Session: 15-01 Impingement Cooling I

Paper Number: 123990

123990 - Numerical Analysis of Jet Impingement Heat Transfer for Gas Turbine Rotor Blades 

Jet impingement is widely adopted for turbine blade cooling due to the higher heat transfer rate compared to conventional forced convection solutions. Although RANS turbulence modeling is suitable for industrial scale applications, it lacks of accuracy when dealing with jet impingement heat transfer. The present study aims at comparing the aerodynamics and heat transfer of a leading edge cooling cavity for rotating turbine blade applications. The cooling cavity consists of a single array of jets impinging on a leading edge channel provided with three arrays of cooling holes. Different CFD approaches are proposed: RANS/URANS simulations and high-fidelity VLES simulations based on Lattice Boltzmann Methods (LBM). In all cases, commercial CFD solvers are used: ANSYS Fluent and SIMULIA PowerFLOW®, respectively. Despite similar averaged simulation results, substantial local differences emerge when comparing the different models against each other. Indeed, with the LBM approach, the normalized Nusselt evolution is flattened with respect to RANS simulations. The latter provides higher amplitude fluctuations in both the radial and span-wise directions. RANS/URANS jets have thinner shear layers and tend to diffuse less with respect to LBM predictions. As a result, RANS/URANS are less sensitive to jet-to-jet spacing for the investigated setup. Moreover, results seem to indicate that unsteady approach is more reliable in capturing jet flow behavior within the cavity and heat transfer performance at the leading edge wall, under the effects of rotation.

Presenting Author: Filippo PAGNONI Safran Aircraft Engines

Presenting Author Biography: MSc in aeronautical engineering at Politecnico di Milano (Milan, Italy)
PhD in thermal engineering at ISAE-ENSMA (Poitiers, France) : Design and Experimental Analysis of a Loop Heat Pipe for Thermal Control of Aircraft Engine Equipment
Aerothermal engineer and technical team leader at Safran Aircraft Engines since 2019
- R&D applied to heat transfer solutions for high pressure turbine vanes and blades

Authors:

Filippo PAGNONI Safran Aircraft Engines
Damien Archambaud Safran Aircraft Engines
Ignacio Gonzalez-Martino Dassault Systemes SE
Benoit Bonnal Dassault Systèmes SE