Early detection of fatigue cracks in turbine aero - engine rotor blades during flight

• Autorzy: Szczepanik R.
• Języki publikacji: EN

Abstrakty

EN

The author shows results of research done in the Air Force Institute of Technology concerning design, development and implementation of modern diagnostic systems for aero-engines. The papers gives brief description of a project of a new advanced monitoring system basing on non-contact blade-vibration measurement. Recent monitoring systems for engines offer a great potential to reduce the high maintenance costs of aircraft while increasing reliability and safety. These systems check for abnormal engine responses to detect failures, saving lives and reducing secondary damage to the aircraft. A phenomenon of dynamic change of an aero-engine compressor blades natural frequency in course of fatigue cracks propagation in their roots on the example of a Polish turbojet engine is described. On the ground of this phenomenon main working principles of a device, which measures vibrations of turbine engine rotor blades with application of the noninterfering discrete method (MDPh), used for early detection of first stage compressor blade cracks are discussed. Typical representation of the first stage compressor blades vibration during engine acceleration, representation of the first stage blades vibration during engine acceleration and deceleration with steady-state stator distortions, crack initiation and propagation symptoms in blades, comparison of blade vibration spectra of the same blades for different conditions are presented in the paper.

Słowa kluczowe

EN

aero-engines; diagnostic of aircraft engine; non-contact blade-vibration measurement; damage to the aircraft

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2013
• Tom: Vol. 20, No. 1
• Strony: 337--342
• Opis fizyczny: Bibliogr. 7 poz., rys.

Twórcy

autor

Szczepanik R.

• Air Force Institute of Technology, Księcia Bolesława Street 6, 01-494 Warsaw, Poland tel.: [phone], fax: [phone]

Bibliografia

• [1] Zabłockij, I. E., Korostieliew, J. A., Szpiow, R. A., Noninterferen ce Measurement of turbo-Machine Blades Vibration, Maszinostrojenie, (in Russian), Moscow 1977.
• [2] Oones, H. T., Development of noninterference technique for measuring turbine engine rotor blade stresses, AIAA-85-1472, Ouly, pp.1-5, 1985.
• [3] Kudelski, R., Szczepanik, R., Noninterference measurements of turbo-machine blades vibrations, Proceedings of 6-th Conference – Technology of Turbo-Machines, pp. 373-377, Rzeszow 1988.
• [4] Boakes, S., Definitive HUMS, www.smiths-aerospace.com.
• [5] Szczepanik, R., Kowalski, M., Spychała, J., Some Aspects of Present Maintenance Philosophy for Helicopters in the Polish Air Force, Workshop on Fatigue Design of Helicopters, Pisa, 12-13 Sep. 2002.
• [6] Witos, M., Szczepanik, R., Turbine Engine Health/Maintenance Status Monitoring with use of Phase-Discrete Method of Blade Vibration Monitoring, RTO AVT-121 Symposium on Evaluation, Control and Prevention of High Cycle Fatigue in Gas Turbine Engines for Land, Sea and Air Vehicles, Granada 2005.
• [7] Gas turbine condition monitoring & fault diagnosis. Von Karman Institute, Rhode-Saint-Genese, Belgium 2004.