Improving thermal performance of turbine blade with combination of circular and oblong fins in a wedge channel: a numerical investigation
Abstract
Because of its narrow and aerodynamic design, cooling the trailing edge of a turbine blade offers an essential problem. For the trailing edge internal cooling of gas turbine blades, wedge-shaped channels are used. Pin-fin arrays play a critical role in enhancing heat transmission at the trailing edge of turbine blades. The flow and heat transfer properties of a number of wedge channels with staggered pin-fins of varied shapes are used to develop a design with a more effective heat transfer effect and reduced flow resistance. The present study compares the combination of circular pin fins and oblong pin fins in a wedge duct with a Reynolds number range of 12,000–85,000 and a constant heat flux (surface) of 3280 W/m2 applied to the bottom wall, top wall, and surfaces of the fins. The results indicate that the pressure loss is less in circular fins at the centre and oblong fins side by side, and it is 23.67 % less than circular and oblong fins in opposite positions. The Heat transfer coefficient for circular and oblong fins in opposite positions is 16.72 % higher than circular fins at centre and oblong fin side by side. The thermal performance factor is almost the same for both cases.
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Research ethics: Not applicable.
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Author contributions: The authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Competing interests: The authors state no conflict of interest.
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Research funding: None declared.
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Data availability: Not applicable.
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© 2024 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
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- Probabilistic analysis of solid oxide fuel-cell integrated with gas turbine
- Improving thermal performance of turbine blade with combination of circular and oblong fins in a wedge channel: a numerical investigation
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- Research on cascade control method for turboshaft engine with variable rotor speed
- The overall film cooling performance of crescent holes
- Air tab location effect on supersonic jet mixing
- Design and analysis of air intake of subsonic cruise vehicle with experimental validation
- Research on an optimization design method for a TBCC propulsion scheme
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Articles in the same Issue
- Frontmatter
- Experimental and numerical investigations on controlled parameter selection methods for kerosene-fueled scramjet
- Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization
- Parametric analysis of thermal cycle of a short take-off and vertical landing engine
- Conjugate heat transfer analysis on double-wall cooling configuration including jets impingement and film holes with conformal pins
- Research on the design method of mode transition control law for Ma6 external parallel TBCC engine
- A new schedule method for compact propulsion system model
- Numerical investigation on mixing of heated confined swirling coaxial jets with blockage
- Finite element based dynamic analysis of a porous exponentially graded shaft system subjected to thermal gradients
- Numerical study on aerodynamic performance of an intake duct affected by ground effect
- Influence of metal magnesium addition on detonation initiation in shock wave focusing Pulse Detonation Engine
- Probabilistic analysis of solid oxide fuel-cell integrated with gas turbine
- Improving thermal performance of turbine blade with combination of circular and oblong fins in a wedge channel: a numerical investigation
- Investigation on effect of injector orifice diameter on injector atomization and combustion characteristics of pulse detonation combustor
- Research on cascade control method for turboshaft engine with variable rotor speed
- The overall film cooling performance of crescent holes
- Air tab location effect on supersonic jet mixing
- Design and analysis of air intake of subsonic cruise vehicle with experimental validation
- Research on an optimization design method for a TBCC propulsion scheme
- Performance analysis of a gas turbine engine via intercooling and regeneration- Part 2
- Effects of bleed pressure on shock-wave/boundary-layer interactions in a transonic compressor stator with suction holes
- Effect of asymmetric leading edge on transition of suction side