Development and application of a pre-design tool for aero-engine combustors

Tietz, Sebastian; Behrendt, Thomas

doi:10.1007/s13272-011-0012-x

Cited by 8 publications

(2 citation statements)

References 24 publications

(22 reference statements)

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“…Moreover, the user was able to discard the impracticable configurations at the early stage of the design process by calculating and comparing design versions according to various combustor configurations using the automated preliminary design tool (Pegemanyfar et al , 2006). Because the conditions constantly change in flight, the off-design calculation is important when designing gas turbine engines, so the off-design calculation method was proposed in the combustor design (Tietz and Behrendt, 2011).…”

Section: Combustor Design Methodsmentioning

confidence: 99%

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

Kim,

Jin,

et al. 2024

AEAT

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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.

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Section: Combustor Design Methodsmentioning

confidence: 99%

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

Kim,

Jin,

et al. 2024

AEAT

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show abstract

“…Therefore, different approaches and considerations of combustor design are presented in the above cited references. Large numbers of general combustor design methodologies have been reported in the literatures [6][7][8][9][10][11][12][13]. A more detailed design process for conventional combustors is presented by Pegemanifar and others [14][15][16] where a nonextensive statistical effort has been implemented.…”

Section: Introductionmentioning

confidence: 99%

Development of an Augmented Conceptual Design Tool for Aircraft Gas Turbine Combustors

Saboohi

Ommi

Fakhrtabatabaei³

2016

IJM

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Design and Application of a Multidisciplinary Predesign Process for Novel Engine Concepts

Reitenbach

Krumme

Behrendt

et al. 2018

Journal of Engineering for Gas Turbines and Power

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The purpose of this paper is to present a multidisciplinary predesign process and its application to three aero-engine models. First, a twin spool mixed flow turbofan engine model is created for validation purposes. The second and third engine models investigated comprise future engine concepts: a counter rotating open rotor (CROR) and an ultrahigh bypass turbofan. The turbofan used for validation is based on publicly available reference data from manufacturing and emission certification. At first, the identified interfaces and constraints of the entire predesign process are presented. An important factor of complexity in this highly iterative procedure is the intricate data flow, as well as the extensive amount of data transferred between all involved disciplines and among different fidelity levels applied within the design phases. To cope with the inherent complexity, data modeling techniques have been applied to explicitly determine required data structures of those complex systems. The resulting data model characterizing the components of a gas turbine and their relationships in the design process is presented in detail. Based on the data model, the entire engine predesign process is presented. Starting with the definition of a flight mission scenario and resulting top level engine requirements, thermodynamic engine performance models are developed. By means of these thermodynamic models, a detailed engine component predesign is conducted. The aerodynamic and structural design of the engine components are executed using a stepwise increase in level of detail and are continuously evaluated in context of the overall engine system.

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Development and application of a pre-design tool for aero-engine combustors

Cited by 8 publications

References 24 publications

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

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

Development of an Augmented Conceptual Design Tool for Aircraft Gas Turbine Combustors

Design and Application of a Multidisciplinary Predesign Process for Novel Engine Concepts

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