Modelling strategies for the prediction of hot streak generation in lean burn aeroengine combustors

Andreini, Antonio; Bacci, Tommaso; Insinna, Massimiliano; Mazzei, Lorenzo; Salvadori, Simone

doi:10.1016/j.ast.2018.05.030

Cited by 24 publications

(12 citation statements)

References 26 publications

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“…Thus, several studies have already been made on various configurations, in particular in order to understand the effects of a hot spot migration in the turbine [12][13][14]. For the FACTOR configuration, many LES of the isolated or integrated chamber with the downstream turbine are already available in the literature [15][16][17][18][19][20][21]. Downstream of the injector, the flow presents a central recirculation zone in the combustion chamber and the separation of this recirculation zone gives rise to the appearance of a precessing vortex core (PVC).…”

Section: Combustion Chamber/turbine Integrated Simulationmentioning

confidence: 99%

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

et al. 2021

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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.

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Section: Combustion Chamber/turbine Integrated Simulationmentioning

confidence: 99%

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

et al. 2021

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“…There has been research on combustor relight at altitude [5][6] and work on characterizing the discharge conditions of new generation combustors [7]. These investigations have had to rely on bulk temperature and pressure values obtained from empirical knowledge of the operating conditions to establish their combustor inlet boundary conditions.…”

Section: Figure 1 Generic Relight Envelope Showing Starter Assisted A...mentioning

confidence: 99%

Numerical modeling of core compressor discharge for a windmilling aero engine

Ferrer-Vidal

Pachidis

2021

Aerospace Science and Technology

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“…Therefore, several DHS types can be obtained depending on the combustor geometry and flow conditions. In the literature, only a few studies focus on the influences of DHS combined with residual swirl generated by LBC [22][23][24][25][26][27][28] compared to the abundant studies on the combination of uniform or rounded hot-streak with a residual swirl. The studies of Andreini et al 22 and Koupper et al 23 within the framework of the European project FACTOR are interested in the influence of a swirled DHS on turbine vane aerothermal behavior.…”

Section: Introductionmentioning

confidence: 99%

Numerical prediction of heat transfer characteristics on a turbine nozzle guide vane under various combustor exit hot‐streaks

Mansouri¹

2021

Heat Trans

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The precise prediction of the aerothermal conditions at the outlet of modern combustors of aero engines is of primary interest in the aerothermal design of high‐pressure turbines. The use of high swirling flows to stabilize the flame in the new generation of lean‐burn combustors (LBCs) leads to shorter combustor length and high degrees of unsteady temperature. These aspects generate high levels of turbulence and complex temperature nonuniformity patterns at the combustor–turbine interface. Therefore, the nozzle guide vane (NGV) located at the interface exhibits a high inlet temperature gradient called a hot‐streak. The transport mechanism of the hot‐streak across the NGV needs to be decrypted to increase turbine service life and enhance its performance. In this context, the present study aims to examine numerically the effect of three new distorted hot‐streak gradients on the heat transfer characteristics across a turbine NGV. An innovative LBC is used to generate the three inlet hot‐streaks, which are highly swirled and distorted similar to real aero‐engine conditions. The use of such a generation approach avoids any simplification associated with uniform or circular contours that are widely used by researchers. A solid NGV cascade developed by NASA is adopted for the investigations. The results show significant differences in the thermal field on the cascade at each distorted thermal condition. The transport of the hot‐streak behaves differently under axial and swirl conditions. The presence of a swirl induces flow mixing and results in thermal load increasing on the cascade surfaces (NGV, hub, and shroud).

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Modelling strategies for the prediction of hot streak generation in lean burn aeroengine combustors

Cited by 24 publications

References 26 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

Numerical modeling of core compressor discharge for a windmilling aero engine

Numerical prediction of heat transfer characteristics on a turbine nozzle guide vane under various combustor exit hot‐streaks

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