Multi-objective optimization of discrete film hole arrangement on a high pressure turbine end-wall with conjugate heat transfer simulations

2019 ◽  
Vol 78 ◽  
pp. 108428 ◽  
Author(s):  
Xu Wang ◽  
Huazhao Xu ◽  
Jianhua Wang ◽  
Wei Song ◽  
Ming Wang
Keyword(s):  
Heat Transfer ◽  
High Pressure ◽  
Conjugate Heat Transfer ◽  
Multi Objective Optimization ◽  
High Pressure Turbine ◽  
Multi Objective ◽  
End Wall

Mesh Generation for Conjugate Heat Transfer Analysis of a Cooled High Pressure Turbine Stage

2008 ◽  
Author(s):  
Colinda Goormans-Francke ◽  
Guy Carabin ◽  
Charles Hirsch
Keyword(s):  
Heat Transfer ◽  
High Pressure ◽  
Mesh Generation ◽  
Conjugate Heat Transfer ◽  
Turbine Stage ◽  
High Pressure Turbine ◽  
Flow Solver ◽  
Rib Turbulators ◽  
Structured Mesh ◽  
Grid Points

The presented work demonstrates the feasibility of quasi-automatic structured mesh generation for all details in the complex cooling system of an industrial high pressure turbine stage, as required by advanced Conjugate Heat Transfer (CHT) simulations. The grid generation software has been adapted in order to quasi-automatically mesh typical cooling configurations such as cooling passages, basins, inserts, solid bodies, cooling holes, slots, and rib turbulators. A multi-domain structured mesh with about 154 million grid points and 12,316 blocks has been generated for the turbine stage. It includes 1,000 cooling holes, over 250 rib turbulators and 150 pin fins for the turbine stage. In order to verify the CFD response to the grid properties, simulations were performed as a first step on the coarse grid level (of 21.8 million grid points) using the 3D flow solver package FINE™/Turbo. The conductivity equation was solved for the solid part of the computational domain using the same temporal discretization scheme as for the flow solver. Parallel, coupled fluid/solid calculations using the k-ε turbulence model were performed on three different configurations: nozzle guide vane alone, rotor-blade alone, and full stage. These results show the feasibility of this approach to mesh generation for use in CHT modeling of the complex configuration of cooled turbine stages.

Multi-Objective Optimization of the Impingement-Film Cooling Structure of a Gas Turbine Endwall Using Conjugate Heat Transfer Simulations

2017 ◽  
Vol 10 (2) ◽  
Author(s):  
Zhongran Chi ◽  
Haiqing Liu ◽  
Shusheng Zang
Keyword(s):  
Heat Transfer ◽  
Film Cooling ◽  
Conjugate Heat Transfer ◽  
Pareto Front ◽  
Parametric Design ◽  
Multi Objective Optimization ◽  
Nsga Ii ◽  
Multi Objective ◽  
Lift Off ◽  
Optimization Search

This paper discusses the approach of cooling design optimization of a high-pressure turbine (HPT) endwall with applied 3D conjugate heat transfer (CHT) computational fluid dynamics (CFD). This study involved the optimization of the spacing of impingement jet array and the exit width of shaped holes, which are different for each cooling cavity. The optimization objectives were to reduce the wall-temperature level and to increase the aerodynamic performance. The optimization methodology consisted of an in-house parametric design and CFD mesh generation tool, a CHT CFD solver, a database of CFD results, a metamodel, and an algorithm for multi-objective optimization. The CFD tool was validated against experimental data of an endwall at CHT conditions. The metamodel, which could efficiently estimate the optimization objectives of new individuals without CFD runs, was developed and coupled with nondominated sorting genetic algorithm II (NSGA II) to accelerate the optimization process. Through the optimization search, the Pareto front of the problem was found in each iteration. The accuracy of metamodel with more iterations was improved by enriching database. But optimal designs found by the last iteration are almost identical with those of the first iteration. Through analyzing extra CFD results, it was demonstrated that the design variables in the Pareto front successfully reached the optimal values. The optimal pitches of impingement arrays could be decided accommodating the local thermal load while avoiding jet lift-off of film coolant. It was also suggested that cylindrical film holes near throat should be beneficial to both aerodynamic and cooling performances.

