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Tytuł:
Rapid prototyping process of monocrystal aircraft engine blades
Autorzy:
Budzik, G.
Matysiak, H.
Cygan, R.
Bąk, S.
Cygnar, M.
Powiązania:
https://bibliotekanauki.pl/articles/245805.pdf
Data publikacji:
2009
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
rapid prototyping
monocrystal
aircraft engine
blades
Opis:
The article presents process application of the rapid prototyping (RP) for manufacturing of blades of aircraft turbine in mono- crystallization and also directional crystallization of casting process. It is describing the method of modeling of the chosen elements of casting model kit with the usage of RP and RT systems. The article presents the analysis of a additive rapid prototyping methods (stereolithography) in an aspect of manufacturing of casting models. The possibilities of RP system usage to the ceramic form were the main criteria of the analysis. The ceramic form is a one of the parts of process casting of monocrystal blade of aircraft engine. In the article the possibilities making of models by means of rapid tooling system based on the Vacuum Casting (VC) technology were also analysed. The Vacuum Casting technology allows producing the silicone mould under decreasing pressure. Silicone tools allow creating wax casting models as a vacuum casting process, casting process and low pressure of injection. Rapid prototyping and rapid tooling technologies allow creating casting wax models of a blade and other parts of casting models. RP and RT methods allow creating connectors of the parts. These connectors allow connecting the parts of model kit in a fast and simple method. The stereolithography and Vacuum Casting allow accelerating process of manufacturing of monocrystal blades of aircraft engines.
Źródło:
Journal of KONES; 2009, 16, 4; 23-28
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Rapid prototyping process of monocrystal aircraft engine blades
Autorzy:
Budzik, G.
Matysiak, H.
Cygan, R.
Bąk, S.
Cygnar, M.
Powiązania:
https://bibliotekanauki.pl/articles/246158.pdf
Data publikacji:
2010
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
rapid prototyping
monocrystal
aircraft engine
blades
Opis:
The article presents process application of the rapid prototyping (RP) for manufacturing of blades of aircraft turbine in mono- crystallization and also directional crystallization of casting process. It is describing the method of modelling of the chosen elements of casting model kit with the usage of RP and RT systems. The article presents the analysis of additive rapid prototyping methods (stereolithography) in an aspect of manufacturing of casting models. The possibilities of RP system usage to the ceramic form were the main criteria of the analysis. The ceramic form is a one of the parts of process casting of monocrystal blade of aircraft engine. In the article the possibilities making of models by means of rapid tooling system based on the Vacuum Casting (VC) technology were also analysed. The Vacuum Casting technology allows producing the silicone mold under decreasing pressure. Silicone tools allow creating wax casting models as a vacuum casting process, casting process and Iow pressure of injection. Rapid prototyping and rapid tooling technologies allow creating casting wax models of a blade and other parts of casting models. RP and RT methods allow creating connectors of the parts. These connectors allow connecting the parts of model kit in a fast and simple method. The stereolithography and Vacuum Casting allow accelerating process of manufacturing of monocrystal blades of aircraft engines.
Źródło:
Journal of KONES; 2010, 17, 1; 81-86
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Phase mapping in the diagnosing of a turbojet engine
Odwzorowanie fazowe w diagnozowaniu silnika turboodrzutowego
Autorzy:
Kowalski, M.
Powiązania:
https://bibliotekanauki.pl/articles/281694.pdf
Data publikacji:
2012
Wydawca:
Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:
aircraft engine diagnostics
phase mapping of engine parameters
Opis:
This paper describes possibilities of using the phase portrait for the diagnosis of the turbojet engine AŁ-21F3 type. Attention is paid to description of the theoretical basis of application of this method to identify the engine fuel system. The identification of the engine fuel system was conducted for each operating adjusting point according to the mono-selection 3r plan with variable data sampling period with a frequency equal to a constant submultiple of the engine rotation frequency. It is explained how the settings of the operational control of the AŁ-23F3 engine fuel system influence the shape of the phase characteristics of engine rotation speed. Additionally, the location of the phase portrait distinctive points is determined. Moreover, there are shown examples of phase portraits for selected ranges of engine operation. It is shown, as an example of using the phase mapping, the ability to monitor parameters of the automatic engine start up using the adjusting machine screw of the altitude corrector of the start-up automaton and changes of the diameter of the start-up automaton nozzle. It is also shown that the qualitative analysis of the adjustment of specific ranges of engine operation is sufficient to determine the influence of the individual adjusting points for those operating ranges.
