Temat: aircraft engines - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Fuels for aircraft engines
Paliwa w silnikach lotniczych
Autorzy:: Pągowski, Z.
Powiązania:: https://bibliotekanauki.pl/articles/213513.pdf
Data publikacji:: 2005
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: paliwa
silniki lotnicze
fuels
aircraft engines
Opis:: Paper presents range of issues, related to the development of airplane engine fuels, starting from the Wright Brothers first flight in a year of1903, through the First World War and Second World War eras, and introducing us into contemporary time of piston and turbine airplanes, demanding high performance fuels. Author presents composition and performance of contemporary fuels, passing in the last part of the paper to the fuel development posibilities in the XXI century, both-related with aircraft engine development and increase of public interest in renewable energy sources and their usage in aviation.
Artykuł przedstawia zakres problemów dotyczących rozwoju paliw lotniczych. Rys historyczny paliw lotniczych, począwszy od pierwszego lotu braci Wright w 1903 roku, poprzez czasy pierwszej i drugiej wojen światowych wprowadzają nas w czasy współczesne samolotów tłokowych i turbinowych wymagających paliw o wysokich osiągach. Autor przedstawia skład i osiągi współczesnych paliw, przechodząc w ostatniej części artykułu do możliwości rozwoju paliw lotniczych w XXI wieku, zarówno ze względu na rozwój napędów lotniczych i ze względu na wzrost zainteresowania odnawialnymi źródłami energii i ich wykorzystaniu w lotnictwie.
Źródło:: Prace Instytutu Lotnictwa; 2005, 4 (183); 70-74
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Numerical simulation of thermally loaded aircraft engine turbine blade covered with thermal barrier coating - TBC
Autorzy:: Łazarczyk, M.
Domański, R.
Powiązania:: https://bibliotekanauki.pl/articles/246553.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
turbine
TBC
coating
blade cooling
Opis:: The objective of this thesis is to present the impact of the turbine blade cooling on blade material temperature as well as to assess advantages and disadvantages of applied cooling method (TBC coating combined with internal cooling). To calculate the conjugated heat transfer analysis generating 3d model and mesh of the blade and its cooling was required. Model mesh was covered with boundary layer in order to properly simulate conditions near the blade walls and obtain accurate results. Calculated blade was put in the canal simulating hot combustion gasses flow. Geometry of model described above was created using Unigraphics NX5 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization was done in commercial pre--processor GAMBITŽ. Conjugated heat transfer analysis was conducted in program FLUENTŽ for two different cases, where the TBC material properties were changed. The goal of this thesis was to obtain temperature fields and distribution in the turbine blade airfoil and to evaluate if applied cooling is sufficient to cool down this thermally loaded part of the engine. Calculated results show that proposed blade heat protection with TBC and internal cooling canal is insufficient during steady state condition, especially on the blade leading and trailing edge. In these two locations, the TBC coating is overheated, and the high temperature level of blade material is unacceptable for materials used in jet engine turbine industry.
Źródło:: Journal of KONES; 2012, 19, 3; 271-277
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Examination of the dynamic properties of 1st stage rotor blades in one - pass engine compressors under operating conditions
Autorzy:: Szczepanik, R
Powiązania:: https://bibliotekanauki.pl/articles/242705.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: diagnostics of aircraft engines
compressor blade dynamics
Opis:: This article includes studies of vibration and stress amplitudes in the Is' stage rotor blades of jet trainer one-pass engine compressors before and after refurbishment in operating conditions. The presented results were obtained using SAD-2 blade vibration amplitude registering and measuring apparatus. The same tests were carried on the same one-pass engine after modernisation. Example oscillograms from the vibration tests of the 16 blades are shown in this article, where show the vibrations of three randomly selected one-pass engines after refurbishment (marked 1, 2 and 3) out of a total of 50 engines. The engine vibration spectra cover the full rotation speed range. The difference between the vibration amplitudes of 1st stage rotor blades, in one-pass engine compressors before and after the refurbishment, is results from the difference in how the blades were attached to the disc. Before modernisation the hammer-type root was used, whereas after refurbishment dovetail-type fittings were applied. Furthermore, it was confirmed that there is nocoupling via the blade disc occurred when the blades were arranged on the disc according to the sinusoidal order of their free vibration frequencies. In such cases recorded vibration amplitudes remain within the average range (from 100 to 120 MPa in terms of stress).
Źródło:: Journal of KONES; 2013, 20, 3; 395-404
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Impact of work of turbine adaptive engines for the natural environment
Autorzy:: Ćwik, D.
