Hostname: page-component-78c5997874-mlc7c Total loading time: 0 Render date: 2024-11-17T12:52:54.432Z Has data issue: false hasContentIssue false
  • English
  • Français

Effect of change in role of an aircraft on engine life

Published online by Cambridge University Press:  27 January 2016

A. Gad-Briggs ,
A. Haslam  and
P. Laskaridis
A. Gad-Briggs*
Affiliation:
Department of Power and Propulsion, School of Engineering, Cranfield University, Bedford, UK
A. Haslam*
Affiliation:
Department of Power and Propulsion, School of Engineering, Cranfield University, Bedford, UK
P. Laskaridis*
Affiliation:
Department of Power and Propulsion, School of Engineering, Cranfield University, Bedford, UK
*
agbriggs@hotmail.co.uk
a.haslam@cranfield.ac.uk
p.laskaridis@cranfield.ac.uk
Get access Rights & Permissions [Opens in a new window]

Abstract

New aircraft require years of development from concept to realisation and can be prone to delays. Consequently, military operators take existing fleets and operate them in a different role. The objective of this study is to examine the effect of operating a typical low bypass military fast jet engine, originally designed for a European theatre, in a hot and harsh climate. The specific purpose is to determine the effect on the high-pressure turbine blade life and the life- cycle cost of the engine.

A mission profile and respective performance conditions were analysed and modelled using an in-house performance tool. The flow conditions were simulated using ANSYS® FLUENT. A conjugated heat transfer solution was adopted to determine the blade metal temperature. The blade was modelled physically in 3D using SIMULIA® ABAQUS FEA software. The stresses were derived and used to calculate the temperature coupled low cycle fatigue and creep life.

A deterioration case was also studied to evaluate the effect of sand and dust ingestion. There was a significant life reduction of approximately 50% due to creep. The reduction in life was inversely proportional to the life cycle cost of the engine depending on the operating conditions. The results were compared with similar engines and summarised in the context of airworthiness regulations and component integrity.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1196 , October 2013 , pp. 1053 - 1070
Copyright
Copyright © Royal Aeronautical Society 2013 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Corbin, M.E.A. Security After 9/11: Strategy Choices and Budget Tradeoffs, Center for Defence Information, 2003, Washington, USA.Google Scholar
2. Matlack, C. Defence on Center Stage at Paris Air show, Bloomberg Business Week, Aviation, 2009, 15 June 2009.Google Scholar
3. Smith, M.E.B. A Parametric Physics Based Creep Life Prediction Approach To Gas Turbine Blade Conceptual Design (unpublished PhD thesis), Georgia Institute of Technology, Georgia, USA, 2008.Google Scholar
4. Lintern, G., Thomley, E., Nelson, B.E. and Roscoe, S.N. Content, Variety and Augmentation of Simulated Visual Scenes fort Teaching Air-to-Ground Attack, NAVTRAEQUIPCEN 81-C-0105-3, Department of the Navy, Naval Training Equipment Center, 1984, Orlando, Florida, USA.Google Scholar
5. Magnusson, S. Similarities and differences in psychophysiological reactions between simulated and real air-to-ground missions, Int J Aviation Psychology, 2002, 12, (1), pp 49–61.Google Scholar
6. Colle, H.A. and Reid, G.B. Estimating a mental workload redline in a simulated air-to-ground combat mission, Int J Aviation Psychology, 2005, 15, (4), pp 303–319.Google Scholar
7. Aungier, R.H. Turbine Aerodynamics: Axial-Flow and Radial-Inflow Turbine Design and Analysis, ASME, 2006, New York, USA.Google Scholar
8. Fielding, L. Turbine Design; The Effect on Axial Flow Turbine Performance of Parameter Variation, 2000, ASME, New York, USA.Google Scholar
9. Wilson, D.G. The Design of High-Efficiency Turbomachinery and Gas Turbines, 1991, 5th Ed, MIT Press, Cambridge, Massachusetts, USA.Google Scholar
10. Naeem, M., Singh, R. and Probert, R. Implications of Aero-Engine Deterioration for a for a High-Pressure Turbine’s Blade Low-Cycle Fatigue (LCF) Life Consumption, Int J Fatigue, 1999, 21, (08), pp 831–847.Google Scholar
11. Lefebvre, A.H. and Ballal, D.R. Gas Turbine Combustion – Alternative Fuels and Emissions, 3rd ed, CRC Press, 2010, USA.Google Scholar
12. Han, J.C., Dutta, S. and Ekkad, S. Gas Turbine Heat Transfer and Cooling Technology, Taylor and Francis, 2000, New York, USA.Google Scholar
13. Matsushita, T., Fecht, H.J., Wunderlich, R.K. and Seetharaman, S. Studies of the thermophysical properties of commercial CMSX-4 alloy, J Chemical Engineering, 2009, 54, pp 2584–2592.Google Scholar
14. Jéhanno, P., Heilmaier, M., Kestler, H., Böning, M., Venskutonis, A., Bewlay, B. and Jackson, M. Assessment of a powder metallurgical processing route for refractory metal silicide alloys, Metallurgical And Materials Transactions, 2005, 36A, pp 515–523.Google Scholar
15. Xu, J., Reuter, S. and Rothkegel, W. Tensile and bending thermo-mechanical fatigue testing on cylindrical and flat specimens of CMSX-4 for design of turbine blades, Int J Fatigue, 2008, 30, pp 363–371.Google Scholar
16. High-Temperature High-Strength Nickel Based Super Alloys, Supplement, (393), 1995, Nickel Development Institute.Google Scholar
17. Suresh, S. Fatigue of Materials, 1998, Second Edition, Cambridge University Press, Cambridge, UK.Google Scholar
18. Gad-Briggs, A. Effect of Change in Role of an Aircraft on Engine Life (unpublished thesis), Cranfield University, Cranfield, UK, 2011.Google Scholar