Simulation by smoothed particle method of gas turbo engine holle fan blade foreign object damage
Aerospace propulsion engineering
Аuthors
*, **, ***Perm National Research Polytechnic University, PNRPU, 29, Komsomolsky Prospekt, Perm, 614990, Russia
*e-mail: nikhamkin@mail.ru
**e-mail: leonid-v-voronov@yandex.ru
***e-mail: olga-l-voronova@yandex.ru
Abstract
Modern fan design for aviation big size gas turbine engines is supposed to use hollow wide-cord rotor blades. Hollow fan blade developing requires complex problem solution in the fields of aerodynamics, design, technology, vibration damping, fatigue resistance and operation damage durability. The article is devoted to the problem of turbo engine hollow fan blade resistance to foreign object damage.
The investigated hollow fan blade is a sheet welded structure with gofered filler. The blade airfoil is shaped and assembled with the method of super-plastic molding and pressure welding combination.
It is proposed the technique of numerical simulation of ballistic damage by stone of hollow fan blade. The technique is based on joint using of finite elements and smoothed particle method. Johnson & Cook model was used to describe high speed plastic behavior of blade titanium alloy under impact by stone.
There were numerically simulated several cases of ballistic damage of blade leading edge and airfoil shell by different size stone moving with speed 266-515 m/s. Damage geometric parameters, residual stress and stain fields were found as result of simulation.
Experimental modeling was executed to verify the calculation technique and results. Specimens of blade edge and airfoil were subjected to impact by granitic ball accelerated in gas gun up to velocity 400 m/s. To estimate residual strains at damage zone special net was wrote on the specimen. It was found good agreement of experimental and calculated data (damage size and residual strain).
The developed numerical simulation technique may be used for comparative analysis measures of blade foreign objects damage resistance improving.
Keywords:
fan blade, foreign object damage, finite elements method, smooched particles methodReferences
- Inozemtsev A.A., Mulyukov R.R., Safiullin R.V., Kruglov A.A., Lutfullin R.Ya, Koksharov N.L., Kharin S.A., Morozov M.A. Nanotekhnologii i nanomaterialy Permskogo kraya, Sbornik statei, Perm, 2009, pp. 61-65.
- Valiakhmetov O.R., Galleev R.M., Ivan’ko V.A., Inozemtsev A.A., Imaev R.M., Koksharov N.L., Kruglov A.A., Lutfullin R.Ya, Mulyukov R.R., Nazarov A.A., Safiullin R.V., Kharin S.A. Rossiiskie nanotekhnologii, 2010, vol. 5, no. 1-2, pp. 102-111.
- Petukhov A.N. Dvigatel’, 2005, no. 5, pp. 14-15.
- Sirotin N.N. Konstruktsiya i ekspluatatsiya, povrezhdaemost’ i rabotosposobnost’ gazoturbinnykh dvigateley (Construction and maintenance, damaging and operational availability of a gas-turbine engine), Moscow, RIA IM-Inform, 2002, 442 p.
- Hudak, S.J., Chell, G.G. Materialy 4 National Conference Turbine Engine High Cycle Fatigue , Monterey, CA, February 1999.
- Duo´ P., Nowell D., Schofield J. Assessment of foreign object damage (FOD) to aero engine blades. Proceeding of the 9th National Turbine Engine HCF Conference, Pinehurst, NC., CD-Rom, 2004.
- Nowell D., Duó P., Stewart I.F. Prediction of fatigue performance in gas turbine blades after foreign object damage, International Journal of Fatigue, 2003, 25, pp. 963-969.
- Guan Yupu, Zhao Zhenhua, Chen Wei, Gao Deping. Foreign Object Damage to Fan Rotor Blades of Aeroengine. Part II: Numerical Simulation of Bird Impact, Chinese Journal of Aeronautics , 2008, 21, рp. 328-334.
- Meguid S.A., Mao R.H., Ng T.Y. FE analysis of geometry effects of an artificial bird striking an aeroengine fan blade, International Journal of Impact Engineering, 2008, 35, pp. 487-498.
- Shmotin Y.N., Chupin P.V., Gabov D.V., Ryabov A.A., Romanov V.I., Kukanov S.S. Bird strike analysis of aircraft engine fan, 7th European LS-DYNA Conference, 2009.
- Nikhamkin M.S., Voronov L.V., Semenova I.V. Foreign object damage and fatigue strength loss in compressor blades, Proceedings of ASME Turbo Expo 2008, Berlin, 2008, GT2008-51493.
- Nikhamkin M.S., Voronov L.V., Semenova I.V. Effect of blade geometry and foreign object kinetic energy on blades damage, Proceedings of ASME Turbo Expo 2010, Glasgow, 2010, GT2010-22425.
- Nikhamkin M.S., Voronov L.V., Lyubchik O.L., Gladkii I.L. Izvestiya Samarskogo nauchnogo tsentra Rossiiskoi akademii nauk, 2011, vol. 13, no. 4(4), pp. 991-997
- Nikhamkin M.S., Semenova I.V., Lyubchik O.L., Gladkii I.L. Izvestiya Samarskogo nauchnogo tsentra Rossiiskoi akademii nauk, 2011, vol. 13, no. 1(2), pp. 226-229.
- Nikhamkin M.S., Voronov L.V., Semenova I.V. Konev I.P., Plotnikov Yu.I Saraeva L.V. Aviatsionnaya promyshlennost’, 2008, no. 1, pp. 21-24.
- Nikhamkin M.S., Semenova I.V. Izvestiya Vuzov :Aviatsionnaya tekhnika, 2011, no. 4, pp. 3-6.
- Nikhamkin M.S., Voronov L.V., Semenova I.V. Aviatsionnaya promyshlennost’, 2010, no. 3 pp. 16-19.
- Stellingwerf R.F., Wingate C.A. Impact modeling with smooth particle hydrodynamics, Los Alamos National Laboratory, MS F645, Los Alamos, New Mexico 87545.
- Hallquist J. LS-DYNA Theoretical Manual, Livermore Software Technology Corporation , 1999, 498 p.
- Chen X. Foreign object damage on the leading edge of a thin blade, Mechanics of Materials, 2005, no. 37, 2005, pp. 447–457.
- Dietenberger M., Buyuk M., Kan C-D. Development of a high strain-rate dependent vehicle model, Proccedings 4 German LS-DYNA Anwenderforum, Bamberg, 2005, B-III-1-10 p.
- Johnson G.R., Cook W.H. A constitutive model and data for metals subjected to large strain, high strain rates and high temperatures, Proceedings 7th International Symposium on Ballistics, Hague, 1983, pp. 541-547.
- Lesuer D.R. Experimental Investigations of Material Models for Ti-6Al-4V Titanium and 2024-T3 Aluminum, U.S. Department of Transportation Federal Aviation Administration, DOT/FAA/AR-00/25, 2000, 41p.
- Kotyakhov F.I. Fizika neftyanykh i gazovykh kollektorov (Physics of oil and gas collectors), Moscow, Nedra, 1977, 287 p.
Download