Examination of the dynamic properties of 1st stage rotor blades in one - pass engine compressors under operating conditions

• Autorzy: Szczepanik R
• Języki publikacji: EN

Abstrakty

EN

This article includes studies of vibration and stress amplitudes in the Is' stage rotor blades of jet trainer one-pass engine compressors before and after refurbishment in operating conditions. The presented results were obtained using SAD-2 blade vibration amplitude registering and measuring apparatus. The same tests were carried on the same one-pass engine after modernisation. Example oscillograms from the vibration tests of the 16 blades are shown in this article, where show the vibrations of three randomly selected one-pass engines after refurbishment (marked 1, 2 and 3) out of a total of 50 engines. The engine vibration spectra cover the full rotation speed range. The difference between the vibration amplitudes of 1st stage rotor blades, in one-pass engine compressors before and after the refurbishment, is results from the difference in how the blades were attached to the disc. Before modernisation the hammer-type root was used, whereas after refurbishment dovetail-type fittings were applied. Furthermore, it was confirmed that there is nocoupling via the blade disc occurred when the blades were arranged on the disc according to the sinusoidal order of their free vibration frequencies. In such cases recorded vibration amplitudes remain within the average range (from 100 to 120 MPa in terms of stress).

Słowa kluczowe

EN

diagnostics of aircraft engines; compressor blade dynamics

• 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. 3
• Strony: 395--404
• Opis fizyczny: Bibliogr. 6 poz., rys.

Twórcy

autor

Szczepanik R

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

Bibliografia

• [1] Rządkowski, R., Drewczyński, M., Szczepanik, R., Dynamic Analysis of Rotor Blades in One-Pass Engines, ITWL Publishing House, Warsaw 2012.
• [2] Szczepanik, R., Witoś, M., Szuty, S., Szczepankowski, A., Szewczyk, J., Krypa, M., The SNDŁ-1b/SPŁ-2b Diagnostic System, Training Manual, Studies of ITWL, No. 11650, Warsaw 1996.
• [3] Szczepanik, R., Witos, M., Kowalski, M., Szczepankowski, A., The Method for Alteration of the Vibration Frequency for a Rotating Blade of a Fluid Flow Machine, in Particular a Rotating Blade of a Compressor in a Turbine Aircraft Engine, Patent No. 189360, Application date: 29th July 1998, Patent Assignee: The Air Force Institute of Technology, Warsaw 1998.
• [4] Szczepanik, R.,Kudelski, R., Report from the Project ‘Engineering and Construction of SAD Instruments for Studies on Vibrations of Blades Rotors in Turbine Engines’, Study of ITWL, No. 9121/I, 1988.
• [5] Szczepanik, R., Experimental studies on Dynamic Properties Demonstrated by Rotor Blades under Various Operating Conditions, Scientific Journal No. 26, ITWL, Warsaw 2010.
• [6] Witoś, M., Diagnostics of the Technical Condition Demonstrated by Compressor Blades of Internal Combustion Turbojet Engines with Use of the Non-contact Method for Vibration Measurements PhD Thesis, ITWL, Warsaw 1994.