W referacie przedstawiono możliwości wykorzystania portretu fazowego do diagnozowania turbinowych silników odrzutowych typu AŁ-21F3. Opisano podstawy teoretyczne zastosowania tej metody do identyfikacji układu paliwowego silnika. Identyfikację układu realizowano dla każdego punktu regulacji eksploatacyjnej, zgodnie z planem monoselekcyjnym 3r, ze zmiennym okresem próbkowania danych, z częstotliwością równą stałej podwielokrotności częstotliwości obrotowej silnika. Wykazano wpływ nastawy regulacji eksploatacyjnej układu paliwowego silnika AŁ-21F3 na kształt charakterystyk fazowych prędkości obrotowej. Określono położenie charakterystycznych punktów portretu fazowego. Przedstawiono przykłady portretów fazowych dla wybranych zakresów pracy silnika. Jako przykład zastosowania odwzorowania fazowego pokazano możliwość kontroli parametrów automatycznego uruchamiania silnika przy pomocy wkręta korektora wysokości automatu uruchamiania oraz zmiany średnicy dyszy automatu ruchamiania. Wykazano także, że do analizy jakościowej regulacji poszczególnych zakresów pracy silnika wystarczającym jest określenie wpływu poszczególnych punktów regulacyjnych na te zakresy pracy.
Źródło:
Journal of Theoretical and Applied Mechanics; 2012, 50, 4; 913-921
1429-2955
Pojawia się w:
Journal of Theoretical and Applied Mechanics
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Application of the phase reproduction method to the analysis of an avionic event on board of the W-3 "Sokół" helicopter
Autorzy:
Kowalski, M.
Powiązania:
https://bibliotekanauki.pl/articles/244580.pdf
Data publikacji:
2011
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engine diagnostics
phase mapping of engine parameters
Opis:
This paper presents a new approach to the study of events/cases of the use of so-called air mapping phase. The examinations were carried out by means of the selective method on the basis of data for basic operational parameters acquired from the both driving units of the W-3 "Sokół" helicopter. The analysis covered quality of information received from the S2-3a on-board recorder of flight parameters, in particular its resolution and recording frequency. Then it was possible to plot waveforms for variation of the recorded parameters associated with operation of the helicopter engines and its rotor. The waveforms were used to determine the most important fragments suitable for detailed analysis of variations exercised by basic parameters and to check them against the Operation Manual for flights of the W-3 helicopter. The selected operation parameters were used for phase imaging (development of phase portraits), which served as the basis to assess dynamic properties of the parameters variations. The final component of the study consisted in discussion of the obtained results with presentation of conclusions. It is infeasible to monitor technical condition of the package joint between the transmission shaft and the PZL-10W aircraft. It is necessary to install additional sensors and gauges intended to improve accuracy and frequency of parameter readouts. Only sufficient amount of information shall enable application of the phase imaging method to efficient monitoring of technical and emergency operating conditions of aircraft engines.
Źródło:
Journal of KONES; 2011, 18, 1; 301-310
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Development of the aircraft power plants - challenges
Autorzy:
Szczeciński, S.
Powiązania:
https://bibliotekanauki.pl/articles/242001.pdf
Data publikacji:
2008
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
transport
combustion engines
internal combustion aircraft engine
Opis:
On the background of a current level of the aircraft power plants modernities presented here is the trial settlement of the possible directions of their further development - resultant from the current and future economic, military, sports needs. The general direction of development of all types of aeronautical propulsion systems, and also of these produced a long time ago and exploited for many years, is their permanent " upgrade" in the new equipment and of methodic of the current technical state checking for the purpose of the indispensable flights safety assurance, the prolongation of the failure-free exploitation time - but also the maintenance of the economic concurrency requirements. Recently, a categorical form receives the requirement of the noise limitation of aviation power plants and the limitation for emission of toxic elements in exhaust. In the piston engines, the direction of developments are aimed on the design of compression ignition engines, fuelled with standardized aircraft jet fuel. Their additional valour is their smaller fuel expenditure, about 30% less with respect to their spark ignition equivalents. Particularly important is the task of decrease the quantities of fuel used up, the limitation of number of produced engines through raising their efficiency and durability, limitation of noisiness of engines alone and driven: propellers, ventilators and the lifting rotors of helicopters, the limitation of thrust, required to the flight of the airplanes and the helicopters. One turned attention on ecological requirements, which force the application of mineral fuels completed by biofuels.
