Integrated Large Eddy Simulation of Combustor and Turbine Interactions: Effect of Turbine Stage Inlet Condition

To study the effects of combustion chamber dynamics on a turbine stage aerodynamics and thermal loads, an integrated Large-Eddy Simulation of the FACTOR combustion chamber simulator along with its high pressure turbine stage is performed and compared to a standalone turbine stage computation operated under the same mean conditions. For this specific configuration, results illustrate that the aerodynamic expansion of the turbine stage is almost insensitive to the inlet turbulent conditions. However, the temperature distribution in the turbine passages as well as on the stator vane and rotor blade walls are highly impacted by these inlet conditions: underlying the importance of inlet conditions in turbine stage computations and the potential of integrated combustion chamber / turbine simulations in such a context.

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Large Eddy Simulation of Combustor and Complete Single-Stage High-Pressure Turbine of the FACTOR Test Rig

Volume 2A: Turbomachinery ◽

10.1115/gt2019-91206 ◽

2019 ◽

Author(s):

Martin Thomas ◽

Jerome Dombard ◽

Florent Duchaine ◽

Laurent Gicquel ◽

Charlie Koupper

Keyword(s):

High Pressure ◽

Large Eddy Simulation ◽

Combustion Chamber ◽

Measurement Data ◽

Single Stage ◽

High Pressure Turbine ◽

Lean Burn ◽

Eddy Simulation ◽

Large Eddy ◽

Compact Design

Abstract Development goals for next generation aircraft engines are mainly determined by the need to reduce fuel consumption and environmental impact. To reduce NOx emissions lean combustion technologies will be applied in future development projects. The more compact design and the absence of dilution holes in this type of engines shortens residence times in the combustion chamber and reduces mixing which results in higher levels of swirl, turbulence and temperature distortions at the exit of the combustion chamber. For these engines interactions between components are more important, so that the traditional engine design approach of component-wise optimization will have to be adapted. To study new lean burn architectures the European FACTOR project investigates the transport of hot streaks produced by a non-reactive combustor simulator through a single stage high-pressure turbine. In this work high-fidelity Large Eddy Simulation (LES) of combustor and complete high-pressure turbine are discussed and validated against experimental data. Measurement data is available on P40 (exit of the combustion chamber), P41 (exit of the stator) and P42 (exit of the rotor) and generally shows a good agreement to LES data.

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Large Eddy Simulation of an ultra-micro combustion chamber

Proceedings of the Sixth International Symposium On Turbulence, Heat and Mass Transfer ◽

10.1615/ichmt.2009.turbulheatmasstransf.410 ◽

2009 ◽

Author(s):

A. Minotti ◽

Enrico Sciubba

Keyword(s):

Large Eddy Simulation ◽

Combustion Chamber ◽

Eddy Simulation ◽

Large Eddy

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A Method of Measuring Turbulent Flow Structures With Particle Image Velocimetry and Incorporating Into Boundary Conditions of Large Eddy Simulations

Journal of Fluids Engineering ◽

10.1115/1.4039256 ◽

2018 ◽

Vol 140 (7) ◽

Cited By ~ 4

Author(s):

Puxuan Li ◽

Steve J. Eckels ◽

Garrett W. Mann ◽

Ning Zhang

Keyword(s):

Particle Image Velocimetry ◽

Large Eddy Simulation ◽

Boundary Conditions ◽

Particle Image ◽

Advantages And Disadvantages ◽

Eddy Simulation ◽

Piv Measurement ◽

Image Velocimetry ◽

Large Eddy ◽

Inlet Conditions

The setup of inlet conditions for a large eddy simulation (LES) is a complex and important problem. Normally, there are two methods to generate the inlet conditions for LES, i.e., synthesized turbulence methods and precursor simulation methods. This study presents a new method for determining inlet boundary conditions of LES using particle image velocimetry (PIV). LES shows sensitivity to inlet boundary conditions in the developing region, and this effect can even extend into the fully developed region of the flow. Two kinds of boundary conditions generated from PIV data, i.e., steady spatial distributed inlet (SSDI) and unsteady spatial distributed inlet (USDI), are studied. PIV provides valuable field measurement, but special care is needed to estimate turbulent kinetic energy and turbulent dissipation rate for SSDI. Correlation coefficients are used to analyze the autocorrelation of the PIV data. Different boundary conditions have different influences on LES, and their advantages and disadvantages for turbulence prediction and static pressure prediction are discussed in the paper. Two kinds of LES with different subgrid turbulence models are evaluated: namely dynamic Smagorinsky–Lilly model (Lilly model) and wall modeled large eddy simulation (WMLES model). The performances of these models for flow prediction in a square duct are presented. Furthermore, the LES results are compared with PIV measurement results and Reynolds-stress model (RSM) results at a downstream location for validation.

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Large-Eddy Simulation of an Integrated High-Pressure Compressor and Combustion Chamber of a Typical Turbine Engine Architecture

Volume 2C: Turbomachinery ◽

10.1115/gt2020-16288 ◽

2020 ◽

Author(s):

Carlos Pérez Arroyo ◽

Jérôme Dombard ◽

Florent Duchaine ◽

Laurent Gicquel ◽

Nicolas Odier ◽

...

Keyword(s):

High Pressure ◽

Large Eddy Simulation ◽

Combustion Chamber ◽

High Amplitude ◽

Turbine Engine ◽

Eddy Simulation ◽

High Pressure Compressor ◽

Large Eddy ◽

Pressure Perturbations ◽

Pressure Compressor

Abstract The design optimization of aviation propulsion systems by means of computational fluid dynamics is key to increase their efficiency and reduce pollutant and noise emissions. The recurrent increase in available computing power allows nowadays to perform unsteady high-fidelity computations of the different components of a gas turbine. However, these simulations are often made independently of each other and they only share average quantities at interfaces. In this work, the methodology and first results for a sectoral large-eddy simulation of an integrated high-pressure compressor and combustion chamber of a typical turbine engine architecture is proposed. In the simulation, the compressor is composed of one main blade and one splitter blade, two radial diffuser vanes and six axial diffuser vanes. The combustion chamber is composed of the contouring casing, the flame-tube and a T-shaped vaporizer. This integrated computation considers a good trade-off between accuracy of the simulation and affordable CPU cost. Results are compared between the stand-alone combustion chamber simulation and the integrated one in terms of global, integral and average quantities. It is shown that pressure perturbations generated by the interaction of the impeller blades with the diffuser vanes are propagated through the axial diffuser and enter the combustion chamber through the dilution holes and the vaporizer. Due to the high amplitude of the pressure perturbations, several variables are perturbed at the blade-passing frequency and multiples. This is also reflected on combustion where two broadband peaks appear for the global heat release.

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