Papers by Michal Wachlaczenko
Journal of Konbin, 2014
The paper presents description of rotating bladed disk mathematical model. Correctly defined math... more The paper presents description of rotating bladed disk mathematical model. Correctly defined mathematical model of rotor allows creation of numerical simulation model which can be used to generate tip-timing data. First of all, the model is necessary to conduct a research on blade response due to input force in form of changing rotational speed. This enables the possibility to determine turbojet engine terminal operating conditions causing its failure.
Rotating stall and surge are common phenomena in compressors, and related research has been carri... more Rotating stall and surge are common phenomena in compressors, and related research has been carried out since the invention of the gas-turbine engine. Signals of fast response pressure sensors analysed with spectral methods based on Fourier transform are primarily used to characterise compressor stall. This article focuses on the application of blade tip timing (BTT) for this purpose and aims to demonstrate current analysis capabilities, issues and challenges related to practical applications. By using real engine test results, we show that BTT provides more information at the cost of more complex analysis. The signals of four tip timing and three pressure probes installed in the first compressor stage are processed. We observed flow disturbances and blade responses caused by objects located in the inlet at a constant speed and also surge events during snap acceleration. All-blade spectrum and modal tracking are used to identify the presence of non-integral vibration and to determine the nominal frequency and nodal diameter. This data seeds the Least Squares Fitting, which delivers amplitude and phase. A method for sensor fusion is presented. For the selected non-integral responses, tip timing and pressure results are evaluated to show how they can complement each other. The proposed methodology can be used both for compressor development and Blade Health Monitoring.
Journal of Theoretical and Applied Mechanics, 2010
The paper presents numerical analysis of airplane parameters of motion during wing transverse vib... more The paper presents numerical analysis of airplane parameters of motion during wing transverse vibrations of an average commercial airplane. The mathematical model of the airplane motion including a system of twelve ordinary differential equations was employed. Using available publications and M28 "Bryza" airplane geometrical and mass relationships, a computer code evaluating parameters of the motion was developed. In order to take the wing transverse vibrations under consideration, the way of wing displacements in the aircraft-fixed system of coordinates was elaborated as well as vibration amplitude and frequency were assumed. The analysis covered two cases of wing transverse vibrations: bending of both wing halves in phase and in counter-phase. On the basis of the obtained results, some conclusions referring the airplane dynamic properties during wing vibrations were formulated.
Journal of Theoretical and Applied Mechanics, 2012
This paper presents numerical analysis of airplane motion parameters during wing in-flight icing.... more This paper presents numerical analysis of airplane motion parameters during wing in-flight icing. The wing external flaps deflection event was taken under consideration. The mathematical model of the airplane motion including twelve ordinary differential equations was employed. Using available publications as well as TS-11 "Iskra" jet trainer geometrical and mass relationships, a computer code evaluating motion parameters of an iced airplane was developed. On the basis of analysis results, conclusions referring airplane dynamic properties during wing ice accretion was formulated.
Journal of Physics: Conference Series
In a recently implemented aerial target, the propulsion system consists of two JetCat micro turbo... more In a recently implemented aerial target, the propulsion system consists of two JetCat micro turbojet engines. Due to the limited durability of the rotor support bearings, the engine operation time has been limited to two hours or two flights. In addition, after each flight, an engine bench test with vibration measurement is required. The adopted maintenance system is also labor-intensive and costly due to obligatory shaft bearing inspections performed frequently in the repair shop. These problems result from the limitations of the available high-speed bearing technology and the high rotor loads related to aircraft maneuvers in the air. The goal of the work is to develop a method for assessing the health of the main shaft bearings in the micro turbojet based on vibration signals. Methods known from full-scale jet engines were adapted for monitoring the health of the main shaft bearings. An accelerometer and rotational speed sensor were mounted on the engine. Vibration and other param...
Biuletyn Wojskowej Akademii Technicznej, 2003
Rotating stall and surge are common phenomena in compressors, and related research has been carri... more Rotating stall and surge are common phenomena in compressors, and related research has been carried out since the invention of the gas-turbine engine. Signals of fast response pressure sensors analysed with spectral methods based on Fourier transform are primarily used to characterise compressor stall. This article focuses on the application of blade tip timing (BTT) for this purpose and aims to demonstrate current analysis capabilities, issues and challenges related to practical applications. By using real engine test results, we show that BTT provides more information at the cost of more complex analysis. The signals of four tip timing and three pressure probes installed in the first compressor stage are processed. We observed flow disturbances and blade responses caused by objects located in the inlet at a constant speed and also surge events during snap acceleration. All-blade spectrum and modal tracking are used to identify the presence of non-integral vibration and to determin...
