Hostname: page-component-cd9895bd7-hc48f Total loading time: 0 Render date: 2024-12-19T01:56:08.542Z Has data issue: false hasContentIssue false
  • English
  • Français

Assessment of degradation equivalent operating time for aircraft gas turbine engines

Published online by Cambridge University Press:  09 January 2020

O. Alozie Open the ORCID record for O. Alozie [Opens in a new window] ,
Y.G. Li ,
M. Diakostefanis ,
X. Wu ,
X. Shong  and
W. Ren
O. Alozie*
Affiliation:
School of Aerospace, Transport and Manufacturing Cranfield UniversityMK43 0AL, Bedford UK
Y.G. Li
Affiliation:
School of Aerospace, Transport and Manufacturing Cranfield UniversityMK43 0AL, Bedford UK
M. Diakostefanis
Affiliation:
School of Aerospace, Transport and Manufacturing Cranfield UniversityMK43 0AL, Bedford UK
X. Wu
Affiliation:
Shenyang Engine Design and Research Institute (SEDRI) Aircraft Engine Corporation of China (AECC) Beijing China
X. Shong
Affiliation:
Shenyang Engine Design and Research Institute (SEDRI) Aircraft Engine Corporation of China (AECC) Beijing China
W. Ren
Affiliation:
Shenyang Engine Design and Research Institute (SEDRI) Aircraft Engine Corporation of China (AECC) Beijing China
*
[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper presents a novel method for quantifying the effect of ambient, environmental and operating conditions on the progression of degradation in aircraft gas turbines based on the measured engine and environmental parameters. The proposed equivalent operating time (EOT) model considers the degradation modes of fouling, erosion, and blade-tip wear due to creep strain, and expresses the actual degradation rate over the engine clock time relative to a pre-defined reference condition. In this work, the effects of changing environmental and engine operating conditions on the EOT for the core engine booster compressor and the high-pressure turbine were assessed by performance simulation with an engine model. The application to a single and multiple flight scenarios showed that, compared to the actual engine clock time, the EOT provides a clear description of component degradation, prediction of remaining useful life, and sufficient margin for maintenance action to be planned and performed before functional failure.

Keywords

Gas turbinePerformanceDegradationFoulingErosionCreepEquivalent Operating TimePrognosticsRemaining useful life
Type
Research Article
Information
The Aeronautical Journal , Volume 124 , Issue 1274 , April 2020 , pp. 549 - 580
Copyright
© Royal Aeronautical Society 2020

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.)

Footnotes

A version of this paper was presented at the 24th ISABE Conference in Canberra, Australia, September 2019.

