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


  • Z Saboohi
  • F Ommi
  • A Fakhrtabatabaei



Combustor design is the most unreliable and challenging portion in the design process of a gas turbine. To ensure the proper performance, many experimental tests must be performed on a combustor in the industry. The above mentioned design phase is costly and time consuming. This paper focused on an automated and augmented conceptual design methodology for conventional combustors. The design tool developed for this study employs empirical and semi-empirical models which include two main parts of the combustor, the reference diameter and area as well as the component design. The necessity of this work arose from an urgent need for comprehensive and fast generation data in the conceptual design phase of a combustion chamber. This automated and comprehensive tool, equipped with the capacity to provide many details, has a considerable impact on the reduction of further experimental effort. Also, the said tool is equipped with a geometrical model generation section that has application in the future design phases, e.g., detail design.


Sawyer, J.W., Gas Turbine Engineering Handbook: Theory & Design, 3rd edn., Gas Turbine Publications, Norwalk, 1985. ISBN: 0-937506-14-1.

Lefebvre, A.H., Gas Turbine Combustion Alternative Fuels and Emissions. 3rd edn., CRC Press, NY, 2010. ISBN: 978-1-4200-8604-1.

Walsh, P.P. and Fletcher, P., Gas Turbine Performance. 2nd edn., John Wiley & Sons, Oxford, 2004. ISBN: 0-632-06434-X.

Mattingly, J.D., Aircraft Engine Design. 2nd edn., AIAA, Reston, 2002. ISBN: 1-56347-538-3.

Meller, A.M., Design of Modern Turbine Combustor. Academic Press, London, 1990. ISBN: 978-0124900554.

Lefebvre, A.H., Fuel Effects on Gas Turbine Combustion Liner Temperature, Pattern Factor, and Pollutant Emissions, Journal of Aircraft, 21(11), 1984, 887-898.

Mellor, A.M. and Fritsky, K.J., Turbine Combustor Preliminary Design Approach, Journal of Propulsion and Power, 6(3), 1990, 334-343.

Mohammad, B.S., and Jeng, S.M., Design Procedures and a Developed Computer Code for Preliminary Single Annular Combustor Design. Proc. 45th AIAA Conference and Exhibit, Denver, 2009 (AIAA 2009-5208).

Khandelwal, B., Yan, M., Hedge, G., Sethi, V. and Singh, R., Design Procedure of a Reverse Flow Combustor for a Helicopter Engine with High Temperature Rise, SAE Technical Paper, No. 2011-01-2562, 2011.

Hegde, G.B., Khandelwal, B., Sethi, V. and Singh, R., Design, Evaluation and Performance Analysis of Staged Low Emission Combustors. Proc. ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, Copenhagen, 2012, 867-875.

Conrado, A.C., Lacava, P.T., Filho, A.C.P. and Sanchez M.S., Basis Design Principles for Gas Turbine Combustor. Proc. of the 10th Brazilian Congress of Thermal Science and Engineering, Rio de Janeiro, 2004.

Rezvani, R., Denny, R.K. and Mavris, D.N., A Design-Oriented Semi-Analytical Emissions Prediction Method for Gas Turbine Combustors. 47th AIAA Aerospace Sciences Meeting, Orlando, 2009 (AIAA 2009-704).

Tietz, S. and Behrendt, T., Development and Application of a Pre-Design Tool for Aero-Engine Combustors, CEAS Aeronautical Journal, 2(1-4), 2011, 111-123.

Pegemanifar, N. and Pfitzer, M., Development of a Combustion Chamber Design Methodology and Automated of the Design Process. Proc. 25th International Congress of the Aeronautical Sciences, Hamburg, 2006.

Pegemanifar, N., von der Bank, R., Zedda, M., Pfitzer, M., and Nicolas S., Design Methodologies and CFD Methods for the Development of Low Emission Combustion Systems in Aero-Engines. Proc. 8th World Congress on Computational Mechanics, Venice, 2008.

Pegemanifar, N. and Pfitzer, M., State of the Art Combustor Design Utilizing the Preliminary Combustor Design System Pre-codes. Proc. of ASME Turbo Expo 2008: Power for Land, Sea and Air, Berlin, 2008.

Bragg, S.L., Application of Reaction Rate Theory to Combustion Chamber Analysis, Aeronautical Research Council, London, 1953.

Odgers, J. and Carrier C., Modeling of Gas Turbine Combustors; Considerations of Combustion Efficiency and Stability, Journal of Gas Turbines and Power, 95(2), 1973, 105-113.

Rezvani, R., A Conceptual Methodology for the Prediction of Engine Emissions, PhD thesis, Georgia Institute of Technology, 2010.

Mavris, D., Enhanced Emission Prediction Modeling and Analysis for Conceptual Design, Final Report for NASA grant NNX07AO08A 17, 2010.

Tai, J., A Multidisciplinary Design Approach to Size Stopped Rotor/Wing Configurations Using Reaction Derive and Circulation Control, PhD thesis, Georgia Institute of Technology, 1998.

Chen, R.H. and Driscoll, J.F., The Role of the Recirculation Vortex in Improving Fuel-Air Mixing within Swirling Flames. Symposium (International) on Combustion, Vol. 22, No. 1, Elsevier, 1989.

Knight, H.A. and Walker, R.B., The Component Pressure Losses in Combustion Chambers. No. NGTER-143. Gt. Brit. National Gas Turbine Establishment, Farnborough, Hants, England, 1953.

Charest, M., Design Methodology for a Lean Premixed Prevaporized Can Combustor, MS thesis, Carlton University, 2005.

Dodds, W., Engine and Aircraft Technologies to Reduce Emissions. UC Technology Transfer Symposium, Dreams of Flight, San Diego, 2002.



How to Cite

Saboohi, Z., Ommi, F. and Fakhrtabatabaei, A. (2016) “Development of an Augmented Conceptual Design Tool for Aircraft Gas Turbine Combustors”, The International Journal of Multiphysics, 10(1), pp. 53-74. doi: 10.21152/1750-9548.10.1.53.