Kowalski, M.
Steżycki, P.
Powiązania:: https://bibliotekanauki.pl/articles/246614.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: noise of aircraft engines
environmental impact
jet engine turbine
emission of toxic compounds
aircraft engines
turbine jet engine
Opis:: The article describes the problem of the operation of turbine jet, adaptive engine work on the natural environment. In particular, the analysis of noise generated by turbine jet engines has been made. It points out possible directions of noise decrease with particular emphasis upon structural changes within the engines, the task of which is to reduce the noise mission. The example of the modernization is based upon the “bypass” type of one-flow turbine jet engine. The essay contains theoretical basis of calculation of the noise emission level and the results, which graphically indicate a relative level of noise of this type of engine depending upon the amount of discharged air and the diameter of the discharge nozzle and the radius, upon the basis of which the noise level is determined. This work also includes a comparison of the relative noise level of this type of engine with regard to one-flow turbine engine equipped with the function of air discharge to the environment and with regard to two-flow turbine jet engine equipped with air stream flow mixing device. The use of low-emission combustion chambers in the "bypass" turbine engine was indicated. This allowed addressing the problem of emissions of toxic exhaust components by this type of aircraft engines. At the same time, the dependence of this emission related to the mass of fuel used on the engine's thrust range was indicated. The article was concluded with a short summary.
Źródło:: Journal of KONES; 2018, 25, 4; 509-516
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Analysis of 1st stage compressor rotor blade stress and vibration amplitudes in one-pass jet engine
Autorzy:: Szczepanik, R.
Powiązania:: https://bibliotekanauki.pl/articles/244813.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: diagnostics of aircraft engines
compressor blade dynamics
Opis:: This paper considers 1st stage compressor blade dynamics in the one-pass jet engines of trainer aircraft. Research was carried out on an engine test bench using the SAD system and its results were compared with those obtained using the tensometric approach. In this paper presented basic dynamic properties of rotor blades, bench test of rotor blade dynamics, Bench tests of the dynamic behaviour of blades subjected to external impacts and then Comparison of strain gauge and SAD tip-timing results. Then discusses the results of tests assessing the accuracy of the 1987 ITWL device by comparing strain gauge signals with those recorded by SAD apparatus in a running engine. It also presented simultaneous vibration readings of all the rotor blades at selected rotation speeds. Also shows that increased stress in these blades may be due to repeated engine surges, normal and hot engine surges, entry into the engine of a foreign object. Among others selection and layout of rotor blades in the 1st stage of a one-pass engine compressor, stress amplitudes for rotor blade, stress in rotor blade, stress amplitudes, free inlet flow and smooth engine acceleration, vibration amplitudes, asynchronous vibrations are presented in the paper.
Źródło:: Journal of KONES; 2013, 20, 4; 441-450
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Modelling of vane and rotor blade rows in simulations of gas turbine performance
Autorzy:: Sznajder, Janusz
Powiązania:: https://bibliotekanauki.pl/articles/244955.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
mechanical engineering
engine parts
simulation
modelling
Opis:: A method of modelling of nozzle and rotor blade rows of gas turbine dedicated to simulations of gas turbine performance is proposed. The method is applicable especially in early design stage when many of geometric parameters are yet subject to change. The method is based on analytical formulas derived from considerations of flow theory and from cascade experiments. It involves determination of parameters of gas flow on the mean radius of blade rows. The blade row gas exit angle, determined in turbine design point is a basis for determination of details of blade contour behind the throat position. Throat area is then fixed based on required maximum mass flow in critical conditions. Blade leading edge radius is determined based on flow inlet angle to the blade row in the design point. The accuracy of analytical formulas applied for definition of blade contour details for assumed gas exit angle was verified by comparing the results of analytical formulas with CFD simulations for an airfoil cascade. Losses of enthalpy due to non-isentropic gas flow are evaluated using the analytical model of Craig and Cox, based on cascade experiments. Effects of blade cooling flows on losses of total pressure of the gas are determined based on analytical formulas applicable to film cooling with cooling streams blowing from discrete point along blade surface, including leading and trailing edges. The losses of total pressure due to film cooling of blades are incorporated into the Craig and Cox model as additional factor modifying gas flow velocities.
Źródło:: Journal of KONES; 2019, 26, 1; 183-190
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Influence of geometry and type of cooling holes on thermal load of combustion chamber
Autorzy:: Swiatek, M.
Domański, R.
