Effect of Thermal Conductivity on Nozzle Guide Vane Internal Surface Temperature Distribution
-
Arun Kumar Pujari
,
B. V. S. S. S Prasad
Abstract
Conjugate heat transfer analysis is carried out in a cascade domain for a nozzle guide vane. The nozzle guide vane is internally cooled by jet impingement cooling, and the external surface is cooled by film cooling. A computational study was carried out with three different materials, having conductivity values of 0.0048, 0.2 and 1.1 W/m.K. Distribution of local surface temperature along the leading edge, pressure and suction surface is reported. The leading edge region showed the maximum increase in internal surface temperature as the conductivity increased among the different regions of the vane internal surface. However, the pressure and suction surfaces showed relatively less increase in the surface temperature distribution. In order to validate the computational result, the obtained temperature data were compared with experimentally obtained surface temperature data. The flow phenomena like jet lift-off and self-induced cross-flow affect the local temperature distribution differently in the three materials. For a constant mainstream and coolant flow, the surface temperature gradient is higher for the lower conductivity material, and the gradient decreases as conductivity increases. Hence, a material with higher conductivity is desired in a combined impingement and film cooled nozzle guide vane, to increase the durability of the vane.
Nomenclature
- Bi
Biot number, non-dimensional [h.t/k]
- C
Vane chord, m
- d
Jet diameter, m
- D
Coolant plenum diameter, m
- h
Heat transfer coefficient, W/m2K
- hi
Heat transfer coefficient of internal surface, W/m2K
- he
Heat transfer coefficient of external surface, W/m2K
- H
Distance between jet hole and target surface, m
- k
Thermal conductivity, W/m.K
- l
Span length, m
- M
Mass flow, kg/s
- Nu
Nusselt number, non-dimensional
- q″
Heat flux
- Re
Reynolds number, non-dimensional
- S
Distance along the vane surface from leading edge, m
- Sp.max
Distance along pressure surface from leading edge to trailing edge, m
- Ss.max
Distance along suction surface from leading edge to trailing edge, m
- T
Temperature, K
- t
Thickness of vane, m
- V
Velocity
- y+
Dimensionless wall distance
- Z
Distance along the span
Greek Symbols
- ρ
Density, kg/m3
- κ
Turbulent kinetic energy, m2/s2
- ω
Specific dissipation rate, 1/sec
- μ
Coefficient of viscosity, N s/m2
- φ
Overall effectiveness, (Tm-Te)/(Tm-Tc)
Subscripts
- amb
Ambient
- c
Coolant
- e
External
- f
Fluid
- i
Internal
- m
Mainstream
- s
Solid
- w
Wall
Abbreviations
- AIT
Aft Impingement Tube
- DH
Hydraulic Diameter
- FIT
Front Impingement Tube
- HTC
Heat Transfer Coefficient
- LER
Leading Edge Region
- NDL
Non-Dimensional Length, (=S/Ss.max, S/Spmax)
- NDT
Non-Dimensional Temperature, θ
- NGV
Nozzle Guide Vane
- PSIH
Pressure Surface Impingement Hole
- PSMS
Pressure Surface Mid-Span
- RANS
Reynolds Averaged Navier Stokes
- SSFR
Suction Surface Fillet Region
- SSIH
Suction Surface Impingement Hole
- SSMS
Suction Surface Mid-Span
- SST
Shear Stress Transport
Acknowledgment
The authors would like to thank GATET and GTRE Bangalore for the financial support for the present investigation.
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© 2018 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Rotor Balancing with Turbine Blade Assembly Using Ant Colony Optimization for Aero-Engine Applications
- Effect of Thermal Conductivity on Nozzle Guide Vane Internal Surface Temperature Distribution
- Investigation of Leading Edge Tubercles with Different Wavelengths in an Annular Compressor Cascade
- Risk Analysis of Propulsion System based on Similarity Measure and Weighted Fuzzy Risk Priority Number in FMEA
- Research on Integrated Control Method of Tiltrotor with Variable Rotor Speed Based on Two-Speed Gearbox
- Thermo-Efficiencies of a Tubular Combustor Under Different Inlet Conditions
- Flow Mixing and Screech Characteristics of Elliptical Supersonic Jet
- Numerical Simulation on the Effect of Cooling Hole Configuration on the Film Cooling Effectiveness in TBC Coated Turbine Vanes
- An Investigation of the Behavior of Steady-State Laminar Jet Spray Flames
Articles in the same Issue
- Frontmatter
- Rotor Balancing with Turbine Blade Assembly Using Ant Colony Optimization for Aero-Engine Applications
- Effect of Thermal Conductivity on Nozzle Guide Vane Internal Surface Temperature Distribution
- Investigation of Leading Edge Tubercles with Different Wavelengths in an Annular Compressor Cascade
- Risk Analysis of Propulsion System based on Similarity Measure and Weighted Fuzzy Risk Priority Number in FMEA
- Research on Integrated Control Method of Tiltrotor with Variable Rotor Speed Based on Two-Speed Gearbox
- Thermo-Efficiencies of a Tubular Combustor Under Different Inlet Conditions
- Flow Mixing and Screech Characteristics of Elliptical Supersonic Jet
- Numerical Simulation on the Effect of Cooling Hole Configuration on the Film Cooling Effectiveness in TBC Coated Turbine Vanes
- An Investigation of the Behavior of Steady-State Laminar Jet Spray Flames
