Design of experiments for verification of computational life prediction methods

Abstract


The failure of heavily loaded rotating parts of aviation gas turbine engines may bring about dangerous consequences. The life of such parts is limited with the use of computational and experimental methods. Computational life prediction methods that are used without carrying out life-cycle tests of engine parts or assemblies should be substantiated experimentally. The best option for verifying the computational methods is to use the results of cyclic tests of model disks. These tests make it possible to reproduce loading conditions and surface conditions that correspond to those of real disks, and the data on the load history and material properties make it possible to simulate stress-strain behavior of disks under test conditions by calculation. This paper shows the process of planning such tests. It is assumed that the tests will be carried out in two stages - before and after the initiation of a low-cycle fatigue crack. A number of criteria are formulated that the geometry of model disks and their loading conditions are to satisfy. Based on these criteria, model disks were designed and the conditions for their testing were selected.


About the authors

O. V. Samsonova

UEC-Aviadvigatel Stock Company

Author for correspondence.
Email: olga.samsonova.avid@gmail.com

Russian Federation

Engineer of Rotor and Blades Structural Analysis Department

K. V. Fetisov

UEC-Aviadvigatel Stock Company

Email: olga.samsonova.avid@gmail.com

Russian Federation

Engineer of Rotor and Blades Structural Analysis Department

I. V. Karpman

UEC-Aviadvigatel Stock Company

Email: olga.samsonova.avid@gmail.com

Russian Federation

Head of Turbine Rotor Team, Rotor and Blades Structural Analysis Department

I. V. Burtseva

UEC-Aviadvigatel Stock Company

Email: olga.samsonova.avid@gmail.com

Russian Federation

Head of Rotor and Blades Structural Analysis Department

References

  1. FATA-02074 type certificate data sheet. PS-90A aviation propulsion engine. 2017. 16 p. (In Russ.)
  2. Inozemtsev A.A., Polatidi L.B., Andreychenko I.L. Life validation strategy. Proceedings of 29th Congress of the International Council of the Aeronautical Sciences (September, 7-12, 2014, St. Petersburg, Russian Federation). 2014.
  3. Inozemtsev A.A., Nikhamkin M.A., Sandratskiy V.L. Osnovy konstruirovaniya aviatsionnykh dvigateley i energeticheskikh ustanovok. T. 4. Dinamika i prochnost' aviatsionnykh dvigateley i energeticheskikh ustanovok [Principles of designing aircraft engines and power plants. V. 4. Dynamics and strength of aviation engines and power plants]. Moscow: Mashinostroenie Publ., 2008. 191 p.
  4. Birger I.A., Mavlyutov R.R. Soprotivlenie materialov: uch. posobie [Strength of materials]. Moscow: Nauka Publ., 1986. 560 p.
  5. Potapov S.D., Perepelitsa D.D. Determining service life rate of the main components of aircraft engines on the basis of the remaining life method. Dvigatel’. 2010. No. 5 (71). P. 28-29. (In Russ.)
  6. Shanyavskiy A.A. Bezopasnoe ustalostnoe razrushenie elementov aviakonstruktsiy. Sinergetika v inzhenernykh prilozheniyakh [Safe fatigue failure of airframe elements. Synergetics in engineering applications]. Ufa: Monografiya Publ., 2003. 802 p.
  7. McEvily A.J. Metal failures: Mechanisms, analysis, prevention. New York: Wiley, 2002. 324 p.
  8. NTSB Aircraft Accident Report, NTSB/AAR-98/01 Delta Airlines Flight 288, Pensacola, Florida, 1996.
  9. Nikhamkin M.Sh., Vyatchanin D.A. A probabilistic assessment of cycle life of GTE disks made of granular materials. Russian Aeronautics. 2008. V. 51, Iss. 1. P. 94-96. doi: 10.3103/S1068799808010169
  10. McClung R.C., Leverantet G.R., Wu Y-T., Millwater H., Chell G.G., Kuhlman C.J., Lee Y.-D., Riha D.S., Johns S.R., McKeighan P.C. Development of a probabilistic design system for gas turbine rotor integrity. Proceedings of the Seventh International Fatigue Conference Beijing (China, June 8-12, 1999).
  11. Nikhamkin M., Ilinykh A. Low cycle fatigue and crack grow in powder nickel alloy under turbine disk wave form loading: validation of damage accumulation model. Applied Mechanics and Materials. 2014. V. 467. P. 312-316. doi: 10.4028/www.scientific.net/amm.467.312
  12. Inozemtsev A.A., Nikhamkin M.Sh., Ilyinykh A.V., Ratchiyev A.M. Experimental checking the summation damages model at cyclic loading of turbines disks. Izvestiya Samarskogo Nauchnogo Tsentra RAN. 2012. V. 14, no. 4-5. P. 1372-1375. (In Russ.)
  13. Dem′yanushko I.V., Birger I.A. Raschet na prochnost' vrashchayushchikhsya diskov [The strength calculation of rotating discs]. M.: Mashinostroenie Publ., 1978. 247 p.
  14. Gayda J., Kantzos P. Burst testing and analysis of superalloy disks with a dual grain microstructure. NASA technical reports. 2013. 24 p.
  15. Gayda J., Kantzos P. Cyclic spin testing of superalloy disks with a dual grain microstructure. NASA technical reports. 2005. 21 p.
  16. Pak E.R., Bugreeva S.I., Karpman I.V., Dvoynikov S.S. Matematicheskoe modelirovanie razgonnykh ispytaniy diskov s ispol'zovaniem perspektivnykh kriteriev razrusheniya. Sbornik tezisov dokladov Vserossiyskoy nauchno-tekhnicheskoy konferentsii «Aviadvigateli XXI veka» (November, 24-27, 2015, Moscow). Moscow: TsIAM Publ., 2015. P. 594-595. (In Russ.)
  17. Branco R., Antunes F.V. Finite element modelling and analysis of crack shape evolution in mode-I fatigue Middle Cracked Tension specimens. Engineering Fracture Mechanics. 2008. V. 75, Iss. 10. P. 3020-3037. doi: 10.1016/j.engfracmech.2007.12.012
  18. Potapov S.D., Perepelitsa D.D. Research of influence of residual tension in the zone of the arrangement of the crack on the rate of its growth at cyclic loading. Aerospace MAI Journal. 2014. V. 21, no. 1. P. 104-110. (In Russ.)
  19. Uzbyakov D.M. Research of characteristics of cyclic crack resistance of the granular alloy on the nickel basis with different fraction of granules. PNRPU Aerospace Engineering Bulletin. 2015. No. 40. P. 122-134. doi: 10.15593/2224-9982/2015.40.07 (In Russ.)

Statistics

Views

Abstract - 68

PDF (Russian) - 52

Article Metrics

Metrics Loading ...

PlumX

Dimensions

Refbacks

  • There are currently no refbacks.

Copyright (c) 2019 VESTNIK of Samara University. Aerospace and Mechanical Engineering

License URL: https://journals.ssau.ru/index.php/vestnik/about/editorialPolicies#custom-2

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies