Assessment of a Coolant Injection Model on Cooled High-Pressure Vanes with Large-Eddy Simulation

Harnieh, Mael; Thomas, Martin; Bizzari, Romain; Dombard, Jérôme; Duchaine, Florent; Gicquel, Laurent

doi:10.1007/s10494-019-00091-3

Cited by 2 publications

(1 citation statement)

References 35 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…To accurately reproduce the perforation pattern in the simulation, the cooling holes on the chamber walls and the blade surface are modeled by a heterogeneous injection model [28]. Indeed, this model provides results very similar to a simulation with meshed holes for a much lower computational cost [29]. The meshes are, respectively, composed of 29.6 M cells for the plenum/combustion chamber region and 12.4 M cells for the two stator blades.…”

Section: Description Of the Configurationmentioning

confidence: 99%

Generation of Realistic Boundary Conditions at the Combustion Chamber/Turbine Interface Using Large-Eddy Simulation

et al. 2021

View full text Add to dashboard Cite

Numerical simulation of multiple components in turbomachinery applications is very CPU-demanding but remains necessary in the majority of cases to capture the proper coupling and a reliable flow prediction. During a design phase, the cost of simulation is, however, an important criterion which often defines the numerical methods to be used. In this context, the use of realistic boundary conditions capable of accurately reproducing the coupling between components is of great interest. With this in mind, this paper presents a method able to generate more realistic boundary conditions for isolated turbine large-eddy simulation (LES) while exploiting an available integrated combustion chamber/turbine LES. The unsteady boundary conditions to be used at the inflow of the isolated turbine LES are built from the modal decomposition of the database recorded at the interface between the two components of the integrated LES simulation. Given the reference LES database, the reconstructed field boundary conditions can then be compared to standard boundary conditions in the case of isolated turbine configuration flow predictions to illustrate the impact. The results demonstrate the capacity of this type of conditions to reproduce the coupling between the combustion chamber and the turbine when standard conditions cannot. The aerothermal predictions of the blade are, in particular, very satisfactory, which constitutes an important criterion for the adoption of such a method during a design phase.

show abstract

Section: Description Of the Configurationmentioning

confidence: 99%

Generation of Realistic Boundary Conditions at the Combustion Chamber/Turbine Interface Using Large-Eddy Simulation

et al. 2021

View full text Add to dashboard Cite

show abstract

High-fidelity numerical investigation of a real gas annular cascade with experimental validation

Giauque,

Schuster,

Corre

2023

Physics of Fluids

View full text Add to dashboard Cite

This study aims at investigating real gas flow in the complex geometry of the Cambridge University annular turbine cascade using numerical simulations. The objectives include validating the numerical approach and understanding the loss mechanisms in this configuration. The numerical results are compared to experimental measurements obtained at various locations in the domain. Two turbulence modeling techniques, large Eddy simulation (LES) and Reynolds-averaged Navier–Stokes (RANS), are employed to assess the influence of turbulence models and inlet turbulence levels. The results show good agreement between numerical simulations and experimental measurements in regions upstream of the trailing edge. However, discrepancies arise in the transition region of the suction side boundary layer, and RANS results are influenced by the choice of turbulence injection. In the wake of the blade, both RANS and LES accurately predict the stagnation pressure ratio, with some slight differences in shock positions and total pressure levels. The analysis reveals that large vortical structures at the hub contribute significantly to the overall losses in this annular configuration. The study quantifies losses due to boundary layers, the wake, and vortical structures using a loss coefficient, with RANS and LES producing slightly different results. These differences, while calling for further experimental measurements, also hint at the possible inaccuracy of the present turbulence models in the context of real gas flows for which a dedicated modeling effort is required.

show abstract

Assessment of a Coolant Injection Model on Cooled High-Pressure Vanes with Large-Eddy Simulation

Cited by 2 publications

References 35 publications

Generation of Realistic Boundary Conditions at the Combustion Chamber/Turbine Interface Using Large-Eddy Simulation

Generation of Realistic Boundary Conditions at the Combustion Chamber/Turbine Interface Using Large-Eddy Simulation

High-fidelity numerical investigation of a real gas annular cascade with experimental validation

Contact Info

Product

Resources

About