Źródło:
Journal of KONES; 2008, 15, 4; 545-555
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Influence of the selected exploitation tasks on airline operating cost and flight safety taking as an example turbofan engine
Autorzy:
Glowacki, P.
Powiązania:
https://bibliotekanauki.pl/articles/242859.pdf
Data publikacji:
2016
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engine
maintenance
exploitation cost
flight safety
Opis:
The total cost of the aircraft maintenance was in 2012 about $ 80 billion, including maintenance, repair and overhaul, ie. MRO market (Maintenance, Repairs and Overhaul), the operators of these aircraft have spent about $ 60.7 billion – of which 40% were direct maintenance costs of the engines. It can be concluded that main influencer on airline direct maintenance costs are spending for power plants. The article shows that the appropriate exploitation of the engine, leading not only to the total operating costs (mainly the cost of fuel and maintenance) reduction. Also through continuously engine health monitoring, resulting in a higher reliability, and thereby increases the safety of flying and – what is now especially important – by decreasing fuel consumption reduces greenhouse gas and exhaust toxic components emissions. The modern aircraft engine and its basic performances were described. Based on data, analysis from approximately twenty thousand flights of the specific operator and self-experience, the benefits from the use of specific maintenance and operational tasks are presented. Results of the calculations were demonstrated which proved that engine life extension between overhaul (TBO) has impact on the operator’s maintenance reserves reduction, positive cash flow and fuel cost savings. The article confirms that it need not be contradiction between aircraft operator economic effect, and the improvement of safety of flying.
Źródło:
Journal of KONES; 2016, 23, 2; 129-136
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Study on kerosene atomization process under a high speed air stream
Autorzy:
Perkowski, W.
Irzycki, A.
Snopkiewicz, K.
Grudzień, Ł.
Kawalec, M.
Powiązania:
https://bibliotekanauki.pl/articles/247137.pdf
Data publikacji:
2011
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
transport
aircraft engine
combustion chamber
fuel atomization
Opis:
For the needs of fuel-injection system development for the experimental detonation combustion chamber with a rotating detonation (PoiG - Project: "Turbine engine with detonation combustion chamber") a series of experiments with injection of kerosene under a high speed air stream was performed at the Institute of Aviation. The proper preparation of combustible mixture is very important for the initiation and sustenance of a rotating detonation. The task in case of kerosene-air mixture is far more difficult than for mixtures of hydrogen-air or kerosene-oxygen. A simple stream injector has been tested as a base system, and the kerosene was injected perpendicular to the air stream vector directly from the plane wall of the constant cross-section channel. The process of injection and atomization of kerosene was observed in the special transparent visualization chamber, enabling the spray observation of two mutually perpendicular directions. In subsequent experiments air pressure, air temperature and air flow velocity as well as and injection pressure of kerosene were varied. The tested process was photographed and, in case of chosen experiments, filmed using a high-speed digital camera. The surveys were aimed at identifying and assessing of following parameters of fuel atomization process: the range of the fuel stream and filling grade of research channel with aerosol, aerosol homogeneity and the size of forming it droplets, the possible presence of fuel streams flowing down the walls of channel. The resulting photos allowed for more comprehensive, but only a qualitative assess of the spraying process, while the filmed small regions of visualization chamber allowed the counting down and dimensioning of droplets. This paper presents a test facility and measuring techniques applied during the research activity and selected results of carried out tests.
Źródło:
Journal of KONES; 2011, 18, 4; 341-347
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Aircraft engines : analysis of reported systems failures in Polish aviation during years 2008-2015
Autorzy:
Balicki, W.
Glowacki, P.