Powiązania:: https://bibliotekanauki.pl/articles/246265.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
engine combustion chamber
combustor cooling
CFD
Opis:: The objective of this thesis is to compare various methods of combustor wall cooling and their effectiveness by numerical simulations. It was determined that the first task was to verify how much air is coming through single axial hole with 3.5% pressure drop between hot and cold part of combustion chamber. The results from this flow check serve as a base template for generating more accurate and precise models of single axial hole cooling as well as calculation of hole diameter for multihole cooling. Second task was to generate more sophisticated single hole model with boundary layer in order to better simulate the conditions in areas near the combustion chamber walls and get more accurate results. The same method was used to create multihole model. In order to compare efficiency, all created domains in every model have the same volume, model settings, operating and boundary conditions. Geometry of all models described above is created using SIMENS NX4 and SIMENS NX5 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization into a structural finite volume grid took place in commercial pre-processor GAMBITŽ (GAMBIT and FLUENT - commercial CFD codes from Ansy s Inc). The airflow andheat exchange will be calculated using program FLUENTŽ. The results were shown in the thesis in terms of several comparative pictures of the temperature fields in the combustion chamber domain, and graphs representing difference in temperature fields on cooling wall of the combustion chamber.
Źródło:: Journal of KONES; 2010, 17, 4; 485-494
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Combustor liner cooling methods - numerical simulation
Autorzy:: Lazarczyk, M.
Domański, R.
Powiązania:: https://bibliotekanauki.pl/articles/247755.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
engine combustion chamber
combustor cooling
CFD
Opis:: The objective of this thesis is to compare various methods of combustor wall cooling and to evaluate advantages and disadvantages of each applied cooling methods. It was determined that the flrst task was to verify how much air is coming through singe radial hole with 2.5% pressure drop between hot and cold part ofcombustion chamber. Flowcheck was calculated also to see how geometry of cooling hole affects hole effective area. Second task was to generale 3d model and mesh of both calculated types of cooling. Each model mesh was covered with boundary layer in order to better simulate conditions near the combustion chamber walls and obtain accurate results. In order to run back-to-back analysis, all created models have the same number of mesh elements, same materials used, samefluent settings, same operating and boundary conditions. Geometry of all models described above was created using Unigraphics NX4 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization was done in commercial pre-processor GAMBITŽ. The airflow and conjugated heat transfer analysis was calculated in program FLUENTŽ. The goal of this thesis was to obtain temperature fields and distribution in the combustion chamber domain (lip and panel wall) and to evaluate if applied cooling is sufficient to cool down heat loaded part of the combustor chamber.
Źródło:: Journal of KONES; 2010, 17, 4; 277-286
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Areas of Investigation into Air Intake Systems for the Impact on Compressor Performance Stability in Aircraft Turbine Engines
Autorzy:: Kozakiewicz, Adam
Adamczyk, Maciej
Wróblewski, Mirosław
Powiązania:: https://bibliotekanauki.pl/articles/2067549.pdf
Data publikacji:: 2022
Wydawca:: Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:: mechanical engineering
aviation
aircraft engines
compressor stall
compressors
Opis:: The high demands placed on aircraft turbine engines necessitate the use of the latest engine compressors which must be increasingly efficient and more robust due to the increased loads. The key safety issue in this context is to ensure compressor stability over all engine speed ranges and aircraft flight regimes. This paper presents selected areas of research into surge and stall of axial compressors used in aircraft turbine engines based on scientific publications in recent years. On the basis of the analysed literature the authors defined the main research areas into compressor surge, namely: air intake research, compressor research and combined air intake and compressor system research. On the background of the conducted analysis the authors has presented their own areas of research. The aim of this work is to search for an intake-compressor design more passively resistant to stall or surge phenomena without necessity of implementation of complex control systems to prevent compressor stall.
Źródło:: Advances in Science and Technology. Research Journal; 2022, 16, 1; 62--74
2299-8624
Pojawia się w:: Advances in Science and Technology. Research Journal
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Analysis of thermodynamic cycle influence of turbofan mixer engine on its performance
Autorzy:: Jakubowski, R.
