Numerical Study on Heat Transfer Enhancement of Swirl Chamber on Gas Turbine Blade
-
Haifen Du
,
Wei Jiang
Abstract
The optimization of turbine cooling design has become a new research field of gas turbine. The swirl chamber is a prospect cooling concept. In this paper, the numerical simulation of the swirl chamber is carried out by FLUENT. The influence of inlet size parameters, temperature ratio and inlet Reynolds number on the enhanced heat transfer of swirl chamber is studied. The results show that, in the range of the studied condition, Nusselt number decreases with the height, the width, the ratio of width to height and Reynolds number. It also shows that comprehensive heat transfer effect is best at d=20 mm and enhances observably with the enlargement of width, width height ratio, and Reynolds number. Friction factor increases with height, width, temperature ratio and Reynolds number decreases. It is increased by increasing width height ratio. Nusselt number and comprehensive heat transfer effect decrease a little with aggrandizement of temperature ratio.
Funding statement: This paper is funded by the Natural Sciences Foundation of China (NSFC grant #51376140), which is gratefully acknowledged.
Nomenclature
- L
Length of swirl pipe
- L1
Length of inlet duct
- L2
Length of outlet duct
- L3
Length of the second inlet duct to outlet duct
- D
Swirl pipe diameter
- DH
Inlet duct hydraulic diameter
- b
Width of inlet duct
- d
Height of inlet duct
- A
Cross-sectional area of inlet duct
- Ti
Inlet duct temperature
- Tw
Wall surface temperature
- Re
Reynolds number based on inlet duct,=UDH/ʋ
- U
Mean inlet duct velocity
- ʋ
Kinematic viscosity of fluid
- qw
Wall heat flux
- h
Heat transfer coefficient,=q/(Tw–Ti)
- λ
Thermal conductivity
- Nu
Nusselt number,=hD/λ
- Nuc
Circumferentially Nusselt number
- ∆p
Pressure drop between inlet and outlet
- M
Mass flow
- f
Friction factor
- y+
Non-dimensional distance
- x
swirl chamber axial direction
- Pr
Prandtl number of air
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© 2018 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
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- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Experimental Investigation of Shape Transition Effects on Isolator Performance
- Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor
- Gas Turbine Engine Gas-path Fault Diagnosis Based on Improved SBELM Architecture
- The Effects of Turbulent Burning Velocity Models in a Swirl-Stabilized Lean Premixed Combustor
- Inverse Simulation for Gas Turbine Engine Control through Differential Algebraic Inequality Formulation
- Aerodynamic Optimization of Turbine Based Combined Cycle Nozzle
- Nonlinear System Modeling based on System Equilibrium Manifold
- Numerical Study on Heat Transfer Enhancement of Swirl Chamber on Gas Turbine Blade
Articles in the same Issue
- Frontmatter
- Editorials
- Reasons for Triple-Funding of the Jet-Engine-Industry to Meet 2020–2040 6th-Gen-Challenge: Counter-Air Penetration, CAP
- Reasons for triple-funding of the jet-engine-industry to meet 2020-2040 6TH-Gen-Challenge: Counter-Air Penetration, CAP
- Original Research Articles
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Experimental Investigation of Shape Transition Effects on Isolator Performance
- Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor
- Gas Turbine Engine Gas-path Fault Diagnosis Based on Improved SBELM Architecture
- The Effects of Turbulent Burning Velocity Models in a Swirl-Stabilized Lean Premixed Combustor
- Inverse Simulation for Gas Turbine Engine Control through Differential Algebraic Inequality Formulation
- Aerodynamic Optimization of Turbine Based Combined Cycle Nozzle
- Nonlinear System Modeling based on System Equilibrium Manifold
- Numerical Study on Heat Transfer Enhancement of Swirl Chamber on Gas Turbine Blade
