Temat: rotor - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Gyroplane rotors vibration tests
Autorzy:: Wojtas, M.
Trendak, M.
Powiązania:: https://bibliotekanauki.pl/articles/246317.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: rotor vibration
rotor blades
teetering rotor
hub connector
rotor imbalance
Opis:: The article presents vibration test of three different types of gyroplane main rotors. The test was carried out on a specially prepared test bench using a Red Led Tacho Sensor measuring system. Tests were conducted for the project „Research and development works on innovative construction of aircrafts of weight over 560 kilograms at the company Trendak Aviation”. The work outlines the basic properties of the gyroplane vibration and gives their sources. The research focused on the gyroplane main rotor vibration related inter alia to the rotor imbalance as well as rotor hub connector construction. Tested rotors consisted of three different types of gyroplane rotor blades and innovative universal hub connector with positive coning angle of 2.8º. The article summarized the basic properties of three types of gyroplane the rotor blade, marks advantages of use hub connector witch constructional dihedral angle. Discusses the principle of operation of measuring device, tests methodology starting from instrument calibration. The results of the measurements are shown in the graphs in polar coordinates. The vibration measurement is carried out in two axes, in x-axis, longitudinal, along the rotor radius and in y-axis, perpendicular to the x-axis, in the direction of the chord of the rotor blades.
Źródło:: Journal of KONES; 2017, 24, 4; 349-354
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: New gyroplane hub connector with positive coning angle
Autorzy:: Wojtas, M.
Trendak, M.
Powiązania:: https://bibliotekanauki.pl/articles/244662.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: blade dihedral angle
waving
rotor instability
teetering rotor
Opis:: The article presents advantages and disadvantages of two blade teetering rotors with constructional dihedral angle greater than 0o . Several structural design solutions of rotor hub connector are shown in this work. However, the main attention is focused on innovative hub connector design and manufactured by Trendak Aviation Company during the project “Research and development works on innovative construction of aircrafts of weight over 560 kilograms”. Discusses structural advantages of the new rotor hub connector according to other construction. Also were raised issues related to the load of the gyroplane rotor during the flight, in particular the load of rotor blades root, during a gyroplane break manoeuvre, according to conning angle of rotor hub connector. The disadvantages of using the structural dihedral angle in teetering rotors are also presented, focusing on the rotor aeroelastic instability so-called waving, which from the literature analysed is concerned only with two blades teetering rotors. Performed a coarse analysis in SMOG program, prepared at the Institute of Aviation for the analysis of helicopter and gyroplanes rotors. The stability analysis of the rotor for a number of structural dihedral angle and blades setting pitch was performed. Basis of this analysis the stability boundary were determined for the analysed gyroplane rotor with connector hub with positive coning angle of 2.8o. .
Źródło:: Journal of KONES; 2017, 24, 3; 325-330
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Comparison of higher harmonic contents in salient pole synchronous generator with different rotor construction
Autorzy:: Ludwinek, K.
Nadolski, R.
Staszak, J.
Powiązania:: https://bibliotekanauki.pl/articles/140521.pdf
Data publikacji:: 2017
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: salient pole synchronous generator
higher harmonics
solid rotor
rotor with radial incisions
laminated rotor
Opis:: The paper presents a comparison of higher harmonics in induced phase voltages of a stator winding in the no-load state of a three-phase 5.5 kVA salient pole synchronous generator. The comparison is carried out for the synchronous generator with different salient pole rotor constructions: a non-skewed solid rotor, a non-skewed solid rotor with radial incisions, and a laminated electrotechnical steel rotor with skewed slots and damping bars. The calculations of higher harmonics are based on the magnetic field distributions in the air gap, which are carried out in a 2D model in a FEMM program and on the induced voltage waveforms in the stator windings registered during experimental investigations of the 5.5 kVA salient pole synchronous generator in the no-load state.