Powiązania:: https://bibliotekanauki.pl/articles/245722.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
turbojet engines
modelling of turbojet engines
turbojet engine characteristics
Opis:: The turbofan engines are widely used as propulsion of the contemporary airplanes. In the military application the turbofan mixer engines are used. Although the turbofan mixer engines are applied for a long time, the information about exact analysis of their thermodynamic cycle and performance are still in complete. The thermodynamic cycle of the turbofan mixer engine is presented and discussed in this paper. Based on it the cycle parameters selection is discussed. Then the optimization of turbofan mixer engine cycle is presented. Final results present the influence of chosen engine cycle parameters on the engine performance. The results are analyzed and discussed. On the basis of them the conclusions are formulated. It is not such an easy process to choose for the turbofan mixer engine thermodynamic parameters. It is connected with the fulfilment of two important rules. The equalization of total pressure of mixer inflow streamfor mixer efficient work is the first of it. The other rule is connected with engine cycle optimization. As it is shown it is not possible to choose engine parameters to reconcile the demands of specific thrust maximization and specific fuel consumption minimization. The engine thermodynamics parameters selection process is the search of the compromise between these two demand fulfilments, very often including engine mass analysis.
Źródło:: Journal of KONES; 2009, 16, 4; 171-178
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Analysis of an aircraft engine start-up process on the example of the PZL-130 TC-II „Orlik” training aircraft
Autorzy:: Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/244355.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: diagnostics of aircraft engines
qualification tests of aircraft driving units
Opis:: The paper discloses the analysis of processes that take place during the start-up operation of the driving unit for the training aircraft of the TZL-130 TC-II Turbo-Orlik type. The aircraft is designed for selective and initial trainings at the Air Force School of “Little Eagles” in Dęblin. The driving unit comprises the PT6A-25C turbo-propeller engine from Pratt & Whitney combined with the four-bladed airscrew from Hatzell. It is specifically mentioned that data for the analysis were sourced from the S2-3a on-board recorder of flight parameters manufactured by the Air Force Institute of Technology (AFIT). The analysis was carried out both during ground and flight tests. The paper briefly outlines general structures and operation principles of typical start-up systems with the focus to their key components. Attention is paid to how important it is to select an appropriate start-up system to match the specific aircraft type and the guideline parameters for selection that should be adhered to are specified. Also there are disclosed the key mathematical relationships that are indispensable to design start-up systems and to find out their basic characteristics. It is emphasized that the start-up operation must be considered as a non-stationary process that lasts from the standstill state of the engine until the moment when the minimum required rpm is reached, sufficient to generate necessary power of the engine. In addition, the attention is paid to the fact that the value of the engine acceleration is crucial to the achievable start-up time that is deemed as one of key parameters for all start-up systems. It is demonstrated that to achieve the required level of acceleration, it is necessary to secure the so called overhead of the engine power which needs constant flow offuel and air into the combustion chamber of the engine. The last part of the paper comprises selected characteristic curves that were obtained from the analysis of the engine start-up processes both on ground and in flight. The final conclusions emphasize that the start-up system for the presented driving unit is really efficient and guarantees correct operation of the engine under any conditions.
Źródło:: Journal of KONES; 2014, 21, 3; 177-189
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Impact of the additives used in mineral jet fuels on the lubricating properties of synthetic fuels for turbine aircraft engines
Autorzy:: Dzięgielewski, W.
Kaźmierczak, U.
Kulczycki, A.
Ozimina, D.
Powiązania:: https://bibliotekanauki.pl/articles/245539.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: lubricity
fuels for turbine aircraft engines
synthetic components
additives
Opis:: Hydrocarbon containing synthetic fuels represent a promising alternative fuels. Despite different chemical compositions, their properties should be similar to properties of mineral fuels, as they are designed for the same drive units. The basic parameter related to the protection of the adequate service life of the power supply devices, including precision pairs, is lubricity. Lubricity depends on a number of factors, including these related to the chemical composition of fuel components and operating additives introduced into fuels in order to modify their properties. The preliminary results of research on the effect of additives: lubricating, anti-corrosion and anti-electrostatic once, on the lubricating properties of a synthetic fuel are shown in the paper. It was observed that there are relations between the content of additives and the dynamics of film formation. It is significant that this does not apply only to the lubricating additive, but also the additive, which protects the correct electrostatic balance by providing sufficiently high electrical conductivity of the fuel. This may indicate that the formation of a lubricating film remains in relation to the intensity of energy transport from the lubricated surface to the molecules of lubricating additives inside the film. The results shown in the paper preliminary confirm the hypothesis, that synthetic components of fuels change the concentration of ordered molecular structures (which are present in mineral part of fuels and which can be responsible for energy transport inside the lubricating film), what resulted in worse fuel ability to create protective film, and anti-electrostatic additive improves lubricity of blends of synthetic and mineral components.
