Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
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R K Mishra
,
Prashant Kumar
Abstract
Pack aluminization of high pressure turbine nozzle guide vane of an aero gas turbine engine has been carried out following a well defined systematic procedure. The process parameters are first optimized on dummy vanes and optimized process is followed for the actual vanes for evaluation and testing. Visual and binocular examination followed by metallurgical evaluation have been carried out to validate the process and to establish the adequacy and correctness of the coating. The coated vanes are then evaluated through engine level tests for performance and durability. The results of engine level tests and inspection post accelerated mission test cycles ensure that the vanes with aluminide coating can withstand severe engine operating cycles without any damage or failure which would otherwise would have happened without the coating. The condition of vanes post endurance test is also an indication of enhanced life of the vanes with coating.
References
1. Hour J, Wicks BJ, Antoniou RA. An investigation of fatigue failures of turbine blades in a gas turbine engine by mechanical analysis. J Eng Fail Anal. 2002 April;9(2):201–11.10.1016/S1350-6307(01)00005-XSearch in Google Scholar
2. Kazempour-Liacy H, Abouali S, Akbari-Garakani M. Failure analysis of a first stage gas turbine blade. J Eng Fail Anal. 2011 January;18(1):517–22.10.1016/j.engfailanal.2010.09.040Search in Google Scholar
3. Suresh S. Fatigue of materials, 2nd ed. Cambridge: Cambridge University Press, 2003:256–57.Search in Google Scholar
4. Bannantine JA, Comer JJ, Handrock JL. Fundamental of metal fatigue analysis. Upper Saddle River, NJ: Prentice Hall Inc; 1990. p. 40–87.Search in Google Scholar
5. Cohen H, Rogers GFC, Saravanamuttoo HIH. Gas turbine theory. Boston, MA: Addition Wesley Longman, 1996.Search in Google Scholar
6. Arthur H. Lefebvre, GAS turbine combustion. London: CRC Press, 1998.Search in Google Scholar
7. Muduli SK, Mishra RK, Satpathy RK, Chandel S. Effect of operating conditions on the performance parameters of a highly loaded annular combustor. Int J Turbo Jet Engines. 2014;32:25–32. DOI:10.1515/tjj-2014-0016. 2015.Search in Google Scholar
8. Mishra RK. Influence of upstream flow distortion on the performance of an aero gas turbine combustor. XIX International Symposium on Air Breathing Engines, Montreal, Canada, Sept 2009.Search in Google Scholar
9. Mishra RK, Bhat MN, Navindgi RD, Sampathkumaran TK. Effect of fuel-air ratio on the performance of a short annular aero gas turbine combustor. 6th National Conference on Air Breathing Engines. Bangalore, India, 2003.Search in Google Scholar
10. Mishra RK, Chandel S. Soot formation and its effect in an aero gas turbine combustor. Int J Turbo Jet Engines. ISSN (Online) 2191-0332, ISSN (Print) 0334-0082 DOI:10.1515/tjj-2016-0062, October 2016.Search in Google Scholar
11. Meher-Homji CB, Gabriles G. Gas turbine blade failures-causes, avoidance and trouble shooting. Proceedings of 27th Turbomachinery Symposium, 1995.Search in Google Scholar
12. Mishra RK, Thomas J, Srinivasan K, Nandi V, Bhat R. Failure analysis of nozzle guide vane of a low pressure turbine in an aero gas turbine engine. J Fail Anal Prev., 2014;14:578–587. DOI:10.1007/s11668-014-9858-7Search in Google Scholar
13. Eliaz N, Shemesh G, Latanision RM. Hot corrosion in gas turbine components. J Eng Fail Anal. 2002 Feb;9:31–43.10.1016/S1350-6307(00)00035-2Search in Google Scholar
14. Meetham GW, Rolls-Royce Plc, Derby, England. Recent advances and developments in coatings. Proceedings of the seminar on advances in Plating and coating technology. Series 4, Organized by Hindustan Aeronautics Limited, 20–22 July, 1989. Bangalore, India.Search in Google Scholar
15. Krishnamohan Rao Y, Krishnadas Nair CG. High temperature protective coatings for aeroengine gas turbine applications. Proceedings of the seminar on advances in Plating and coating technology. Series 4. Organized by Hindustan Aeronautics Limited, 20–22 July, 1989. Bangalore, India.Search in Google Scholar
16. Bernstein HL, Allen JM, 1992. A review of high temperature coatings for combustion turbine blades. Proceedings of the Steam and Combustion Turbine-Blading Conference and Workshop-1992, EPRI TR-102061, Research Project 1856-09, pp. 6–19-6-47.Search in Google Scholar
17. Committee on Coatings for High-Temperature Structural Materials. Coatings for high-temperature structural materials: trends and opportunities. Washington, D.C.: National Academy Press, 1996. National Materials Advisory Board Commission on Engineering and Technical Systems, National Research Council.Search in Google Scholar
18. Ahlatci H. Use of coatings for hot corrosion and erosion protection in turbine hot section components. J Eng Sci. 1999;5:885–92.Search in Google Scholar
19. Nicholls JR, Rickerby DS. “Materials and processes for high temperature surface engineering.” High Temperature Power Plant and Process Plant Applications Session as held at the Materials Congress’98, 1998.Search in Google Scholar
20. Goward GW. Progress in coatings for gas turbine airfoils. Surf Coat Technol. 1998;108:73–79.10.1016/S0257-8972(98)00667-7Search in Google Scholar
21. Nicholls JR. Advances in coating design for high-performance gas turbines. MRS Bull. 2003;28:659–70.10.1557/mrs2003.194Search in Google Scholar
22. Rajendran R. Gas turbine coatings–an overview. Eng Fail Anal. 2012;26:355–69.10.1016/j.engfailanal.2012.07.007Search in Google Scholar
23. Pomeroy MJ. Coatings for gas turbine materials and long term stability issues. Mater Des. 2005;26:223–31.10.1016/j.matdes.2004.02.005Search in Google Scholar
24. García de la Yedra A, Martín-Meizoso A, Rodríguez Martín R, Pedrejón JL. Thermo-mechanical fatigue behaviour and life prediction of C-1023 nickel based superalloy. Int J Eng, Sci Technol. 2011;3:88–101.10.4314/ijest.v3i6.8Search in Google Scholar
25. DeMasi-Marcin JT, Gupta DK. Protective coatings in the gas turbine engine. Surf Coat Technol. 1994;68:1–9.10.1016/0257-8972(94)90129-5Search in Google Scholar
26. Gurrappa I. Identification of hot corrosion resistant MCrAlY based bond coatings for gas turbine engine applications. Surf Coat Technol. 2001;139:272–83.10.1016/S0257-8972(00)01156-7Search in Google Scholar
27. Vaßen R, Jarligo MO, Steinke T, Mack DE, Stöver D. Overview on advanced thermal barrier coatings. Surf Coat Technol. 2010;205:938–42.10.1016/j.surfcoat.2010.08.151Search in Google Scholar
28. Padture NP, Gell M, Jordan EH. Thermal barrier coatings for gas-turbine engine applications. Science. 2002;296:280–84.10.1126/science.1068609Search in Google Scholar PubMed
29. Hetmańczyk M, Swadźba L, Mendala B. Advanced materials and protective coatings in aero-engines application. J Achievements Mater Manuf Eng. 2007;24:372–81.Search in Google Scholar
30. MIL-HDBK-506(AT), Handbook process for coating, pack cementation, chrome aluminide, Department of Defense, 10 April 1998.Search in Google Scholar
31. Mevrel R, Duret C, Pichoir R. Pack cementation processes. Mater Sci Technol. 1986;2(3):201–06.10.1179/mst.1986.2.3.201Search in Google Scholar
32. Shankar V, Terrance ALE, Venkadesan S, Annapurna J. The effect of diffusion barrier formation on the kinetics of aluminizing in inconel-718. J Mater Sci. 1994;29(20):5424–28.10.1007/BF01171556Search in Google Scholar
33. Zielińska M, Sieniawski J, Yavorska M, Motyka M. Influence of chemical composition of nickel based super-alloy on the formation of aluminide coatings. Arch Metall Mater. 2011;56(1):193–97.10.2478/v10172-011-0023-ySearch in Google Scholar
© 2017 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
Articles in the same Issue
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
