Computational evaluation of annular combustion chamber flame tube walls stress-and-strain state

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Аuthors

Anisimov V. M.*, Orlov M. Y.**, Zubrilin I. A.***

Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia

*e-mail: vradik@mail.ru
**e-mail: adler65@mail.ru
***e-mail: zubrilin416@mail.ru

Abstract

The important goal of GTE combustion chambers and installations design and workout consists in provision of the specified durability and reliability. In response to this problem, the temperature of the combustion chamber major elements should stay within the operating temperature range of their structural materials, and their deformation should not exceed the specified values.

Combustion chamber flame tube walls are some of the most heat-loaded elements. Thus, the problem associated with the study of their stress-and-strain state is particularly up-to-date. It is worsen by the existing tendencies aimed at increasing compression ratio of the compressor and gas temperature at the turbine input. Temperature distribution over compressor flame tube surface determining in the course of complete product bench testing presents a complex task. The effective method of rectifying the above said problem during gas turbine units consists in numerical modeling methods implementation, which requires developing procedures of their implementation.

Such procedure was developed while GTD combustion chamber for terrestrial surface application design. For its realization we used geometrically conjugate 3-D model of the combustion chamber, including both air-gas channel necessary for gas dynamic processes modeling, and flame tube walls with multilayer thermal-protective coating for heat transfer computation. Combustion chamber operating procedure mathematical model was developed earlier and passed validation process. Simulation was carried out in ANSYS.

Temperature distribution on the flame tube wall was obtained by computation. Based on the analysis of the obtained results we managed to reduce maximum flame tube wall temperature to the required value at the expense of apertures areas redistribution between cooling system strips. Stresses and deformations occurring due to flame tube walls heating were determined as well. It was revealed that maximum stress occur at cooling apertures locations. The value of calculated strength factor equals 2.7.

The developed procedure for combustion chamber flame tube walls thermal-and-stress states determination can be implemented for various combustion chamber desings, materials and multi-layer walls. This procedure allows predicting the most dangerous temperature zones on the flame tube walls and burn-out in this zones prior to bench testing.

Keywords:

flame tube, thermal-protective coating, cooling system, thermal state, stress and deformation, computer simulation, conjugate geometrical model

References

  1. Park J.S., Moon H., Kim K.M., Kang S.H., Cho H.H. Thermal Analysis of Cooling System in a Gas Turbine Transition Piece. Proceeding of ASME Turbo Expo 2011, pp. 1-10.

  2. Jeromin A., Eichier C., Noll B., Aigner M. Full 3D Conjugate Heat Transfer Simulation and Heat Transfer Coefficient Prediction for the Effusion Сooled Wall of a Gas Turbine Combustor. Proceeding of ASME Turbo Expo 2008 Power for Land, Sea and Air, pp. 1-9.

  3. Bouchard D., Pucher G., Allan W.D.E. Can-Annular Combustion Chamber Surface Temperatures Measurements and Damage Signatures at Operationally Representative Conditions. Proceeding of ASME Turbo Expo 2011, pp. 1-9.

  4. Jie H., Jinhai G. Local Thermal Buckling Analysis Method of Combustor Liner. Proceeding of ASME Turbo Expo 2009: Power for Land, Sea and Air, pp. 1-13.

  5. Patil S., Abraham S., Tafti D., Ekkad S., Kim Y., Dutta P., Moon H.K., Srinivasan R. Experimental and Numerical Investigation of Convective Heat Transfer in a Gas Turbine Can Combustor. Proceeding of ASME Turbo Expo 2009: Power for Land, Sea and Air, pp. 1-9.

  6. Da Soghe R., Bianchini C., Andreini A., Mazzei L. Thermo-Fluid Dynamic Analysis of a Gas Turbine Transition-Piece. Proceeding of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, pp. 1-12.

  7. Andreini A., Facchini B., Mazzei L., Bellocci L., Turrini F. Assessment of Aero-Thermal Design Methodology For Effusion Cooled Lean Burn Annular Combustors. Proceeding of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, pp. 1-11.