Powiązania:
https://bibliotekanauki.pl/articles/243587.pdf
Data publikacji:
2016
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engine
failure
engine system
ATA chapter
safety system
Opis:
Aircraft engine failure during different aircraft flight phases can cause accidents or incidents. ICAO Annex 19 requires from each state establishing the state safety program (SSP) and from the subordinate aviation organizations safety management system (SMS). Point 5.2.1 of Annex 19 instructs to establish safety database, which should be used for effective analysis of actual and potential safety deficiencies. Such analysis should lead to determining necessary measures in order to improve safety. Polish Civil Aviation Authority among other databases manages an important one called European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS). The authors have done a laborious processing of the data contained in that database analysing engine failures based on criteria like phases of flight, ATA chapters concerning powerplant and category of the occurrence. Separately, under consideration were taken engines installed on aircraft with an MTOM <5700 kg (mainly General Aviation) and for aircraft with MTOM > 5700 kg (commercial aviation). The article presents a proposed method of predicting the number of events, the alert levels for the next years and for ATA chapters’ determination, assuming a normal distribution (Gaussian). It is one of the first attempts to use the actual data contained in the database of events in Poland. The results of this analysis can support the decisions of supervisory authorities in the areas where security threats are most important.
Źródło:
Journal of KONES; 2016, 23, 1; 31-37
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Researches of the dynamic characteristics of the turbine jet engine in flight based on its ground tests
Autorzy:
Golak, K.
Lindstedt, P.
Grądzki, R.
Powiązania:
https://bibliotekanauki.pl/articles/247300.pdf
Data publikacji:
2016
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
jet engine
adjustment
ground tests
engine condition
aircraft engine maintenance
Opis:
Turbine jet engines maintenance (adjustment) actions are performed during standard ground tests, but they are used during the flight. It turns out that the characteristics of the engine determined during the ground tests from the input value "w" introduced by the engine control lever DSS are significantly different from those obtained from disturbance “z" operating in the engine during the aircraft flight. It is noticed, that improvement of the engine control state made by mechanic during aircraft ground tests may cause the deterioration of the engine performance, which is felt by the pilot. The article presents a method that allows determining the basic characteristics of the engine in flight based only on the signals measured during testing ground. This method is based on measurement the major engine signals n – engine rpm, p4 – turbine discharge total pressure, p2 – low pressure compressor inlet, mp – fuel usage, then the designation of synthetic signals y=n/p4 (which describes the engine output), u=mp/p2 (describes engine input) and further their own and cross correlation function. Next, the power spectral density functions of these synthetic signals were calculated. Power spectral density functions is a basis to determine the spectral transfer function HW(jω) (during the ground tests) and HZ(jω) (in flight) which are the basis to determine the characteristics (step response) of the turbine jet engine in flight and during ground tests.
Źródło:
Journal of KONES; 2016, 23, 3; 151-156
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Pracownia Zawieszeń Magnetycznych Laboratorium Badań Napędów Lotniczych WAT
Magnetic Suspension Workroom of Aircraft Engine Laboratory in Military University of Technology
Autorzy:
Olejnik, A.
Falkowski, K.
Henzel, M.
Powiązania:
https://bibliotekanauki.pl/articles/276598.pdf
Data publikacji:
2013
Wydawca:
Sieć Badawcza Łukasiewicz - Przemysłowy Instytut Automatyki i Pomiarów
Tematy:
zawieszenia magnetyczne
silnik lotniczy
magnetic suspension
aircraft engine
Opis:
W artykule opisane zostały efekty realizacji projektu POIG.02.02.00-14-022/09 Programu Operacyjnego Innowacyjna Gospodarka, którego głównym celem było utworzenie w Wojskowej Akademii Technicznej Laboratorium Badań Lotniczych. W Laboratorium powstała m.in. Pracowania Zawieszeń Magnetycznych, która będzie prowadzić unikalne w skali Kraju i Unii Europejskiej numeryczne oraz doświadczalne badania nad opracowywaniem pasywnych i aktywnych zawieszeń magnetycznych, ich optymalizacją, sterowaniem, zasilaniem itp. Działalność Laboratorium będzie nakierowana na rozwiązywanie problemów napędów lotniczych i w istotny sposób przyczyni się do rozwiązywania problemów eksploatacyjnych, umożliwi modernizację testowanych konstrukcji, jak również projektowanie nowych.