Źródło:: Archives of Electrical Engineering; 2017, 66, 1; 121-139
1427-4221
2300-2506
Pojawia się w:: Archives of Electrical Engineering
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Analiza modalna i harmoniczna modelu zespołu elektrowibratora przy różnej konfiguracji ciężarów
Modal and frequancy analysis kit electrovibrator for different configuration of activators
Autorzy:: Madej, J.
Sitek, M.
Powiązania:: https://bibliotekanauki.pl/articles/386701.pdf
Data publikacji:: 2011
Wydawca:: Politechnika Białostocka. Oficyna Wydawnicza Politechniki Białostockiej
Tematy:: analiza drgań
analiza
wirnik
analysis
rotor
rotor vibration
Opis:: W niniejszym opracowaniu przedstawiono analizę częstotliwości drgań własnych i analizę harmoniczną zespołu wirnika wibratora elektrycznego. Otrzymane wyniki posłużą do optymalizacji poszczególnych elementów elektrowibratora, a w szczególności kształtu ciężarków oraz łap elektrowibratora, które często ulegają uszkodzeniu podczas pracy całego urządzenia. Znajomość maksymalnych wartości przemieszczeń ciężarków pozwoli z kolei na optymalizację kształtu osłony elektrowibratora.
This paper presents modal analysis and frequency analysis rotor kit of three-phase induction rotating electrovibrator. The received solutions will be use for optimization parts of electrovibrator, especially shape activators and foots of electrovibrator, it's often brake down. The knowledge about maximum translation of activators will be helpful for optimization of iron activator cover.
Źródło:: Acta Mechanica et Automatica; 2011, 5, 3; 87-90
1898-4088
2300-5319
Pojawia się w:: Acta Mechanica et Automatica
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Vibration of a mistuned three-bladed rotor under regular and chaotic excitations
Autorzy:: Warminski, J.
Latalski, J.
Szmit, Z.
Powiązania:: https://bibliotekanauki.pl/articles/280551.pdf
Data publikacji:: 2018
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: rotating beam
multi-bladed rotor
rotor mistuning
chaotic oscillations
Opis:: This study considers forced vibrations of a rotating structure consisting of a rigid hub and three flexible beams. The blades are nominally made of a multilayered laminate with a specific stacking sequence resulting in full isotropic macroscopic material behaviour. However, in the performed analysis it is assumed that the rotor has been mistuned because of manufacturing tolerances of the composite material. These inaccuracies are represented by deviations of reinforcing fibres orientations from their nominal values. The considered tolerances break the intended macroscopic material isotropy and make the laminate to exhibit the fully orthotropic behaviour. Based on previous authors research, the system of four mutually coupled dimensionless ordinary differential governing equations is adopted. Forced responses of the system under regular and chaotic excitations are investigated.
Źródło:: Journal of Theoretical and Applied Mechanics; 2018, 56, 2; 549-566
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Analysis of technological process of installation turbochargers
Autorzy:: Cygnar, M.
Mazurków, A.
Jaskólski, J.
Powiązania:: https://bibliotekanauki.pl/articles/244108.pdf
Data publikacji:: 2008
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: turbocharger
installation of turbocharger's group
turbine's rotor
compressor's rotor
Opis:: The technological process of installation of turbocharger as well as detailed analysis of chosen stages of installation having fundamental influence on the correct work of the turbocharger are presented in the article. The purpose of this article is performance of whole process of installation turbocharger as well as analysis of particularly significant stages of this process. The creature of turbocharging and it is myself this of working of turbocharger is enough simple. Difficulties appear if we put to the analysis conditions work of turbocharger: high temperature offumes, variable loads, aggressive environment of combustion gases, high rotatory speeds of rotors. Some of exploitation problems are possible to the elimination on the design stage or by means of application of appropriate materials. However technological process of installation is responsible for output quality and failure-free lasting work of turbocharger. In the process of installation it can distinguish some essential stages: processing and installation of shaft with the turbine's rotor, the weighing of turbine's rotor and the compressor, the installation of rotor's group, weighing of rotor's group in the trunk, positional tests under load. High rotary speeds cause during work of rotator so that created during of installation of turbocharger inappropriate balancing can bring to important damages of turbocharger. The correct course of process of installation and the final verification on braked position allows to avoid most of breakdowns of turbocharger group as well as to ensure long term of correct exploitation.From this reason very important is detailed analysis of respective stages of installation of group.
