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1
Content available The Effect of Environmental Flight Conditions on Damage Propagation in Composite Sandwich Structure
Synaszko P., Sałaciński M., Kornas Ł.
Fatigue of Aircraft Structures
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2015
|
Iss. 7
24--27
EN
The aim of the study was to determine the traceability of damage growth caused by inclusions of water in the composite sandwich structure. It was assumed that as a result of temperature changes during the flight and accompanying phase transformation, the zone containing water inclusions increases. The growth is caused by the destruction (mainly the tearing of walls) of the core. As part of the work, this assumption was verified experimentally. For the experiment to be successful it was necessary to simulate actual flight conditions. The simulation involved inducing phase transformations of water in the core cell as a function of time and temperature. Before and after the experiments the non-destructive tests using pulsed thermography were performed. The test results revealed an increase in the number of cells occupied by water. Adequate specimens were designed and manufactured. The study showed that cyclical changes in temperature affected the propagation of water in core sandwich structures. Further, it was found that the increase in the surface area of water-containing inclusions could be monitored using thermographic techniques.
2
Content available An Approach to Structural Health Monitoring of Composite Structures Based on Embedded PZT Transducers
Dziendzikowski M., Dragan K., Kurnyta A., Kornas Ł., Latoszek A., Zabłocka M., Kłysz S., Leski A., Chalimoniuk M., Giewoń J.
Fatigue of Aircraft Structures
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2014
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Iss. 6
113--118
EN
One approach to developing a system of continues automated monitoring of structural health is to use elastic waves excited in a given medium by a piezoelectric transducers network. Depending on their source and the geometry of the structure under consideration elastic waves can propagate over a significant distance. They are also sensitive to local structure discontinuities and deformations providing a tool for detecting local damage in large aerospace structures. This paper investigates the issue of Barely Visible Impact Damages (BVIDs) detection in composite materials. The model description and the results of impact tests verifying damage detection capabilities of the proposed signal characteristics are presented in the paper.
3
Content available Damage Detection and Size Quantification of FML with the Use of NDE
Dragan K., Kornas Ł., Kosmatka M., Leski A., Sałaciński M., Synaszko P., Bieniaś J.
Fatigue of Aircraft Structures
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2012
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Iss. 4
5--9
EN
Composite materials have been developed in recent years. A new generation of structural composite materials for advanced aircraft is Fibre Metal Laminates (FML). They are hybrid composites consisting of alternating thin layers of metal sheets and fiber-reinforced composite material. FMLs have both low weight and good mechanical properties (high damage tolerance: fatigue and impact characteristics, corrosion and fire resistance). Quality control of materials and structures in aircraft is an important issue, also for Fibre Metal Laminates. For FML parts, a 100% non-destructive inspection for internal quality during the manufacturing process is required. In the case of FML composites, the most relevant defects that should be detected by non-destructive testing are porosity and delaminations. In this paper, a number of different non-destructive methods for the inspection of Fibre Metal Laminates were studied. The possibility of quality control of manufactured FML laminates - detection of defects as well as the procedures and processes are presented and discussed.
4
Content available remote Problematyka diagnozowania kompozytowych konstrukcji lotniczych
Dragan K., Kornas Ł, Pałka N.
Przegląd Spawalnictwa
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2011
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R. 83, nr 13
23-28
PL
W artykule przedstawiony zostanie opis problematyki diagnozowania kompozytowych konstrukcji lotniczych. Kompozyty, charakteryzuje zdecydowanie większy stosunek masa/wytrzymałość, niż większość konstrukcji wykonywanych np. z stopów lekkich. Są one jednak wrażliwe na uszkodzenia od udarów mechanicznych i termicznych. Ponadto w trakcie wytwarzania powstają uszkodzenia wpływające na zmniejszenie ich wytrzymałości. W artykule przedstawiono podejście do diagnostyki takich struktur z wykorzystaniem metod badań nieniszczących takich jak: metoda ultradźwiękowa z wykorzystaniem Phased Array, oraz metoda spektroskopii terahertzowej. Omówiono i przedstawiono problemy diagnozowania konstrukcji kompozytowych, w tym konstrukcji FML (Fibre Metal Laminates). Dla każdej z tych metod badań nieniszczących przedstawiono ich zalety i ograniczenia związane z diagnostyką takich konstrukcji.
EN
This paper presents approach for NDT techniques for composite structural integrity assessment of the aerospace structures. In such structures besides of higher mass/durability ratio than e.g. aluminum alloys aerospace components there is higher vulnerability on the failure mode creation because of impact damage from mechanical and thermal shocks. Moreover during the manufacturing process different damages occur and affect material strength. For the purpose of damage detection different NDE (Non Destructive Evaluation) techniques will be presented such as: ultrasonic with the use of Phased Array and THz spectroscopy. The main problems of the composites structures NDE will be highlighted and presented including FML (Fibre Metal Laminates). All the advantages and limitations of the above described NDE methods will be delivered.
5
Content available Termograficzna metoda badań nieniszczących konstrukcji lotniczych
Kornas Ł., Wiśniewski T., Dragan K.
Pomiary Automatyka Kontrola
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2011
|
R. 57, nr 10
1227-1229
PL
W artykule opisano metodę badań nieniszczących konstrukcji lotniczych w podczerwieni wykorzystującą technikę termografii impulsowej (ang. pulsed thermography). Pomiary w podczerwieni zrealizowano na elementach konstrukcji lotniczych wykonanych ze stopów aluminium oraz coraz powszechniej stosowanych struktur kompozytowych zbrojonych włóknem węglowym lub szklanym. W takich strukturach powstają uszkodzenia zagrażające trwałości konstrukcji lotniczych takie jak: korozja (ubytkowa, ukryta, naprężeniowa, etc.); pęknięcia zmęczeniowe; wady i uszkodzenia w kompozytach (m.in. wtrącenia ciał obcych, rozwarstwienia, etc.). Zaprezentowano wyniki badań termograficznych oraz ich analizę z przeprowadzonej inspekcji struktur przekładkowych i laminarnych, w których zarejestrowano typowe nieciągłości strukturalne lub konstrukcyjne jakie mogą w nich występować. Zwrócono również uwagę na zalety i ograniczenia zastosowanej techniki badawczej.
EN
The paper presents a method for nondestructive testing of aircraft structures using infrared pulsed thermography. In the pulsed ther-mography method, a disorder in the thermal equilibrium is intro-duced for a short time interval (a few thousandths of a second for metals) by providing a momentary portion of thermal energy. Infra-red measurements were taken on aircraft structural components made of aluminum alloys as well as of carbon- or glass-fiber rein-forced composites (use of which is increasingly more common). In such structures, damage modes that endanger the structure durability may occur. These are: corrosion (cavity, hidden, stress, etc.); fatigue cracks; defects and damage in composites (such as foreign body intrusions, delaminations, etc.). In the paper there are presented the results of thermographic testing. There is also described the analysis of the inspections performed on sandwich and laminar structures in which typical structural defects were recorded. The advantages and limitations of the pulsed thermography method are given.
6
Content available Analysis of the Possibility to Assess the Occurrence of Hidden Corrosion in Lap Joints Using Active Thermography
Kornas Ł., Dragan K.
Fatigue of Aircraft Structures
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2011
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Iss. 3
53--56
EN
The article details the NDT technique of pulse thermography used for objective diagnosis of riveted lap joints construction. The degradation of materials manifesting in corrosion is inherent in the process of aircraft operation. One type of corrosion is galvanic corrosion occurring in the overlap joints (known as hidden corrosion). As a result of the potential difference between the two layers of the aluminum alloy skin, there occurs the phenomenon of oxidation of the material, producing corrosion products in the form of oxide compounds characterized by heat properties different than those of the base material. Active thermography techniques allow observing infrared energy, which changes due to the difference of thermal properties of the tested materials.
7
Content available Examination of changes in the microstructure of gas turbine blades with visual and thermographic methods
Błachnio J., Kułaszka A., Kornas Ł., Chalimoniuk M.
Journal of KONES
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2010
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Vol. 17, No. 2
27-34
EN
The processes associated with operation of turbinę avionic engines entail the occurrence of various defects affecting turbine components, in particular turbine vanes. The main reasons for defects and deterioration of gas turbine vanes include thermal fatigue and overheating of the vane material. This paper outlines the non-destructive test methods that are currently in use and that are based on an analysis of surface images obtained from the examined parts within the visible bandwidth with the use of a ring-wedge detector. Particular attention is paid to opportunities that enable unbiased diagnostics of changes in the microscopic structure of vanes with the use of the non-destructive thermographic method. Initial examinations ofthe gas turbine vanes, both new ones and those already in operation, have demonstrated the existence of interrelations and dependency between the thermal strain during the turbine operation, changes of signals associated with the thermal response from the material and the condition of the vane microstructures. The results of these examinations have been successfully verified with the use of the metallographic method. The demonstrated interrelations and dependency shall serve as a basis to develop fundamentals for a non-destructive thermographic test method intended to assess the overheating condition of the material for gas turbine vanes.
8
Content available remote Analysis of feasibility to assess microstructure of gas turbine blades by means of the thermographic method
Kułaszka A., Błachnio J., Kornas Ł.
Journal of KONBiN
|
2010
|
No. 1 (13)
325-340
EN
Operation of avionic turbine engines is always associated with possibility of various defects that may happen to turbine components, in particular to its blades. The most frequent reason for defects is overheating of the blade material but the thermal fatigue also occurs quite often. The most efficient examination method that provides plenty of information about structure of the investigated material of turbine blades is metallography but it is a destructive testing technology, so that the turbine no longer can be used after such investigation. This paper deals with methods of non-destructive tests that are currently in use and applicability of such methods to unbiased and trustworthy computer-aided diagnostics aimed to find out how the blade microstructure status varies in time. Results of initial examination of gas turbine blades are presented whereas the tests with use of the non-invasive thermographic method were carried out in order to assess condition of the blade material after the turbines had been subjected to the effect of high temperatures. Subsequently, the obtained results were successfully validated by means of the metallographic method. Eventually the conclusion could be made that the thermographic method makes it possible to achieve comprehensive and trustworthy information how microstructure of the blade materials is altered during the aircraft operation.
PL
W procesie eksploatacji lotniczych silników turbinowych występują różnego rodzaju uszkodzenia elementów turbin, a zwłaszcza ich łopatek. Najczęstszą ich przyczyną jest przegrzanie materiału, a także zmęczenie cieplne łopatek. Mimo, iż badania metodą metalograficzną dostarczają informację o strukturze badanego materiału łopatek turbiny, to w rezultacie są to badania niszczące uniemożliwiające ich dalsze wykorzystanie. W artykule omówiono stosowane obecnie metody badań nieniszczących oraz możliwości ich wykorzystania do obiektywnego diagnozowania zmian stanu mikrostruktury łopatek turbin. Przedstawiono wyniki wstępnych badań łopatek turbiny gazowej poddanych wysokiej temperaturze z zastosowania nieinwazyjnej metody termograficznej do oceny stanu ich mikrostruktury. Wyniki te z powodzeniem zweryfikowano badaniami metodą metalograficzną. Stwierdzono, że metoda termograficzna umożliwia uzyskanie dobrej wiarygodności oceny stanu zmian mikrostruktury łopatek.
9
Content available Diagnostics of Composite Aircraft Structures Using Non-Destructive Tests with Thermographic, Ultrasound and Acoustic Methods
Dragan K., Kornas Ł., Latoszek A., Salaciński M.
Fatigue of Aircraft Structures
|
2010
|
Iss. 2
19--22
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