In the paper are presented results of realization in Military University of Technology of The Innovative Economy Programme. The main goal of the project is organization of the Aircraft Engines Research Laboratory. There are the Magnetic Suspension Workroom. There are realized the unique in Poland and European Union research investigations under passive and active magnetic suspensions, their optimization, control, supplying, etc. The Engine Laboratory will find solutions of operation problems, reliability of constructions. It makes possible modernization of investigated constructions and designing practical of new applications.
Źródło:
Pomiary Automatyka Robotyka; 2013, 17, 2; 245-249
1427-9126
Pojawia się w:
Pomiary Automatyka Robotyka
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Estimation of turboprop engine parameters for various fuels
Autorzy:
Jakubowski, R.
Ciechanowicz, M.
Powiązania:
https://bibliotekanauki.pl/articles/245965.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engine
fuel
turboprop engine
silnik lotniczy
paliwo
silnik turbośmigłowy
Opis:
The analysis of work parameters of a turboprop engine fuelled by various fuels was done in the article. The turboprop engine model was presented in the beginning. The main feature of this model is description of the flow in the engine as semi-perfect gas model. By this way, the change of fumes chemical composition influence the gas properties as heat constant and isentropic index are determined. Next energy balance of a compressor and turbine was analysed and turbine pressure drop was evaluated. Finally, engine output power was determined. It was done for selected fuels, which could be applied in the aero engines. The results of analyse were presented in the tables and charts and discussed. Summary of the test results with the results for contemporary applied fuel allows drawing the conclusions about the turboprop engine performance change by various fuel application. Main of them refers to the point that higher combustion heat value of fuel and higher heat constant of fumes cause better engine work conditions By this way the hydrogen seems to be perspective fuel of future, because its combustion heat value is three times JET A-1 and by this way it is possible the engine fuel consumption will be lower.
Źródło:
Journal of KONES; 2017, 24, 1; 203-210
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Application of visual test methods loaded elements of rotating machinery flow to assess their condition
Zastosowanie wizyjnych metod badań obciążonych elementów wirnikowych maszyn przepływowych do oceny ich stanu technicznego
Autorzy:
Warczek, J.
Juzuń, M.
Powiązania:
https://bibliotekanauki.pl/articles/198416.pdf
Data publikacji:
2016
Wydawca:
Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:
non-destructive tests
aircraft engine diagnostics
condition of aircraft engine assess
badania nieniszczące
diagnostyka silników lotniczych
oszacowanie stanu technicznego silnika lotniczego
Opis:
The article presents the aims and objectives of the process of non-destructive testing of turbine aircraft engines using visual methods indirect use of endoscopy. Presents brief characteristics of the construction of engines tested, analyzed the diagnostic procedures used in non-destructive testing methods are shown diagnostic equipment used in research. The paper presents examples of the results of diagnostic checks obtained for the test aircraft engine.
W artykule przedstawiono cele i założenia procesu badań nieniszczących lotniczych silników turbinowych przy użyciu metod wizualnych pośrednich, z wykorzystaniem endoskopii. Przedstawiono krótkie charakterystyki budowy badanych silników, przeanalizowano procedury diagnostyczne, wykorzystywane w metodach badań nieniszczących, przedstawiono sprzęt diagnostyczny wykorzystany w badaniach. W artykule przedstawiono przykładowe wyniki sprawdzeń diagnostycznych, uzyskane dla badanego silnika lotniczego.
Źródło:
Zeszyty Naukowe. Transport / Politechnika Śląska; 2016, 90; 195-204
0209-3324
2450-1549
Pojawia się w:
Zeszyty Naukowe. Transport / Politechnika Śląska
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical Simulation of Fatigue Fracture of the Turbine Disc
Autorzy:
Witek, L.
