Integrated Process for CFD Modeling and Optimization of Gas Turbine Combustors

Dudebout, Rudolph; Reynolds, Bob; Molla-Hosseini, K.

doi:10.1115/gt2004-54011

Cited by 9 publications

(5 citation statements)

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“…Additionally, some penalty-function constraints were assigned regarding the maximum values for the emissions of CO, CH 4 and NO (less than 10, 0.01 and 250 ppmvd @ 15% O 2 , respectively), plus a roof for the pressure losses (less than 7%). The limits have been chosen on the basis of indications given in [13].…”

Section: The Baseline Design Optimizationmentioning

confidence: 99%

“…In [2] an algorithm is presented to produce the global layout of combustion chambers for aircraft application, based on generic relations between combustor overall performance and geometry. In [3,4] the general structure of the Honeywell analysis procedure named Advanced Combustion Tool (ACT) is presented. It is based on CAD, CFD and pre and post-processing tools and allows the integrated modeling and design refinement of gas turbine combustor.…”

Section: Introductionmentioning

confidence: 99%

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An integrated approach for optimal design of micro gas turbine combustors

2009

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The present work presents an approach for the optimized design of small gas turbine combustors, that integrates a 0-D code, CFD analyses and an advanced game theory multi-objective optimization algorithm. The output of the 0-D code is a baseline design of the combustor, given the required fuel characteristics, the basic geometry (tubular or annular) and the combustion concept (i.e. lean premixed primary zone or diffusive processes). For the optimization of the baseline design a simplified parametric CAD/mesher model is then defined and submitted to a CFD code. Free parameters of the optimization process are position and size of the liner hole arrays, their total area and the shape of the exit duct, while different objectives are the minimization of NO x emissions, pressure losses and combustor exit Pattern Factor. A 3D simulation of the optimized geometry completes the design procedure. As a first demonstrative example, the integrated design process was applied to a tubular combustion chamber with a lean premixed primary zone for a recuperative methane-fuelled small gas turbine of the 100 kW class.

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Section: The Baseline Design Optimizationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

An integrated approach for optimal design of micro gas turbine combustors

2009

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“…For this purpose, several procedures have been developed for the sole combustion system. Honeywell Engines & Systems started implementing the Advanced Combustion Tool in 1998, an integrated process for rapidly analyzing and optimizing the combustor's aerodynamics from compressor deswirl to turbine stator inlet [1]. Rolls-Royce too supported the development of such methodologies.…”

Section: Introductionmentioning

confidence: 99%

Development of an Integrated Procedure for Combustor Aero-Thermal Preliminary Design

Elmi¹,

Agnolio²,

Ferraro³

et al. 2021

Preprint

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In the development of an aero-engine combustor, the definition of a preliminary design is a practice in which knowhow, product experience and design rules are focal in deriving a configuration able to meet the functional requirements. Several configurations, and hence multiple geometries resulting in different behaviours, are iteratively analysed in this phase to extensively explore the design space. In this context, an automated procedure ranging from preliminary design to life estimation is necessary and crucial. A framework in which the tools employed in the design workflow are integrated and the low-added-value tasks are automated can allow the reduction of time per analysis within the loop and the enhancement of the procedure's robustness. In this paper will be presented the Combustor Design System Integration (DSI), a methodology aimed at easing and streamlining the design process of aero-engine combustors. To do this, digitization has been taken as the common thread for developing a data-centric approach. The logic behind the procedure will be reported, to focus then on the aero-thermal preliminary design. The procedure, for this phase, is composed of three main integrated components: a CAD generation system, which collects all the geometries for creating an exportable 3D model, a 1D thermal solver for the positioning and sizing of the aero feature on liners (i.e. cooling, dilution…) and a CFD environment with automated pre/post processing operations for reacting-flow analysis. The aim of this work is to contextualize the DSI approach in the combustor design process and to provide a first description of the methodology designed and developed in GE Avio. For that purpose, a straight-through configuration -the lean combustor NEWAC developed in the homonymous EU project-will be exploited as a test case. The development of the procedure is still in progress, so a validation through test cell data comparison, as well as highly-resolved CFD results, will be the subject for future papers.

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“…Rudolph D. et al [8], developed the Advanced Combustion Tool (ACT) CFD process to rapidly analyze the performance of a gas turbine combustor from a given fuel injector, CAD geometry and engine cycle information.…”

Section: Introductionmentioning

confidence: 99%

On Low-Emission Annular Combustor Based on Designing of Liner Air Admission Holes

Dolmatov

Hajivand

2018

NTU "KhPI" Bulletin

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Numerical experiments was carried out to predict the total temperature characteristics and formation of nitrogen oxide emissions and pattern factor in an annular combustor liner based on geometrical parameters and location and rows of different air admission holes, for 6 various cases, using computational fluid dynamics (CFD) .The simulation has been performed using ANSYS CFX including finite rate chemistry and eddy dissipation model, for simulation of liquid kerosene (Jet A)-air combustion after fuel droplet evaporation. The spray modeling was performed, including Rosin-Rammler droplet distribution. Thermal and prompt nitrogen oxide (NO x) formation was performed to predicting NO x emission characteristics with a k-ε model of turbulent. In this investigation the 3D CAD model of the realistic annular combustion chamber is presented for the simulation with double radial air swirler for the better mixing fuel with air. Beside this the characteristic and the flame structure is presented including the contour plots of total temperature and NO concentration at the outlet of the combustor liner and in cross section plane along the X axis from the injector center of the combustor including the chart of the velocity and NO, CO, CO 2 , O 2 and the total temperature along the liner from the injector center. For the combustion of kerosene with air 2 step kinetic schemes are presented in this study. The results show that the best result with the low concentration of NO is the case 5 but with a high percentage of pressure drop and the case 3 have the maximum concentration of NO with the low percentage of pressure drop.

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Integrated Process for CFD Modeling and Optimization of Gas Turbine Combustors

Cited by 9 publications

References 0 publications

An integrated approach for optimal design of micro gas turbine combustors

An integrated approach for optimal design of micro gas turbine combustors

Development of an Integrated Procedure for Combustor Aero-Thermal Preliminary Design

On Low-Emission Annular Combustor Based on Designing of Liner Air Admission Holes

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