Innovative vortex cooling concept and its application to turbine airfoil trailing edge cooling design

Cheng, Qi; Flannery, Kelly; Saito, Kozo; Downs, J. P.; Soechting, F. O.

doi:10.2514/6.1997-3013

Cited by 12 publications

(4 citation statements)

References 7 publications

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“…Chang and Dhir 6,7 found that vortex cooling heat transfer enhancement was mainly caused by large axial velocity near the wall and high turbulence level. Ligrani et al 8 and Qian et al 9 observed the Go¨rtler vortex pairs in the vortex chamber and confirmed their significant influences on heat transfer improvement. Zhang et al 10 experimentally investigated thermal and friction characteristics in pipes with twisted-tape inserts and axial interrupted ribs.…”

Section: Introductionmentioning

confidence: 77%

Effects of aerodynamic parameters on steam vortex cooling behavior for gas turbine blade leading edge

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part A:

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Three-dimensional Reynolds-averaged Navier-Stokes equations are applied to further explore steam vortex cooling mechanism in gas turbine blade leading edge. Grid independence analysis and turbulence model validation are carried out to determine the proper grid dimension and turbulence model for simulations. Influences of Reynolds number and temperature ratio on steam vortex cooling flow and heat transfer behavior for the blade leading edge are investigated. Heat transfer and friction correlations for steam vortex cooling are achieved on the basis of numerical data. Results show that radial convection is generated due to violent rotational motion and uneven density distribution, contributing to heat transfer enhancement. For the sake of increasing steam velocity, the obvious increase in heat transfer intensity and decrease in friction coefficient are observed with the increasing Reynolds number. When the temperature ratio increases, the heat transfer intensity decreases slightly and the friction coefficient decreases significantly. The thermal performance increases with the increasing Reynolds number and the decreasing temperature ratio. Compared with calculating results, the heat transfer and friction correlations can predict steam vortex cooling characteristics accurately.

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Section: Introductionmentioning

confidence: 77%

Effects of aerodynamic parameters on steam vortex cooling behavior for gas turbine blade leading edge

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…The swirl flow contributes to creating a thin boundary layer and high convective heat transfer coefficient, which was first demonstrated by Kreith et al [19]. Qian et al [20] found that the Görtler vortex pairs of swirl cooling lead to high turbulence and heat dissipation rate, which was also confirmed by the numerical simulations of Du et al [21]. Liu et al [22] investigated the effects of jet nozzle geometrical parameters and flow parameters on swirl cooling's flow and heat transfer characteristics by a blade leading edge model.…”

Section: Introductionmentioning

confidence: 92%

Cooling Characteristic of a Wall Jet for Suppressing Crossflow Effect under Conjugate Heat Transfer Condition

Deng

Feng

2022

Aerospace

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The leading edge is the critical portion for a gas turbine blade and is often insufficiently cooled due to the adverse effect of Crossflow in the cooling chamber. A novel internal cooling structure, wall jet cooling, can suppress Crossflow effect by changing the coolant flow direction. In this paper, the conjugate heat transfer and aerodynamic characteristics of blades with three different internal cooling structures, including impingement with a single row of jets, swirl cooling, and wall jet cooling, are investigated through RANS simulations. The results show that wall jet cooling combines the advantages of impingement cooling and swirl cooling, and has a 19–54% higher laterally-averaged overall cooling effectiveness than the conventional methods at different positions on the suction side. In the blade with wall jet cooling, the spent coolant at the leading edge is extracted away through the downstream channels so that the jet could accurately impinge the target surface without unnecessary mixing, and the high turbulence generated by the separation vortex enhances the heat transfer intensity. The Coriolis force induces the coolant air to adhere to the pressure side’s inner wall surface, preventing the jet from leaving the target surface. The parallel cooling channels eliminate the common Crossflow effect and make the flow distribution of the orifices more uniform. The trailing edge outlet reduces the entire cooling structure’s pressure to a low level, which means less penalty on power output and engine efficiency.

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“…They captured the Görtler vortex pairs in the vortex chamber and determined their pronounced influences on heat transfer improvement. Other researches [9][10][11][12] into the mechanism of flow and thermal properties for vortex cooling were also reported.…”

Section: Introductionmentioning

confidence: 98%

Effect of jet nozzle geometry on flow and heat transfer performance of vortex cooling for gas turbine blade leading edge

et al. 2016

Applied Thermal Engineering

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Innovative vortex cooling concept and its application to turbine airfoil trailing edge cooling design

Cited by 12 publications

References 7 publications

Effects of aerodynamic parameters on steam vortex cooling behavior for gas turbine blade leading edge

Effects of aerodynamic parameters on steam vortex cooling behavior for gas turbine blade leading edge

Cooling Characteristic of a Wall Jet for Suppressing Crossflow Effect under Conjugate Heat Transfer Condition

Effect of jet nozzle geometry on flow and heat transfer performance of vortex cooling for gas turbine blade leading edge

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