Access the full text.
Sign up today, get DeepDyve free for 14 days.
Journal of Engineering for Gas Turbines and Power, 6
H. Versteeg, W. Malalasekera (2007)
An introduction to computational fluid dynamics - the finite volume method
P. Stuttaford, P. Rubini (1996)
Preliminary Gas Turbine Combustor Design Using a Network ApproachJournal of Engineering for Gas Turbines and Power-transactions of The Asme, 119
F. Mare, W. Jones, K. Menzies (2004)
Large eddy simulation of a model gas turbine combustorCombustion and Flame, 137
Raja Marudhappan, U. Chandrasekhar, K. Reddy (2017)
Optimization of Simplex Atomizer Inlet Port Configuration through Computational Fluid Dynamics and Experimental Study for Aero-Gas Turbine ApplicationsJournal of The Institution of Engineers (India): Series C, 98
Y. Khavkin (1996)
Combustion System Design
A. Mellor, K. Fritsky (1990)
Turbine combustor preliminary design approachJournal of Propulsion and Power, 6
C. Mark, A. Selwyn (2016)
Design and analysis of annular combustion chamber of a low bypass turbofan engine in a jet trainer aircraftPropulsion and Power Research, 5
A. Fossi, A. deChamplain, B. Akih-Kumgeh (2015)
Unsteady RANS and scale adaptive simulations of a turbulent spray flame in a swirled-stabilized gas turbine model combustor using tabulated chemistryInternational Journal of Numerical Methods for Heat & Fluid Flow, 25
A. Bahramian, Mozhdeh Maleki, B. Medi (2017)
CFD Modeling of Flame Structures in a Gas Turbine Combustion Reactor: Velocity, Temperature, and Species DistributionInternational Journal of Chemical Reactor Engineering, 15
D. Veynante, L. Vervisch (2002)
Turbulent combustion modelingVKI Lecture Series
M. Sosnowski, J. Krzywański, R. Gnatowska (2017)
Polyhedral meshing as an innovative approach to computational domain discretization of a cyclone in a fluidized bed CLC unit, 14
A. Conrado, P. Lacava, A. Carlos, Pereira Filho, Departemento Física, Milton Sanches (2004)
BASIC DESIGN PRINCIPLES FOR GAS TURBINE COMBUSTOR
A. Tyliszczak, A. Bogusławski, D. Nowak (2016)
Numerical simulations of combustion process in a gas turbine with a single and multi-point fuel injection systemApplied Energy, 174
Won-Wook Kim, S. Menon, H. Mongia (1999)
Large-Eddy Simulation of a Gas Turbine Combustor FlowCombustion Science and Technology, 143
W. Anderson, D. Bonhaus (1994)
An implicit upwind algorithm for computing turbulent flows on unstructured gridsComputers & Fluids, 23
D. Crocker, D. Nickolaus, Clifford Smith (1998)
CFD Modeling of a Gas Turbine Combustor From Compressor Exit to Turbine InletJournal of Engineering for Gas Turbines and Power-transactions of The Asme, 121
F. Sierra, J. Kubiak, G. Gonzalez, G. Urquiza (2005)
Prediction of temperature front in a gas turbine combustion chamberApplied Thermal Engineering, 25
W. Jones, B. Launder (1972)
The prediction of laminarization with a two-equation model of turbulenceInternational Journal of Heat and Mass Transfer, 15
W. Shyy, S. Correa, M. Braaten (1988)
Computation of Flow in a Gas Turbine CombustorCombustion Science and Technology, 58
W. Zeng, Shuang Liang, Hai-xia Li, Hong-an Ma (2013)
Chemical kinetic simulation of kerosene combustion in an individual flame tubeJournal of Advanced Research, 5
K. Kuo, R. Acharya (2012)
Fundamentals of Turbulent and Multiphase Combustion
Fagner Dias, M. António, R. Nascimento, Lucilene Rodrigues (2014)
Reference Area Investigation in a Gas Turbine Combustion Chamber Using CFDJournal of Mechanical Engineering and Automation, 4
S. Goebel, N. Abuaf, J. Lovett, C. Lee (1993)
Measurements of Combustor Velocity and Turbulence Profiles
The purpose of this paper is to formulate a structured approach to design an annular diffusion flame combustion chamber for use in the development of a 1,400 kW range aero turbo shaft engine. The purpose is extended to perform numerical combustion modeling by solving transient Favre Averaged Navier Stokes equations using realizable two equation k-e turbulence model and Discrete Ordinate radiation model. The presumed shape β-Probability Density Function (β-PDF) is used for turbulence chemistry interaction. The experiments are conducted on the real engine to validate the combustion chamber performance.Design/methodology/approachThe combustor geometry is designed using the reference area method and semi-empirical correlations. The three dimensional combustor model is made using a commercial software. The numerical modeling of the combustion process is performed by following Eulerian approach. The functional testing of combustor was conducted to evaluate the performance.FindingsThe results obtained by the numerical modeling provide a detailed understanding of the combustor internal flow dynamics. The transient flame structures and streamline plots are presented. The velocity profiles obtained at different locations along the combustor by numerical modeling mostly go in-line with the previously published research works. The combustor exit temperature obtained by numerical modeling and experiment are found to be within the acceptable limit. These results form the basis of understanding the design procedure and opens-up avenues for further developments.Research limitations/implicationsInternal flow and combustion dynamics obtained from numerical simulation are not experimented owing to non-availability of adequate research facilities.Practical implicationsThis study contributes toward the understanding of basic procedures and firsthand experience in the design aspects of combustors for aero-engine applications. This work also highlights one of the efficient, faster and economical aero gas turbine annular diffusion flame combustion chamber design and development.Originality/valueThe main novelty in this work is the incorporation of scoops in the dilution zone of the numerical model of combustion chamber to augment the effectiveness of cooling of combustion products to obtain the desired combustor exit temperature. The use of polyhedral cells for computational domain discretization in combustion modeling for aero engine application helps in achieving faster convergence and reliable predictions. The methodology and procedures presented in this work provide a basic understanding of the design aspects to the beginners working in the gas turbine combustors particularly meant for turbo shaft engines applications.
Aircraft Engineering and Aerospace Technology: An International Journal – Emerald Publishing
Published: Jan 30, 2019
Keywords: CFD; Annular combustor; Reference area; Turbo-shaft
Read and print from thousands of top scholarly journals.
Already have an account? Log in
Bookmark this article. You can see your Bookmarks on your DeepDyve Library.
To save an article, log in first, or sign up for a DeepDyve account if you don’t already have one.
Copy and paste the desired citation format or use the link below to download a file formatted for EndNote
Access the full text.
Sign up today, get DeepDyve free for 14 days.
All DeepDyve websites use cookies to improve your online experience. They were placed on your computer when you launched this website. You can change your cookie settings through your browser.