Article 11116

Title of the article

ON THE ISSUE OF FUNCTIONAL DIAGNOSTICS OF GAS TURBINE AIRCRAFT ENGINES BY 3D VIBRATION SPECTRA

Authors

Boloznev Viktor Vasil'evich, candidate of technical sciences, professor, sub-department of electronic and quantum devices, Kazan National Research Technical University named after A. N. Tupolev (420084, 10 K. Marks street, Kazan, Russia)
Zastela Mikhail Yur'evich, candidate of technical sciences, professor, sub-department of electronic and quantum devices, Kazan National Research Technical University named after A. N. Tupolev (420084, 10 K. Marks street, Kazan, Russia)
Mirsaitov Fanis Nailevich, candidate of technical sciences, director of department of information technologies, Open joint-stock company «Tulpar-Tekhnik» (420306, Airport «Kazan-2», Laishevsky district, Republic of Tatarstan, Russia)

Index UDK

629.7.03: 658.562

Abstract

It is shown that the control parameters of fluid (space) of jet engines is possible by measuring indirect parameters – electron density in the flame, and applied to the gas turbine (aircraft) engines – control vibration. It is proved that causes vibration of the turbine and compressor blades are complex processes in many units of the gas turbine engine (GTE). It is proved that it is necessary to control vibrospektr, the vibration control of the rotary engine blades reveals to one half of the rotor fault in the pre-damage stage. It is the basic reason for the lack of vibration control – the complexity of interfacing the sensors with the actual design of GTE. It is shown that the problem of functional diagnostics of a gas turbine aircraft engine is a set of blades control problems with unknown spectra for each of the coordinate axes, as well as the problem of vibration diagnostics of the blades by means of sensors, which are installed in a gas turbine engine is practically impossible. Proposed to GTD diagnostic use radiowave path, as a way of assessing the state of a gas turbine aircraft engine in flight at vibrospektram blades of the turbine and compressor. The process of formation and diagnostic significance of response at radio wave vibration control mode, the gas turbine engine in flight. Application of this method allows to detect defects on the pre-crash phase, and the implementation of structural changes do not require construction of new and existing GTD.

Key words

in-flight diagnostics, gas-turbine engine, turbine blade, RF-method, vibration spectrum, diagnostic response, 3D-vibrations.

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Дата создания: 18.05.2016 11:22
Дата обновления: 19.05.2016 10:23