References

REFERENCES

James, W. and O’Dell, P. Derated climb performance in large civil aircraft, article 6. Boeing Performance and Flight Operations Engineering Conference. 2005.Google Scholar
Donaldson, R., Fischer, D., Gough, J. and Rysz, M. Economic impact of derated climb on large commercial engines, 2007 Boeing Performance and Flight Operations Engineering Conference, 2007, pp 8.1–8.11.Google Scholar
Yong Huang, Z., Wagner, D., Bathias, C. and Louis Chaboche, J.Cumulative fatigue damage in low cycle fatigue and gigacycle fatigue for low carbon-manganese steel, Int J Fatigue, Elsevier Ltd; 2011; 33, (2), 115–121. doi: 10.1016/j.ijfatigue.2010.07.008CrossRefGoogle Scholar
Janawitz, J., Masso, J. and Childs, C. Heavy-Duty Gas Turbine Operating and Maintenance Considerations, GER-3620M. GE Power & Water, 2015, Atlanta, GA.Google Scholar
Lee, J. Total Operating Activities of Gas Turbine Components - Total Equivalent Operating Hours (TEOH), International Gas Turbine and Aeroengine Congress and Exhibition, 1999, Indianapolis, Indiana, pp 1–4.CrossRefGoogle Scholar
Zhou, D., Wei, T., Zhang, H., Ma, S. and Weng, S.A damage evaluation model of turbine blade for gas turbine, J Engineering for Gas Turbines and Power, 2017, 139, (September), 1–9. doi: 10.1115/1.4036060CrossRefGoogle Scholar
Abdul Ghafir, M.F., Li, Y.G., Wang, L. and Zhang, W.Impact analysis of aero-engine performance parameter variation on hot section’s creep life using creep factor approach, AIAA, 2011, 16, (9), 1–12.Google Scholar
Eshati, S., Abu, A., Laskaridis, P. and Haslam, A.Investigation into the effects of operating conditions and design parameters on the creep life of high pressure turbine blades in a stationary gas turbine, Engine, 2011, 15, (3), 237–247.Google Scholar
Hanumanthan, H., Stitt, A., Laskaridis, P. and Singh, R.Severity estimation and effect of operational parameters for civil aircraft jet engines, Proceedings of the Institution of Mechanical Engineers, Part G: J Aerospace Engineering., 2012, 226, (12), 1544–1561. doi: 10.1177/0954410011424854CrossRefGoogle Scholar
Gotoh, J., Yasushi, H., Shigeo, S. and Hiraku, I.US007065471B2: Method and System for Diagnosing State of Gas Turbine, United States: United States Patent; 2006.Google Scholar
Wan, A., Gu, F., Chen, J., Zheng, L., Hall, P., Ji, Y. and Gu, X.Prognostics of gas turbine: A condition-based maintenance approach based on multi-environmental time similarity, Mech Systems and Signal Processing., 2018; 109, 150–165. doi: 10.1016/j.ymssp.2018.02.027CrossRefGoogle Scholar
Seemann, R., Langhans, S., Schilling, T. and Gollnick, V. Modeling the life cycle cost of jet engine maintenance, Deutscher Luft- und Raumfahrtkongress, 2011, (September), 663–672.Google Scholar
Ackert, S. Engine maintenance concepts for financiers, Aircraft Monitor 2011, (2), 30. Google Scholar
Wensky, T., Winkler, L. and Friedrichs, J. Environmental influences on engine performance degradation, Proceedings of ASME Turbo Expo 2010: Power for Land, Sea and Air, Glasgow, UK, 2010, pp 1–6.CrossRefGoogle Scholar
Clarkson, R. and Simpson, H.Maximising airspace use during volcanic eruptions: Matching engine durability against ash cloud occurrence, Sto-Mp-Avt-272. 2017, (June), 1–20. doi: 10.14339/STO-MP-AVT-272Google Scholar
Prata, A.T., Dacre, H.F., Irvine, E.A., Mathieu, E., Shine, K.P. and Clarkson, R.J.Calculating and communicating ensemble-based volcanic ash dosage and concentration risk for aviation, Meteorological Applications., 2019, 26, (2), 253–266. doi: 10.1002/met.1759CrossRefGoogle Scholar
Zaita, A.V., Buley, G. and Karlsons, G.Performance deterioration modeling in aircraft gas turbine engines, J Engineering for Gas Turbines and Power, 1998, 120, (2), 6. doi: 10.1115/1.2818128CrossRefGoogle Scholar
Bojdo, N. and Filippone, A. Effect of desert particulate composition on helicopter engine degradation rate, 40th European Rotorcraft Forum, Southampton, UK, 2015, doi: 10.13140/2.1.2959.8086CrossRefGoogle Scholar
Li, Y.G. and Singh, R. An advanced gas turbine gas path diagnostic system – Pythia, VII International Symposium on Air Breathing Engines, Munich, Germany. 2005, (ISABE-2005-1284), 1–13.Google Scholar
Meher-homji, C.B., Focke, A.B. and Wooldridge, M.B. Fouling of axial flow compressors - causes, effcets, detention, and control, Proceedings of the Eighteenth Turbomachinery Symposium, 1989 55–76.Google Scholar
Igie, U., Goiricelaya, M. and Nalianda, D.Aero engine compressor fouling effects for short- and long-haul missions, Proceedings of the Institution of Mechanical Engineers, Part G: J Aerospace Engineering, 2016, 230, (7), 1312–1324. doi: 10.1177/0954410015607897CrossRefGoogle Scholar
Israel, R. and Rosner, D.E.Use of a generalized stokes number to determine the aerodynamic capture efficiency of non- stokesian particles from a compressible gas flow, Aerosol Science and Technology, 1982, 2, (1), 45–51. doi: 10.1080/02786828308958612CrossRefGoogle Scholar
Bojdo, N., Ellis, M., Filippone, A. and Pawley, A.Particle-vane interaction probability in gas turbine engines, J Turbomachinery, 2019, 141, (September), 1–13. doi: 10.1115/1.4043953CrossRefGoogle Scholar
