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This research aims to explore the cooling efficiency of turbine vanes with matrix cooling channels.

Numerical Investigation on Conjugate Heat Transfer in a Turbine Vane with Matrix Cooling Channel

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Numerical simulation demonstrates improved heat transfer in gas turbine blades, highlighting the role of matrix cooling channels.

This research aims to explore the cooling efficiency of turbine vanes with matrix cooling channels.
Conducted numerical simulations based on the SST k-ω turbulence model.
Analyzed the effects of rib width ratio and rib inclination angle on cooling performance.
Compared matrix cooling channels with traditional pin-fin structures.
Average temperature of turbine vane surfaces reduced by up to 58.81 K under optimal conditions.
Film hole cooling effect significantly enhanced with improved design.
Findings provide insights into high-efficiency thermal protection for gas turbines.

Wang et al. (2026) studied this question.

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