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International Journal of Aerospace Engineering
Volume 2012, Article ID 217463, 6 pages
Research Article

Assessment of Combustor Working Environments

Aerospace Research, Gas Turbine Laboratory, The National Research Council of Canada, 1200 Montreal Road, M-10, Ottawa, ON, Canada K1A 0R6

Received 10 March 2012; Accepted 29 June 2012

Academic Editor: Victor Giurgiutiu

Copyright © 2012 Leiyong Jiang and Andrew Corber. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


In order to assess the remaining life of gas turbine critical components, it is vital to accurately define the aerothermodynamic working environments and service histories. As a part of a major multidisciplinary collaboration program, a benchmark modeling on a practical gas turbine combustor is successfully carried out, and the two-phase, steady, turbulent, compressible, reacting flow fields at both cruise and takeoff are obtained. The results show the complicated flow features inside the combustor. The airflow over each flow element of the combustor can or liner is not evenly distributed, and considerable variations, ±25%, around the average values, are observed. It is more important to note that the temperatures at the combustor can and cooling wiggle strips vary significantly, which can significantly affect fatigue life of engine critical components. The present study suggests that to develop an adequate aerothermodynamics tool, it is necessary to carry out a further systematic study, including validation of numerical results, simulations at typical engine operating conditions, and development of simple correlations between engine operating conditions and component working environments. As an ultimate goal, the cost and time of gas turbine engine fleet management must be significantly reduced.