Journal of Theoretical and Applied Mechanics, 2012
This paper presents numerical analysis of airplane motion parameters during wing in-flight icing.... more This paper presents numerical analysis of airplane motion parameters during wing in-flight icing. The wing external flaps deflection event was taken under consideration. The mathematical model of the airplane motion including twelve ordinary differential equations was employed. Using available publications as well as TS-11 ``Iskra'' jet trainer geometrical and mass relationships, a computer code evaluating motion parameters of an iced airplane was developed. On the basis of analysis results, conclusions referring airplane dynamic properties during wing ice accretion was formulated.
The comprehensive approach for rotating fan, compressor and turbine blades diagnostic has been in... more The comprehensive approach for rotating fan, compressor and turbine blades diagnostic has been introduced in the paper. Critical slowand high-s peed rotating fluid-flow machinery (fans, steam turbines and aero jet eng in s) running at risk of mechanical damage (by foreign objects and erosion), corro si n and other forms of material fatigue (LCF, HCF, VHCF, TMF). Objects endangered with variations of modal characteristics by blade mass change (influence of depo sit) and rate of material anisotropy. For blades’ real operating condition and technical state monitoring purposes a rotating blade observer method (Tip-Timing method) has been used. C ombination of supervised rotating blade row and magnetic reluctance sensor create sort of an encoder which output signal contain simultaneous information about: blade vibration induced by aerodynamic and mass force input; instantaneous rotor rotation speed; rotor unbalance and vibration; coupling conditions of reluctance sensor with vibration an...
The paper presents numerical analysis of airplane parameters of motion during wing transverse vib... more The paper presents numerical analysis of airplane parameters of motion during wing transverse vibrations of an average commercial airplane. The mathematical model of the airplane motion including a system of twelve ordinary differential equations was employed. Using available publications and M28 "Bryza" airplane geometrical and mass relationships, a computer code evaluating parameters of the motion was developed. In order to take the wing transverse vibrations under consideration, the way of wing displacements in the aircraft-fixed system of coordinates was elaborated as well as vibration amplitude and frequency were assumed. The analysis covered two cases of wing transverse vibrations: bending of both wing halves in phase and in counter-phase. On the basis of the obtained results, some conclusions referring the airplane dynamic properties during wing vibrations were formulated.
This paper presents numerical analysis of airplane motion parameters during wing in-flight icing.... more This paper presents numerical analysis of airplane motion parameters during wing in-flight icing. The wing external flaps deflection event was taken under consideration. The mathematical model of the airplane motion including twelve ordinary differential equations was employed. Using available publications as well as TS-11 "Iskra" jet trainer geometrical and mass relationships, a computer code evaluating motion parameters of an iced airplane was developed. On the basis of analysis results, conclusions referring airplane dynamic properties during wing ice accretion was formulated. Notations α, β -angle of attack and slideslip Φ, Θ, Ψ -aircraft roll, pitch and yaw angle m -airplane total mass V = [u, v, w] ⊤ -centre of mass of airplane velocity vector Ω = [p, q, r] ⊤ -rotational velocity vector in airplane-fixed system of coordinates F = [X, Y, Z] ⊤ -external forces vector acting on the airplane M = [L, M, N ] ⊤ -moments of forces vector M acting on the airplane K = i (r i × m i V i ) -total angular momentum around taken reference point M gir = Jω × Ω -gyrostatic moment 270 G. Kowaleczko, M.
Journal of KONBiN, 2014
ABSTRACT The paper presents description of rotating bladed disk mathematical model. Correctly def... more ABSTRACT The paper presents description of rotating bladed disk mathematical model. Correctly defined mathematical model of rotor allows creation of numerical simulation model which can be used to generate tip-timing data. First of all, the model is necessary to conduct a research on blade response due to input force in form of changing rotational speed. This enables the possibility to determine turbojet engine terminal operating conditions causing its failure
The paper has been intended to introduce the Tip Timing Method (TTM) to monitor rotating blades i... more The paper has been intended to introduce the Tip Timing Method (TTM) to monitor rotating blades in an aircraft compressor, that was implemented in Poland: in maintenance of the TS-11 " Iskra " aircraft in 1993 and in the SO-3 engine overhaul technology in 1997. The scope of research performed before the implementation of TTM and its advisory expert-software have been outlined. On the base of conducted experimental research, it has been confirmed that computer-based system to support operational safety of the TS-11 " Iskra " aircraft and overhauls of engines SO-3 has enabled to actively control a process of material fatigue. As a result of reason identification of fatigue problems, flight safety of the TS-11 " Iskra " aircraft was improved and the following problems were eliminated from operational use: a fatigue problem with I stage rotor blades in compressors and instable operation of the SO-3 engines. Unconscious human errors were also eliminated and technical culture of maintenance and overhauls of the SO-3 engines was improved. Reasons for other technical problems with the SO-3 engines were reliably determined. Presented topic has been illustrated by means of many practical examples.
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Papers by Michal Wachlaczenko