scholarly journals Artificial intelligence aided design of film cooling scheme on turbine guide vane

2020 ◽  
Vol 9 (4) ◽  
pp. 344-354
Author(s):  
Dike Li ◽  
Lu Qiu ◽  
Kaihang Tao ◽  
Jianqin Zhu
Keyword(s):  
Artificial Intelligence ◽  
Film Cooling ◽  
Guide Vane ◽  
Turbine Guide Vane ◽  
Aided Design

scholarly journals Numerical Investigation of Single-Row Double-Jet Film Cooling of a Turbine Guide Vane under High-Temperature and High-Pressure Conditions

Energies ◽  
2022 ◽  
Vol 15 (1) ◽  
pp. 287
Author(s):  
Jin Hang ◽  
Jingzhou Zhang ◽  
Chunhua Wang ◽  
Yong Shan
Keyword(s):  
Film Cooling ◽  
Guide Vane ◽  
Suction Surface ◽  
Positive Potential ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Injection Angle ◽  
Jet In Crossflow ◽  
Cooling Enhancement ◽  
Turbine Guide Vane

Single-row double-jet film cooling (DJFC) of a turbine guide vane is numerically investigated in the present study, under a realistic aero-thermal condition. The double-jet units are positioned at specific locations, with 57% axial chord length (Cx) on the suction side or 28% Cx on the pressure side with respect to the leading edge of the guide vane. Three spanwise spacings (Z) in double-jet unit (Z = 0, 0.5d, and 1.0d, here d is the film hole diameter) and four spanwise injection angles (β = 11°, 17°, 23°, and 29°) are considered in the layout design of double jets. The results show that the layout of double jets affects the coupling of adjacent jets and thus subsequently changes the jet-in-crossflow dynamics. Relative to the spanwise injection angle, the spanwise spacing in a double-jet unit is a more important geometric parameter that affects the jet-in-crossflow dynamics in the downstream flowfield. With the increase in the spanwise injection angle and spanwise spacing in the double-jet unit, the film cooling effectiveness is generally improved. On the suction surface, DJFC does not show any benefit on film cooling improvement under smaller blowing ratios. Only under larger blowing ratios does its positive potential for film cooling enhancement start to show. Compared to the suction surface, the positive potential of the DJFC on enhancing film cooling effectiveness behaves more obviously on the pressure surface. In particular, under large blowing ratios, the DJFC plays dual roles in suppressing jet detachment and broadening the coolant jet spread in a spanwise direction. With regard to the DJFC on the suction surface, its main role in film cooling enhancement relies on the improvement of the spanwise film layer coverage on the film-cooled surface.

Multi-Field Coupling Analysis on the Film-Cooling of a Turbine Guide Vane

2013 ◽  
Author(s):  
Zhan Wang ◽  
Jian-Jun Liu ◽  
Chao Zhang
Keyword(s):  
Thermal Stress ◽  
High Temperature ◽  
Creep Strain ◽  
Film Cooling ◽  
Guide Vane ◽  
Temperature Gradients ◽  
Coupling Method ◽  
Coupling Analysis ◽  
Field Coupling ◽  
Turbine Guide Vane

Multi-field coupling method is used to assess the film-cooling properties of a turbine guide vane. The creep strain is used to evaluate the film-cooling validness, in order to take into account the effects of both temperature and thermal stress. Because of the high temperature gradients, thermal stress is much higher than the aerodynamic stress in a guide vane. It is found that large creep strain may be generated where the cooling holes locate, especially near the shower-head and upper endwall. For the shower-head film cooling, three types of holes (cylindrical, fan-shaped, double-jet) were studied. The results showed that fan-shaped and double-jet holes were suitable for the cooling of the shower-head of the guide vane. For the endwall, adding more cooling holes could reduce the area of high temperature and also reduce the creep strain.

