Investigation of High-Pressure Turbine Endwall Film-Cooling Performance Under Realistic Inlet Conditions

Salvadori, Simone; Ottanelli, Luca; Jonsson, Magnus; Ott, Peter; Martelli, Francesco

doi:10.2514/1.59225

Cited by 3 publications

(2 citation statements)

References 16 publications

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“…Such severe conditions result in highly-swirled and temperature-distorted flow field, due to the presence of large scale vorticity generated by the burner, that survives down the High Pressure Turbine (HPT), as proven both numerically and experimentally by Cha et al [1,2]. As a consequence, the presence of such intermittent non-uniformities in velocity and temperature can alter dramatically the heat transfer and the aerodynamics of the end-walls [3,4] and of the vanes [5,6] as well, by increasing local convection heat transfer coefficients [7], potentially causing the damage of the components or affecting their efficiency. Moreover, it has been also widely demonstrated that the different swirler-to-nozzle relative clocking position influences the migration of the high swirled hot streak through the nozzle guide vane (NGV), remaining still recognizable at its exit [8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Combustor-Turbine Interaction by Using Hybrid RANS-LES Approach

Tomasello

Andreini

Meloni³

et al. 2022

Volume 6A: Heat Transfer — Combustors; Film Cooling

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The complex flow field of gas turbine lean combustors is meant to reduce NOx emissions and maintain a stable flame by controlling the local temperature and promoting high turbulent mixing. Still, this may produce large flow and temperature unsteady distortions capable of disrupting the aerodynamics and heat transfer of the first high-pressure-turbine cooled nozzle. Therefore, the interaction between the combustion chamber and the turbine nozzle is analyzed first with the help of scale-resolving simulations that notably also include a realistic turbine nozzle cooling system. To determine the nature and severity of the interaction, and the risks associated to performing decoupled simulation, the results of the coupled computer simulation are analyzed and compared with those of decoupled simulations. In this case, the combustor is computed by replacing the turbine nozzle with a discharge convergent with the same throat area, and the conditions at the interface plane are used as inlet boundary conditions for a conventional RANS of the nozzle. The analyses of the coupled and decoupled simulation reveal that the combustion chamber is weakly affected by the presence of the nozzle, whereas the two thermal fields of the nozzle surface differ considerably, as well as the disruption of the film cooling by the incoming flow distortions.

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Section: Introductionmentioning

confidence: 99%

Numerical Study of Combustor-Turbine Interaction by Using Hybrid RANS-LES Approach

Tomasello

Andreini

Meloni³

et al. 2022

Volume 6A: Heat Transfer — Combustors; Film Cooling

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show abstract

“…In high-pressure stages, the oblique shocks shed from the trailing edge, impinging the suction side of adjacent vane. Furthermore, non-uniformity in the TET distribution is responsible for an increased vane heat load and positive jet effects, as described by Salvadori et al [1][2][3] Efficiency of film cooling must be evaluated taking into account the presence of oblique shocks and their interaction with the flow on the suction side. This interaction is characterised by a complex threedimensional (3D) process involving the cooling flow, the boundary layer development and the shock itself.…”

Section: Introductionmentioning

confidence: 99%

Film-cooling performance in supersonic flows: effect of shock impingement

Salvadori

Montomoli

Martelli

2013

Proceedings of the Institution of Mechanical Engineers, Part A:

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High pressure turbine stages work in transonic regimes and shocks waves, shed by the trailing edge, impinges into the suction side modifying the flow structures. Gas turbine entry temperature is much higher than the allowable material limit and the hot components can survive only using advanced film cooling systems. Unfortunately these systems are designed without taking into account the interaction with the shock waves and this paper would like to address this problem and to evaluate if this assumption is correct or not. A correct prediction and understanding of the interaction between the ejected coolant and the shock waves is crucial in order to achieve an optimal distribution of the coolant and to increase the components life.In this work the numerical investigation of a film-cooling test case, investigated experimentally by the University of Karlsruhe, is shown. An in-house CFD solver is used for the numerical analysis. The test rig consists in a converging-diverging nozzle that accelerates the incoming flow up to supersonic conditions and an oblique shock is generated at the nozzle exit section. Three cases have been studied, where the cooling holes has been positioned before, near and after the shock impingement. The results obtained considering four blowing ratios are presented and compared with the available experimental data.The local adiabatic effectiveness is affected by the shock-coolant interaction and this effect has been observed for all the blowing ratios investigated. A similar trend is observed in the experimental data even if the numerical simulations over-predict the impact of the interaction.

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On the Effect of an Aggressive Inlet Swirl Profile on the Aero-thermal Performance of a Cooled Vane

et al. 2015

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Investigation of High-Pressure Turbine Endwall Film-Cooling Performance Under Realistic Inlet Conditions

Cited by 3 publications

References 16 publications

Numerical Study of Combustor-Turbine Interaction by Using Hybrid RANS-LES Approach

Numerical Study of Combustor-Turbine Interaction by Using Hybrid RANS-LES Approach

Film-cooling performance in supersonic flows: effect of shock impingement

On the Effect of an Aggressive Inlet Swirl Profile on the Aero-thermal Performance of a Cooled Vane

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