  8. Vassiliev V., Magni F., Chernyshev S., Kostege V. Impact of the 3D Flow Effects on the Silo Combustor Thermal State. Proceeding of ASME Turbo Expo 2012, pp. 1-10.

  9. Vorob’ev A.G. Vestnik Moskovskogo aviatsionnogo instituta, 2007, vol. 14, no. 4, pp. 42-49.

  10. Kovateva Yu.S., Bogacheva D.Yu. Trudy MAI, 2013, no. 65, available at: http://www.mai.ru/science/trudy/eng/published.php?ID=40191

  11. Kolesnik S.A., Formalev V.F., Selin I.A. Trudy MAI, 2015, no. 80, available at: http://www.mai.ru/science/trudy/eng/published.php?ID=56941

  12. Matveev S.G., Orlov M.Yu., Zubrilin I.A. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta imeni akademika S.P. Koroleva, 2013, no. 3, part 1, pp. 156-162.

  13. Matveev S.G., Orlov M.Yu., Zubrilin I.A., Matveev S.S., Tsybizov Yu.I. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta imeni akademika S.P. Koroleva, 2013, no. 3, part 1, pp. 163-169.

  14. Matveev S.G., Lanskii A.M., Orlov M.Yu., Abrashkin V.Yu., Dmitriev D.N., Zubrilin I.A., Semenov A.V. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta imeni akademika S.P. Koroleva, 2011, no. 5, pp. 168-178.

  15. Matveev S.G., Orlov M.Yu., Abrashkin V.Yu., Zubrilin I.A., Matveev S.S. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta imeni akademika S.P. Koroleva, 2011, no. 5, pp. 179-187.

  16. Grotjans H., Menter F.R. Wall functions for general application CFD codes. Proceedings of the Fourth European Computational Fluid Dynamics Conference, 1998, pp. 1112-1117.

  17. Gibson M.M., Launder B.E. Ground Effects on Pressure Fluctuations in the Atmospheric Boundary Layer. Journal of Fluid Mechanics, 1978, pp. 491– 511.

  18. Launder B.E. Second-Moment Closure: Present... and Future? International Journal of Heat and Fluid Flow, 1989, vol. 10, no. 4. pp. 282 – 300.

  19. Launder B.E., Reece G.J. Progress in the Development of a Reynolds-Stress Turbulence Closure. Journal of Fluid Mechanics, 1975, vol. 68, no. 3, pp. 537 – 566.

  20. Krylov B.A., Manuilov A.A., Fedоrov S.A., Yun A.A. Vestnik Moskovskogo aviatsionnogo instituta, 2010, vol. 17, no. 5, pp. 111-115.

  21. Anderson W., Bonhus D.L. An Implicit Upwind Algorithm for Computing Turbulent Flows on Unstructured Grids. Computers & Fluids, 1994, no. 23(1), pp. 1 – 21.
  22. Oijen A., Goey L.P.H. Modelling of Premixed Laminar Flames Using Flamelet-Generated Manifolds. Combustion Science and Technology, 2000, no. 161, pp. 113 – 137.
  23. ANSYS 15.0 User’s Guide.
  24. Shalin R.E. Aviatsionnye materialy (Aviation materials), Moscow, NPO “VIAM”, 1989, 566 p.
  25. Tamarin Yu.A., Kachanov E.B. Novye tekhnologicheskie protsessy i nadezhnost’ GTD. TsIAM, 2008, issue 7, pp. 125-144.
  26. Yurchenko I.I., Karakotin I.N., Kudinov A.S. Trudy MAI, 2011, no. 43, available at: http://www.mai.ru/science/trudy/eng/published.php?ID=24786
  27. Coppalle A., Vervisch P. The Total Emissivities of High-Temperature Flames. Combustion and Flame, 1983, pp. 101 – 108.
  28. Startsev N.I. Konstruktsiya i proektirovanie osnovnykh uzlov i sistem aviatsionnykh dvigatelei i energeticheskikh ustanovok (Design and engineering of major components and systems of aircraft engines and power plants), Samara, SSAU, 2013, 774 p.

mai.ru — informational site of MAI

Copyright © 1994-2024 by MAI