Multiple-objective Optimization of a Subsonic Small-scale Cavity-stabilized Combustor

Thomas, Nathan; Rumpfkeil, Markus P.; Briones, Alejandro M.; Erdmann, Timothy J.; Rankin, Brent A.

doi:10.2514/6.2019-0990

Cited by 4 publications

(2 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Several studies [2][3][4][5] have used Reynolds Averaged Navier Stokes (RANS) based CFD simulations combined with the Design of Experiments (DOE) algorithms to improve combustor performance by varying geometric and operational design variables. Automated CFD design study workflow presented by Briones 6 , et al and Thomas 7 , et al is used for the design space exploration and optimization of a gas turbine combustor. They use DOE algorithms along with adaptive multi-objective optimization algorithms for exploring the design space.…”

Section: Introductionmentioning

confidence: 99%

Comparison of Response Surface Based Preliminary Design Methodologies for a Gas Turbine Combustor

Mahto,

Chakravarthy

2024

Def. Sc. J.

View full text Add to dashboard Cite

Preliminary design of gas turbine combustor is a multi-objective optimization problem. The methodology to be used at the preliminary design stage depends on the freedom of design choices available. In this article, we explore three preliminary design methodologies for gas turbine combustor - M1: combustion liner design for a given casing; M2: combustion liner design without the casing and M3: coupled design of combustion liner and casing. A workflow for the automated design space exploration of gas turbine combustor using response surface methodology is presented. Computational fluid dynamics studies along with central composite design for design of experiments and genetic aggregation for response surface generation are used to quantify the combustor performance in design space. Comparison of three different design methodologies (M1, M2 and M3) is made to show how the choice of design methodology changes the available design space and limits/expands combustor performance. Candidate optimal designs and associated trade-offs from the optimization study are also presented. This study can aid combustor design engineers choose the most suitable preliminary design methodology for their specific use case.

show abstract

Section: Introductionmentioning

confidence: 99%

Comparison of Response Surface Based Preliminary Design Methodologies for a Gas Turbine Combustor

Mahto,

Chakravarthy

2024

Def. Sc. J.

View full text Add to dashboard Cite

show abstract

“…Laranci et al [11] also employed 3D RANS simulations in their optimization of exit temperature and NOx but within a simpler two variable, full factorial, DoE approach instead of a formal optimization. Recently Briones et al [12] and Thomas et al [13] both optimized combustors considering the exit temperature profile and pressure losses using 3D RANS simulations, with 9 and 15 geometry parameters respectively, but did not consider emissions reduction.…”

Section: Introductionmentioning

confidence: 99%

The Potential of a Multifidelity Approach to Gas Turbine Combustor Design Optimization

Toal

Zhang

Keane

et al. 2021

Journal of Engineering for Gas Turbines and Power

View full text Add to dashboard Cite

The desire to reduce gas turbine emissions drives the use of design optimization approaches within the combustor design process. However, the relative cost of combustion simulations can prohibit such optimizations from being carried out within an industrial setting. Strategies which can significantly reduce the cost of such studies can enable designers to further improve emissions performance. The following paper investigates the application of a multi-fidelity surrogate modelling approach to the design optimization of a typical gas turbine combustor from a civil airliner engine. Results over three different case studies of varying problem dimensionality indicate that a multi-fidelity surrogate modelling based design optimization, whereby the simulation fidelity is varied by adjusting the coarseness of the mesh, can indeed improve optimization performance. These results indicate that such an approach has the potential to significantly reduce design optimization cost whilst achieving similar, or in some cases superior, design performance.

show abstract

Response surface methodology for design of gas turbine combustor

Mahto

Chakravarthy

2022

Applied Thermal Engineering

View full text Add to dashboard Cite

Multiple-objective Optimization of a Subsonic Small-scale Cavity-stabilized Combustor

Cited by 4 publications

References 9 publications

Comparison of Response Surface Based Preliminary Design Methodologies for a Gas Turbine Combustor

Comparison of Response Surface Based Preliminary Design Methodologies for a Gas Turbine Combustor

The Potential of a Multifidelity Approach to Gas Turbine Combustor Design Optimization

Response surface methodology for design of gas turbine combustor

Contact Info

Product

Resources

About