Shrinivas Sreedharan, S. and Tafti, D.K.Effect of blowing ratio on early stage deposition of syngas ash on a film-cooled vane leading edge using large eddy simulations, J Turbomachinery, 2013, 135, (6), 061005. doi: 10.1115/1.4025153CrossRefGoogle Scholar
El-Batsh, H.Modeling Particle Deposition on Compressor and Turbine Blade Surfaces. Vienna University of Technology, 2001, Wien, Austria.Google Scholar
Hamed, A., Tabakoff, W. and Singh, D.Modeling of compressor performance deterioration due to erosion, Int J Rotating Machinery., 1998, 4, (4), 243–248.CrossRefGoogle Scholar
Suman, A., Morini, M., Aldi, N., Casari, N., Pinelli, M. and Spina, P.R.A compressor fouling review based on an historical survey of ASME turbo expo papers, J Turbomachinery, 2017, 139, (4), 041005. doi: 10.1115/1.4035070CrossRefGoogle Scholar
Hamed, A. and Tabakoff, W.Turbine blade surface deterioration by erosion, J Turbomachinery, 2005, 127, (3), 445. doi: 10.1115/1.1860376CrossRefGoogle Scholar
Diakunchak, I.S.Performance deterioration in industrial gas turbines, J Engineering for Gas Turbines and Power, 1992, 114, (2), 161. doi: 10.1115/1.2906565CrossRefGoogle Scholar
Meher-Homji, C.B., Chaker, M.A. and Motiwala, H.M. Gas Turbine Performance Deterioration, 30th Turbomachinery Symposium, Texas A&M University, Texas, 2001; 139–176.Google Scholar
Jacobson, D.H. Gas Turbines, Major Process Equipment Maintenance and Repair, Exxon Co.; 1997, pp 442–479.Google Scholar
van der Walt, J.P. and Nurick, A.Erosion of dust-filtered helicopter turbine engines. Part 1: Basic theoretical considerations, J Aircraft, 1995, 32, (1), pp 106–111. doi: 10.2514/3.56919. Google Scholar
Smeltzer, C.E., Gulden, M.E., McElmury, S.S. and Compton, W.A. Mechanisms of Sand and Dust Erosion in Gas Turbine Engines, Fort Eustis, Virginia, 1970. doi:AD0876584CrossRefGoogle Scholar
Kim, J., Dunn, M.G., Baran, A.J., Wade, D.P. and Tremba, E.L.Deposition of volcanic materials in the hot sections of two gas turbine engines, J Engineering for Gas Turbines and Power, 1993, 115, (3), 641. doi: 10.1115/1.2906754CrossRefGoogle Scholar
General Electric Aircraft Engines. HPT Clearance Control - Intelligent Engine Systems - Phase 1, Cincinnati, Ohio; 2005.Google Scholar
Abu, A.O., Eshati, S., Laskaridis, P.,and Singh, R.Aero-engine turbine blade life assessment using the Neu/Sehitoglu damage model, Int J Fatigue, 2014, 61. doi: 10.1016/j.ijfatigue.2013.11.015Google Scholar
Baskharone, E.A.Principles of Turbomachinery in Air-Breathing Rngines. Cambridge University Press, 2006, New York.CrossRefGoogle Scholar
Li, Y.G. Training future engineers on gas turbine gas path diagnostics using Pythia, Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, Dusseldorf, Germany, June 16-20, 2014; 2014, pp 1–10.Google Scholar
SAFRAN Snecma - Communications Department. Commercial Aircraft Engines CFM56-7B, Cedex, France; 2011, p. 2.Google Scholar
Li, Y.G., Pilidis, P. and Newby, M.A. An adaptation approach for gas turbine design-point performance simulation, J Engineering for Gas Turbines and Power, 2006, 128, (4), 789–795. doi: 10.1115/1.2136369CrossRefGoogle Scholar
Lo Gatto, E., Li, Y.G. and Pilidis, P. Gas turbine off-design performance adaptation using a genetic algorithm, ASME Turbo Expo 2006: Power for Land, Sea, and Air, Barcelona, Spain, 2006.CrossRefGoogle Scholar
Jasmani, M.S., Li, Y.G. and Ariffin, Z.Measurement selections for multicomponent gas path diagnostics using analytical approach and measurement subset concept, J Engineering for Gas Turbines and Power, 2011, 133, (11), 111701. doi: 10.1115/1.4002348CrossRefGoogle Scholar
Zaba, T.B. and Lombardi, P.Experience in the operation of air filters in gas turbine installations, Brown Boveri Review, Baden, Switzerland, 1984.Google Scholar
Facility for Airborne Atmospheric Measurement. Natural Environment Research Council., Met Office. FAAM B702 FENNEC flight, number 4: Airborne atmospheric measurements from core and non-core instrument suites on board the BAEou, Morocco, during SAMUM 2006, Tellus, Series B: Chemical and Physical Meteorology, 2009, 61, (1), 32–50. doi: 10.1111/j.1600-0889.2008.00385.xCrossRefGoogle Scholar
Kandler, K., Schütz, L., Deutscher, C., Ebert, M., Hofmann, H., Jäckel, S., Jaenicke, R., Knippertz, P., Lieke, K., Massling, A., Petzold, A., Schladitz, A., Weinzierl, B., Wiedensohler, A., Zorn, S. and Weinbruch, S.Size distribution, mass concentration, chemical and mineralogical composition and derived optical parameters of the boundary layer aerosol at Tinfou, Morocco, during SAMUM 2006, Tellus, Series B: Chemical and Physical Meteorology, 2009, 61, (1), 32–50. doi: 10.1111/j.1600-0889.2008.00385.xCrossRefGoogle Scholar
Droplet Measurement Technologies. Passive Cavity Aerosol Spectrometer Probe (PCASP-100x) Operator Manual, Boulder, USA, 2011.Google Scholar
Sasahara, O. JT9D Engine/Module performance detrioration results from back to back testing, International Symposium on Air Breathing Engines, Beijing, China, 1985, pp 528–535.Google Scholar
Aircraft Commerce. Aircraft owner’s & operator’s guide: B737NG family, Aircraft Commerce. 2010, 3–30.Google Scholar