Effects of Double-Side Labyrinth Seals on Aerodynamic Performance in a Transonic Shrouded Turbine Stage

Weihang, Li; Chen, Shaowen; Liu, Hongyan; Zhou, Zhi‐Hua; Wang, Songtao

doi:10.1115/1.4045182

Cited by 6 publications

(1 citation statement)

References 32 publications

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“…Porreca et al, [10][11][12] Rebholz et al, 13 and Liu 14,15 studied shroud reduction on the turbine blade, by comparing the influences of full and partial shroud structure on leakage flow and turbine performance, improved and optimized partial shroud structures were brought up. Li 16 applied four configurations with or without labyrinth seal arranged on casing and rotor blade tip for computational simulations and found that the double-side labyrinth seal achieved the highest turbine stage efficiency. Wasilczuk et al 17 proposed a seal structure with air curtain through slots fully incorporated within the fin of labyrinth seal on the shroud.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigations on leakage performance and flow mechanism of spiral groove seal for shrouded blade in axial turbine

Xiong

Zhu

Wang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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Flow field of shroud leakage flow for a single-stage axial turbine has been investigated in this article. The spiral groove seal (SGS) is adopted for shrouded rotor blade to reduce tip leakage and improve turbine aerodynamic performance. A series of three-dimensional (3D) computational fluid dynamics (CFD) simulations are performed to investigate leakage characteristics and flow mechanism of various configurations with different angle, depth, width, and grooves number of the SGS. The original staggered labyrinth seal (LS) is also calculated for comparison. The results illustrate that small spiral groove angle can create more axial flow resistance; meanwhile, it will increase grooves number existing in the axial direction. Groove depth and tooth width will influence the number, shape, and strength of vortex in the groove. The leakage mass flow can be reduced by 36% and isentropic efficiency of the turbine can be increased by 0.26% when spiral groove angle, depth, and width of the SGS are 1.5°, 1.8 mm, and 0.8 mm, respectively. Overall, the optimal SGS can influence vortex generation and enhance energy dissipation in shroud cavity to reduce the leakage and suppress mixing loss of leakage flow with the main flow to some extent. It can be attributed to the combination of throttling effect and pumping effect of the SGS that realize leakage reduction and efficiency improvement. As a result, the SGS can effectively improve tip leakage flow of shrouded blade in axial turbine.

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Section: Introductionmentioning

confidence: 99%

Numerical investigations on leakage performance and flow mechanism of spiral groove seal for shrouded blade in axial turbine

Xiong

Zhu

Wang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

View full text Add to dashboard Cite

show abstract

A fluidic oscillator seal concept for sealing performance enhancement by controlling the kinetic energy carry-over effect

Gu,

Yang,

Zhang

et al. 2024

Tribology International

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Leakage flow mixing in shrouded axial turbines and its control strategies using casing optimization

Huang,

Zhang,

Wang

et al. 2024

Physics of Fluids

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The geometry of the shroud cavity, which accommodates the rotor shroud leakage flow, is very important due to its impact on the leakage flow path as well as the interaction between the leakage flow and mainstream. The research in this paper numerically investigates the potential for reducing the leakage loss by optimization to the casing. The spatial loss audit and the loss breakdown based on loss mechanisms undertaken in the first part of this study are the foundation to develop promising strategies for minimizing the leakage loss. The profiled casing in the exit cavity effectively deflects the leakage jet into the axial direction when it re-enters the mainstream. The mixing loss is significantly reduced due to the notable decrease in axial velocity disparity of the two streams. On this basis, the exit and inlet cavity are further shaped to both form a step. Reductions in the shroud leakage loss are achieved by alleviating the flow nonuniformity in the exit cavity and reducing the leakage flow rate, respectively. The work in this study contributes to the refinement of control methods for the shroud leakage loss.

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Effects of Double-Side Labyrinth Seals on Aerodynamic Performance in a Transonic Shrouded Turbine Stage

Cited by 6 publications

References 32 publications

Numerical investigations on leakage performance and flow mechanism of spiral groove seal for shrouded blade in axial turbine

Numerical investigations on leakage performance and flow mechanism of spiral groove seal for shrouded blade in axial turbine

A fluidic oscillator seal concept for sealing performance enhancement by controlling the kinetic energy carry-over effect

Leakage flow mixing in shrouded axial turbines and its control strategies using casing optimization

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