System for inflight early detection of cracks in turbine aero-engine compressor blades

• Autorzy: Szczepanik R.
• Konferencja: Proceedings of the Third Seminar on Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education/seminar(III; 23-25.11.1998; Warszawa, Polska)
• Języki publikacji: EN

Abstrakty

EN

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 noninterferent discretephase method (MDPh), used for early detection of first stage compressor blade cracks are discussed. The structure of a computer-based aero-engine compressor blades has been discussed and presented in this paper.

Słowa kluczowe

EN

early warning system; turbine aero-engine; compressor blade

PL

system wczesnego ostrzegania; turbina silnika lotniczego; spężarki

• Wydawca: Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology
• Czasopismo: Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics
• Rocznik: 1999
• Tom: nr 9
• Strony: 139--144
• Opis fizyczny: Bibliogr. 11 poz., rys., wykr.

Twórcy

autor

Szczepanik R.

• Air Force Institute of Technology, Poland