Powiązania:
https://bibliotekanauki.pl/articles/97889.pdf
Data publikacji:
2012
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
aircraft engine
crack propagation analysis
finite element method
fatigue fracture
Opis:
This paper presents the results of the crack propagation analysis of an aircraft engine turbine disc. In the first part of the work the finite element method was used for calculation of the stress state and the stress intensity factor (SIF, KI, K-factor) in the turbine disc with an embedded quarter-elliptical corner crack, subjected to low-cycle thermo-mechanical fatigue. To refine the K-factor calculation, specially degenerated finite elements were used. These elements provide stress singularity suitable for the linear-elastic material of the disc. The performed calculations yielded the stress intensity factor KI for different crack sizes. Subsequently, ΔK parameter was determined as a difference of the KI values calculated for the turbine’s speeds equal to 6373 and 14200 RPM. Based on the Paris-Erdogan equation and the obtained ΔK values, the fatigue crack growth plot for the turbine disc subjected to complex thermo-mechanical loads was determined.
Źródło:
Fatigue of Aircraft Structures; 2012, 4; 114-122
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Aspekty metrologiczne bezdotykowego diagnozowania wirujących łopatek sprężarki
Metrological aspects of non-contact roating blade measurements
Autorzy:
Witoś, M.
Kowalski, M.
Powiązania:
https://bibliotekanauki.pl/articles/209146.pdf
Data publikacji:
2008
Wydawca:
Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:
odstęp czasu
nierównomierne próbkowanie
łopatki
zmęczenie
silniki lotnicze
diagnostyka silników lotniczych
tip timing
nonuniform sampling
blades
fatigue
aircraft engine
diagnosis of aircraft engine
Opis:
Przedstawiono podstawy teoretyczne stosowania elastycznego znacznika fazy - wirującej i drgającej łopatki sprężarki - do kompleksowego diagnozowania turbinowego silnika lotniczego (metoda tip timing). Wskazano na rolę numerycznych metod analizy w rozdzieleniu składowych sygnału pomiarowego (aperiodycznej i oscylacyjnej) oraz potrzebę weryfikacji istniejących algorytmów analizy danych, pochodzących z nierównomiernego próbkowania. Omówiono 15-letnie spostrzeżenia eksploatacyjne stosowania metody na samolotach TS-11 "Iskra".
The paper presents theoretical background of using elastic key phasor-rotating and vibrating compressor blade - for complex jet engine diagnosis (tip timing method). The role of numerical methods of measurement signal decomposition onto parts (aperiodic and oscillation) is pointed. It also shows the need of existing algorithms (from irregular sampling) verification. Fifteen years' service knowledge of using mentioned method aboard T-11 "Iskra" is presented.
Źródło:
Biuletyn Wojskowej Akademii Technicznej; 2008, 57, 2; 289-299
1234-5865
Pojawia się w:
Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Influence of the cyclic hardening model on the results of the numerical analysis of fatigue life on example of the compressor blade
Autorzy:
Bednarz, Arkadiusz
Powiązania:
https://bibliotekanauki.pl/articles/245046.pdf
Data publikacji:
2019
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
fatigue life
compressor blade
aircraft engine
cyclic hardening
numerical analysis
Opis:
The main goal of the presented work is to determine the impact of the cyclic hardening model on the numerical results of the ε-N fatigue test. As an object of study, compressor blade (from PZL-10W helicopter engine) was used. The examined blade was made of EI-961 alloy. In numerical analysis, a geometrical model of the blade with a preliminary defect was created. Geometrical defect – V-notch was created on the leading edge. This defect was introduced in order to weaken the structure of the element and the possibility of observing the crack initiation process (in experimental tests). Material data to ε-N analysis, based on Manson-Coffin-Basquin equation, were estimated for Mitchell’s model. This model was built based on strength data provided by the steel producer. Based on three different models of cyclic hardening (Manson, Fatemi, and Xianxin), a number of load cycles were calculated. Load cycle during numerical analysis was represented as resonance bending with an amplitude of displacement equal to A = 1.8 mm. Obtained results were compared with experimental data. Additionally, the analytical model of ε-N fatigue (depending on the cyclic hardening) was prepared. All the work carried out has been summarized by a comprehensive comparative analysis of the results. Obtained results and dependencies can be used in the selection of an appropriate model of cyclic hardening in further fatigue tests of many aerospace elements.
Źródło:
Journal of KONES; 2019, 26, 2; 7-14
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Wyświetlanie 1-15 z 83

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