Preliminary design and performance analysis of a low emission aero-derived gas turbine combustor

Khandelwal, Bhupendra; Karakurt, Adam; Sethi, Vishal; Singh, Riti; Quan, Z.

doi:10.1017/s0001924000008848

Cited by 2 publications

(3 citation statements)

References 10 publications

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“…Singh [9] has mentioned that for modem civil engine combustors, the liner length to depth ratio is about 2. Therefore, the length of the liner can be calculated as follows: vi.…”

Section: M/s and 8 M/s Are Chosen And Then The Dome Section Areamentioning

confidence: 99%

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Design, Evaluation and Performance Analysis of Staged Low Emission Combustors

Khandelwal

Banjo

Sethi

2014

Journal of Engineering for Gas Turbines and Power

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The most uncertain and challenging part in the design of a gas turbine has long been the combustion chamber. There has been a large number of experimentations in industry and universities alike to better understand the dynamic and complex processes that occur inside a combustion chamber. This study concentrates on gas turbine combustors, as a whole, and formulates a theoretical design procedure for staged combustors, in particu lar. Not much of the literature currently available in the public domain provides intensive study on designing staged combustors. The work covers an extensive study o f the design methods applied in conventional combustor designs, which includes the reverse flow com bustor and the axial flow annular combustors. The knowledge acquired from this study is then applied to develop a theoretical design methodology for double staged (radial and axial) low emission annular combustors. Additionally, a model combustor is designed for each type, radial and axial, of staging using the developed methodology. A prediction of the performance of the model combustors is executed. The main conclusion is that the dimensions of the model combustors obtained from the developed design methodology are within the feasibility limits. The comparison between the radially staged and the axi ally staged combustor has yielded the predicted results such as a lower NOx prediction for the latter and a shorter combustor length for the former. The NOx emission results of the new combustor models are found to be in the range o f50-60ppm. However, the pre dicted NOx results are only very crude and need further detailed study.

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“…Singh [9] has mentioned that for modem civil engine combustors, the liner length to depth ratio is about 2. Therefore, the length of the liner can be calculated as follows: vi.…”

Section: M/s and 8 M/s Are Chosen And Then The Dome Section Areamentioning

confidence: 99%

“…This process is followed to main tain maximum reliability during altitude relight. Recently, a large number of combustor design methodologies have been reported in the literature [2][3][4][5][6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Design, Evaluation and Performance Analysis of Staged Low Emission Combustors

Khandelwal

Banjo

Sethi

2014

Journal of Engineering for Gas Turbines and Power

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“…Today, gas turbine engine combustor development has entered the stage of optimization to develop the most suitable combustor considering the interrelation of various technical requirements. Moreover, it is developed in the direction of composing a comprehensive and automated combustor design system that combines preliminary design, numerical simulation, optimization and experiment into one cycle (Khandelwal, 2012; Habibi et al , 2019).…”

Section: Introductionmentioning

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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Preliminary design and performance analysis of a low emission aero-derived gas turbine combustor

Cited by 2 publications

References 10 publications

Design, Evaluation and Performance Analysis of Staged Low Emission Combustors

Design, Evaluation and Performance Analysis of Staged Low Emission Combustors

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

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