Towards Efficient CFD-Simulations of Engine Like Turbine Guide Vane Film Cooling

2011 ◽  
Author(s):  
Andreas Bradley ◽  
Hossein Nadali Najafabadi ◽  
Matts Karlsson ◽  
Joakim Wren ◽  
Esa Utriainen ◽  
...  
Keyword(s):  
Film Cooling ◽  
Guide Vane ◽  
Cfd Simulations ◽  
Turbine Guide Vane

Film cooling on a turbine guide vane: A numerical analysis with a multigrid technique

2001 ◽  
Vol 215 (1) ◽  
pp. 39-53 ◽  
Author(s):  
S Sarkar ◽  
K Das ◽  
D Basu
Keyword(s):  
Heat Transfer ◽  
Film Cooling ◽  
Guide Vane ◽  
Navier Stokes ◽  
Time Stepping ◽  
Flow And Heat Transfer ◽  
Local Time Stepping ◽  
Turbine Guide Vane ◽  
Nozzle Guide ◽  
Internal Convection

The flow and heat transfer due to film cooling over a turbine nozzle guide vane, which was also cooled by internal convection, were numerically analysed under engine conditions. The time-dependent, two-dimensional, mass-averaged, Navier-Stokes (N-S) equations are solved in the physical plane based on the four-stage Runge-Kutta algorithm in the finite volume formulation. Local time stepping, variable coefficient implicit residual smoothing and a full multigrid technique have been implemented to accelerate the steady state calculations. Turbulence was simulated by the algebraic Baldwin-Lomax (B-L) model. The computed heat transfer distributions with film cooling in conjunction was successful in describing the coolant behavior over the curved suction and pressure surfaces of a turbine blade for varying blowing and temperature ratios.

scholarly journals Numerical Investigation of a Radially Cooled Turbine Guide Vane Using Air and Steam as a Cooling Medium

Computation ◽  
2021 ◽  
Vol 9 (6) ◽  
pp. 63
Author(s):  
Sondre Norheim ◽  
Shokri Amzin
Keyword(s):  
Numerical Model ◽  
Gas Turbines ◽  
Guide Vane ◽  
Axial Direction ◽  
Average Error ◽  
Inlet Temperature ◽  
Average Temperature ◽  
Cooling Medium ◽  
Turbine Guide Vane ◽  
Steam Cooling

Gas turbine performance is closely linked to the turbine inlet temperature, which is limited by the turbine guide vanes ability to withstand the massive thermal loads. Thus, steam cooling has been introduced as an advanced cooling technology to improve the efficiency of modern high-temperature gas turbines. This study compares the cooling performance of compressed air and steam in the renowned radially cooled NASA C3X turbine guide vane, using a numerical model. The conjugate heat transfer (CHT) model is based on the RANS-method, where the shear stress transport (SST) k−ω model is selected to predict the effects of turbulence. The numerical model is validated against experimental pressure and temperature distributions at the external surface of the vane. The results are in good agreement with the experimental data, with an average error of 1.39% and 3.78%, respectively. By comparing the two coolants, steam is confirmed as the superior cooling medium. The disparity between the coolants increases along the axial direction of the vane, and the total volume average temperature difference is 30 K. Further investigations are recommended to deal with the local hot-spots located near the leading- and trailing edge of the vane.

Application of RANS and LES to the Prediction of Flows in High Pressure Turbine Components

2011 ◽  
Author(s):  
Nicolas Gourdain ◽  
Laurent Y. M. Gicquel ◽  
Remy Fransen ◽  
Elena Collado ◽  
Tony Arts
Keyword(s):  
Heat Transfer ◽  
Vortex Shedding ◽  
Guide Vane ◽  
Unsteady Flows ◽  
Separated Flow ◽  
Heat Fluxes ◽  
Boundary Layer Transition ◽  
Wall Heat Transfer ◽  
Layer Transition ◽  
Turbine Guide Vane

This paper investigates the capability of numerical simulations to estimate unsteady flows and wall heat fluxes in turbine components with both structured and unstructured flow solvers. Different numerical approaches are assessed, from steady-state methods based on the Reynolds Averaged Navier-Stokes (RANS) equations to more sophisticated methods such as the Large Eddy Simulation (LES) technique. Three test cases are investigated: the vortex shedding induced by a turbine guide vane, the wall heat transfer in another turbine guide vane and a separated flow phenomenon in an internal turbine cooling channel. Steady flow simulations usually fail to predict the mean effects of unsteady flows (such as vortex shedding) and wall heat transfer, mainly because laminar-to turbulent transition and the inlet turbulent intensity are not correctly taken into account. Actually, only the LES (partially) succeeds to accurately estimate unsteady flows and wall heat fluxes in complex configurations. The results presented in this paper indicate that this method considerably improves the level of physical description (including boundary layer transition). However, the LES still requires developments and validations for such complex flows. This study also points out the dependency of results to parameters such as the freestream turbulence intensity. When feasible solutions obtained with both structured and unstructured flow solvers are compared to experimental data.

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