Źródło:: Journal of KONES; 2018, 25, 2; 121-128
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Simulations of hot-gas flow in internally cooled cascade of turbine vanes
Autorzy:: Sznajder, Janusz
Powiązania:: https://bibliotekanauki.pl/articles/242679.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
mechanical engineering
engine parts
simulation and modelling
Opis:: An experiment in cooling of gas turbine nozzle guide vanes was modelled numerically with a conjugate viscousflow and solid-material heat conduction solver. The nozzle vanes were arranged in a cascade and operated in highpressure, hot-temperature conditions, typical for first turbine stage in a flow of controlled-intensity, artificiallygenerated turbulence. The vane cooling was internal, accomplished by 10 channels in each vane with cooling-air flow. Numerical simulations of the experiment were conducted applying two turbulence models of the k-omega family: k-omega-SST and Transition SST implemented in the ANSYS Fluent solver. Boundary conditions for the simulations were set based on conditions of experiment: total pressures and total temperature on inlet to cascade, static pressure on the outlet of the cascade and heat flux on the surface of cooling channels. The values of heat flux on the surface of cooling channels were evaluated based on Nusselt numbers obtained from experiment and varied in time until steadystate conditions were obtained. Two test cases, one with subcritical outlet flow, and another one, with supercritical outlet flow were simulated. The result of experiment – distributions of pressure, surface temperature, and heat transfer coefficients on the vane external surface were compared to results of numerical simulations. Sensitivity of the vane surface temperatures and heat transfer coefficients to turbulence models and to boundary-condition values of parameters of turbulence models: turbulence energy and specific dissipation of turbulence energy was also studied.
Źródło:: Journal of KONES; 2019, 26, 2; 151-158
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Optical measurement of aircraft engine turbine blades
Autorzy:: Budzik, G.
Kubiak, K.
Rokicki, P.
Dziubek, T.
Nowotnik, A.
Matysiak, H.
Cygan, R.
Tutak, M.
Boś, P.
Powiązania:: https://bibliotekanauki.pl/articles/247470.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines turbine blades
optical measurements
coordinate measuring technique
Opis:: Manufacturing of aircraft engine turbine blades requires control of blade geometric parameters at different stages of technological process. Acceleration and automation of measurement process can affect the duration of the finished item production. Modern technologies for measurement of aircraft engine turbine blades are based on numerical machines - measurement process is based on processing of numerical data obtained by measurement using coordinate measuring machines. The paper presents the opportunity of automation of aircraft engine turbine blades measurements using scanner ATOS II Triple Scan with blue light source technology. Coordinate measuring technique allows to specify full methodology for designation of complex dimensions of physical objects and transform them into a computer program space of coordinate measuring devices. Presented paper includes capabilities of device used in the study to improve the measurement process in the technological and economical aspects. Another issue described in the paper is impact of measurement performance in automatic mode on the quality of performance – the numerical model of surface, from the standpoint of accuracy and number of collected data points in time. The paper includes an analysis of conditions related to the measurement works, such as the process of preparing the model, measurement equipment and data processing capacity. As the result methodology for automated scanning measurements of aircraft engine turbine blades will be presented.
Źródło:: Journal of KONES; 2013, 20, 2; 21-26
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Analysis of dimensional accuracy of blade of aircraft engine using a coordinate measuring machine
Autorzy:: Budzik, G
Kubiak, Krzysztof
Zaborniak, M.
Przeszłowski, Ł.
Dziubek, T.
Cygan, M.
Tutak, M.
Matysiak, H
Powiązania:: https://bibliotekanauki.pl/articles/244267.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines turbine blades
optical measurements
coordinate measuring technique
Opis:: Technological process of aircraft engine turbine blades requires control of blade geometric parameters. Innovation technologies for measurement of aircraft engine turbine blades are based on coordinate numerical machines – measurement process is based on processing of numerical data obtained by measurement using coordinate measuring machines. The paper presents the opportunity of analysis of dimensional accuracy of aircraft engine turbine blades measurements using coordinate measuring machine (CMM). Coordinate measuring machine allows specifying full methodology for designation of complex dimensions of physical objects (blade of aircraft engine) and transforming them into a computer program space of coordinate measuring devices. Presented paper includes capabilities of device used in the study to improve the measurement process and blades geometry analysis in the technological and economical aspects. Another issue described in the paper is impact of measurement performance in automatic mode on the quality of performance – the numerical model of geometry, from the standpoint of accuracy and number of collected data points in time. Measurements using a coordinate measuring machine are among the most accurate methods of measuring. The paper includes an analysis of conditions related to the measurement works, such as the process of preparing the model, measurement equipment and data processing capacity. As the result, methodology of (CMM) measurements of aircraft engine turbine blades will be presented.
Źródło:: Journal of KONES; 2014, 21, 2; 33-37
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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