, the pressure gradient along the vortex axis is developed to estimate the simplified dilation term (velocity gradient) due to its ease of measurement. However, the pressure gradient ( ∂p/ ∂x) along the vortex axis can lead to bias when evaluating the cross-flow state of the streamwise vortex, with the shock wave structure and high-vorticity fluid leading to under- and overestimation, respectively. This study provides a theoretical basis for an accurate determination of the flow state of a streamwise vortex in an inward-turning inlet and thus lays the foundation for effective vortex control.

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Section: Introduction and Validation Of The Numerical Approachmentioning

confidence: 99%