State-of-the-Art Combustor Design Utilizing the Preliminary Combustor Design System PRECODES

Pegemanyfar, Nima; Pfitzner, Michael

doi:10.1115/gt2008-50577

Cited by 6 publications

(5 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…As the advanced gas turbine engine combustor accepted the new combustion technology, it became impossible to follow the previous design model as it is, and accordingly, design methods for various types of low-emission combustors have been proposed in recent years (Khandelwal et al , 2014; Li et al , 2017; Pegemanyfar, 2008). In particular, Liu et al (2021) presented in detail a design methodology that combines empirical and semiempirical methods with physics-based and numerical methods so that they can be applied to various low-emission combustors.…”

Section: Combustor Design Methodsmentioning

confidence: 99%

“…Due to the complexity and repeatability of the combustor design, attempts have been made to construct an automated and integrated design system by combining preliminary design, performance evaluation and optimization (Fuligno et al , 2006; Li et al , 2017). Furthermore, studies on modularization, parameterization and automation of each stage of the design have been intensified (Pegemanyfar, 2008; Pegemanyfar et al , 2006). Methodologies for designing a combustor in response to a new combustion technology were also proposed out of the conventional combustor design (Li et al , 2017; Liu et al , 2021).…”

Section: Combustor Design Methodsmentioning

confidence: 99%

“…The application of CFD in the combustor design becomes more active, and the design converges closer to the target, thereby reducing the number of experiments, but the CFD simulation also consumes a lot of time and effort. This made designers feel uncomfortable, and the development of various software at the same time as research to solve this problem made it possible to automatically proceed with the whole process from preliminary design to CAD geometry, mesh generation and CFD simulation (Pegemanyfar, 2008).…”

Section: D Performance Evaluationmentioning

confidence: 99%

See 2 more Smart Citations

Design methodology for combustor in advanced gas turbine engines: a review

Kim,

Jin,

et al. 2024

AEAT

View full text Add to dashboard Cite

Purpose A combustor design is a particularly important and difficult task in the development of gas turbine engines. During studies for accurate and easy combustor design, reasonable design methodologies have been established and used in engine development. The purpose of this paper is to review the design methodology for combustor in development of advanced gas turbine engines. The advanced combustor development task can be successfully achieved in less time and at lower cost by adopting new and superior design methodologies. Design/methodology/approach The review considers the main technical problems (combustion, cooling, fuel injection and ignition technology) in the development of modern combustor design and deals with combustor design methods by dividing it into preliminary design, performance evaluation, optimization and experiment. The advanced combustion and cooling technologies mainly used in combustor design are mentioned in detail. In accordance with the modern combustor design method, the design mechanisms are considered and the methods used in every stage of the design are reviewed technically. Findings The improved performances and strict emission limits of gas turbine engines require the application of advanced technologies when designing combustors. The optimized design mechanism and reasonable performance evaluation methods are very important in reducing experiments and increasing the effectiveness of the design. Originality/value This paper provides a comprehensive review of the design methodology for the advanced gas turbine engine combustor.

show abstract

Section: Combustor Design Methodsmentioning

confidence: 99%

Section: Combustor Design Methodsmentioning

confidence: 99%

Section: D Performance Evaluationmentioning

confidence: 99%

See 1 more Smart Citation

Design methodology for combustor in advanced gas turbine engines: a review

Kim,

Jin,

et al. 2024

AEAT

View full text Add to dashboard Cite

show abstract

“…They use DOE algorithms along with adaptive multi-objective optimization algorithms for exploring the design space. Pegemanyfar [8][9] , et al discuss a combustor design tool that uses a combination of empirical design rules, network solvers, and CFD solvers for preliminary combustor design. More recently, machine learning methods have been incorporated into the search for optimal engine designs.…”

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

“…Rolls-Royce too supported the development of such methodologies. In PRECODES (Preliminary Combustor Design System), design rules and parameters were formalized in a knowledge-based system for determining the flame tube concept and then feeding the preliminary phase [2][3][4][5]. A more detailed approach is represented by PROMETHEUS Design System [6,7], in which pre-and-post processing operation are automatically set according to a feature recognition method.…”

Section: Introductionmentioning

confidence: 99%

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

Elmi¹,

Agnolio²,

Ferraro³

et al. 2021

Preprint

View full text Add to dashboard Cite

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.

show abstract

State-of-the-Art Combustor Design Utilizing the Preliminary Combustor Design System PRECODES

Cited by 6 publications

References 0 publications

Design methodology for combustor in advanced gas turbine engines: a review

Design methodology for combustor in advanced gas turbine engines: a review

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

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

Contact Info

Product

Resources

About