Optimization of a high pressure turbine blade tip cavity with conjugate heat transfer analysis

2016 ◽  
Vol 30 (12) ◽  
pp. 5529-5538 ◽  
Author(s):  
Jinuk Kim ◽  
Young Seok Kang ◽  
Dongwha Kim ◽  
Jihyeong Lee ◽  
Bong Jun Cha ◽  
...  
Keyword(s):  
Heat Transfer ◽  
High Pressure ◽  
Turbine Blade ◽  
Conjugate Heat Transfer ◽  
Heat Transfer Analysis ◽  
High Pressure Turbine ◽  
Blade Tip

Multi-Objective Optimization of the Impingement-Film Cooling Structure of a HPT Endwall Using Conjugate Heat Transfer CFD

2016 ◽  
Author(s):  
Zhongran Chi ◽  
Haiqing Liu ◽  
Shusheng Zang
Keyword(s):  
Heat Transfer ◽  
Genetic Algorithm ◽  
Wall Temperature ◽  
Conjugate Heat Transfer ◽  
Pareto Front ◽  
Multi Objective Optimization ◽  
Nsga Ii ◽  
Multi Objective ◽  
Lift Off ◽  
Optimization Search

This paper discusses the approach of cooling design optimization of a HPT endwall with 3D Conjugate Heat Transfer (CHT) CFD applied. This study involved the optimization of the spacing of impingement jet array and the exit width of shaped holes, which were different for each cooling cavity. The optimization objectives were to reduce the wall temperature level and also to increase the aerodynamic performance of the gas turbine. The optimization methodology consisted of an in-house parametric design & CFD mesh generation tool, a CHT CFD solver, a database of wall temperature distributions, a metamodel, and a genetic algorithm (GA) for evolutionary multi-objective optimization. The CFD tool was validated against experimental data of an endwall at CHT conditions. The metamodel, which could efficiently predict the aerodynamic loss and the wall temperature distribution of a new individual based on the database, was developed and coupled with Non-dominated Sorting Genetic Algorithm II (NSGA-II) to accelerate the optimization process. Through optimization search, the Pareto front of the problem was found costing only tens of CFD runs. By comparing with additional CFD results, it was demonstrated that the design variables in the Pareto front successfully reached the optimal values. The optimal spacing of each impingement array was decided accommodating the local thermal load while avoiding jet lift-off of film coolant. It was also suggested that using cylindrical film holes near throat could benefit both aerodynamics and cooling.

scholarly journals Erratum to “Optimization of a high pressure turbine blade tip cavity with conjugate heat transfer analysis”

2017 ◽  
Vol 31 (1) ◽  
pp. 479-479
Author(s):  
Jinuk Kim ◽  
Young Seok Kang ◽  
Dongwha Kim ◽  
Jihyeong Lee ◽  
Bong Jun Cha ◽  
...  
Keyword(s):  
Heat Transfer ◽  
High Pressure ◽  
Turbine Blade ◽  
Conjugate Heat Transfer ◽  
Heat Transfer Analysis ◽  
High Pressure Turbine ◽  
Blade Tip

Turbulence Model Assessment for Conjugate Heat Transfer in a High Pressure Turbine Vane Model

2008 ◽  
Author(s):  
Gustavo A. Ledezma ◽  
Gregory M. Laskowski ◽  
Anil K. Tolpadi
Keyword(s):  
Heat Transfer ◽  
High Pressure ◽  
Film Cooling ◽  
Conjugate Heat Transfer ◽  
Internal Cooling ◽  
Model Assessment ◽  
High Pressure Turbine ◽  
Turbine Vane ◽  
Internally Cooled ◽  
Near Wall

An assessment of steady state Reynolds Averaged Navier-Stokes (RANS) models has been undertaken for conjugate heat transfer of an internally cooled high-pressure turbine vane with and without film cooling. The assessment includes near wall treatment and different 2-equation Eddy Viscosity Models (EVM) and 6-equation Reynolds Stress Models (RSM) models. The present study was conducted using CFX v11.0 with unstructured tetrahedral meshes with near wall prism layers. The validation cases are the 1983 NASA C3X internally cooled vane and the 1988 NASA C3X internally and film cooled vane. Internal cooling for both cases is achieved with ten radial cooling channels of constant cross-sectional area. Film cooling is achieved for the same airfoil geometry but with three separately fed upstream plenums feeding various rows of film cooling holes. Predictions obtained with the different modeling strategies are compared to documented metal surface pressures and temperatures and the differences are discussed. A conjugate heat transfer assessment is made using the vane Biot number. In general good agreement with experimental data is obtained for wall integration meshes with the k-ω and SST turbulence models.

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