Źródło:: Journal of KONES; 2008, 15, 2; 35-39
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Interferencja wirnik nośny - wirnik ogonowy
Interference between the main and tail rotors
Autorzy:: Łusiak, T.
Powiązania:: https://bibliotekanauki.pl/articles/212441.pdf
Data publikacji:: 2006
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: interferencja
wirnik nośny
wirnik ogonowy
interference
main rotor
tail rotor
Opis:: W artykule przedstawiono modele zaburzeń opływu śmigłowca w płaszczyźnie wirnika ogonowego wywołanych bliskością wirnika nośnego. Przedstawiono model śladu zawirnikowego w oparciu o zasadę Biota i Savarta w celu określenia zaburzeń pola prędkości indukowanej przez wirnik nośny w płaszczyźnie wirnika ogonowego [4].
The influence of disturbances to the flow around a helicopter resulting from a resultant reaction of the wake from the main rotor on the tail rotor, on the loading as well as control and noise of the helicopter was presented. The analysis was based on a rotational model of the system. The basis of the model of the interference is the replacement of wake generated by rotors and fixed lifting surfaces by a uniform rotational model in the form of discrete rotational grids. This allows for the integration of fields induced through all rotational elements of the system, in accordance with the Biot-Savart law. This law was accepted in view of the fact that, as the only law included in the flow model, it enables a constant processing of load calculations in an undefined flight, with the retention of a reasonable calculation time. The undertaking of this subject should help explain phenomena not completely recognized and which exert a significant influence on safety when operating helicopters certain states of flight. The results of modeling, carried out for the SW4 helicopter, contain an evaluation of disturbances of the field of flow around the tail rotor in given states of flight, in which the case of take-off in a sidewind and with the carrying out of a directional maneuver is of primary significance. In other cases, when the tail rotor does not enter into intensive disturbances of the velocity field by the main rotor, the interference phenomena are of lesser importance. The numerical program used allows for information about flow around and loads on the taił rotor in flow disturbed by the (main) rotor to be obtained. Resultant loads on the tail rotor can be evaluated, along with its chosen elements.
Źródło:: Prace Instytutu Lotnictwa; 2006, 1-2 (184-185); 198-202
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Numerical simulation of model helicopter rotor in hover
Autorzy:: Doerffer, P.
Szulc, O.
Powiązania:: https://bibliotekanauki.pl/articles/1943245.pdf
Data publikacji:: 2008
Wydawca:: Politechnika Gdańska
Tematy:: transonic
hover
helicopter rotor
Opis:: The article presents details of a URANS simulation of the flow field near a hovering model of the Caradonna and Tung (1981) helicopter rotor [1]. The CFD code SPARC [2] proves to be capable of capturing the aerodynamics of a two-bladed rotor in high-speed transonic hover conditions. A comparison of the simulation results with the experimental data is acceptable, hence the described methodology might be used with confidence in future numerical studies of application of noise-reducing devices on helicopter blades.
Źródło:: TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk; 2008, 12, 3-4; 227-236
1428-6394
Pojawia się w:: TASK Quarterly. Scientific Bulletin of Academic Computer Centre in Gdansk
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Anomaly of rotor dynamics in ultra-light helicopter – Robinson R22
Autorzy:: Sobieszek, Agnieszka
Powiązania:: https://bibliotekanauki.pl/articles/242430.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: rotor hub
Robinson R22
helicopter
pull-up manoeuvre
rotor dynamics
Opis:: The article presents the analysis of anomaly of rotor dynamics in ultra-light helicopter - Robinson R22. Robinson R22 is two-seat, two-blade main rotor and single-engine helicopter, well known as simple and common used aircraft because of low price and high availability. At the same time, large number of accidents and strictly defined rules (recommended piloting technique) and weather condition for safe flight show disadvantages of Robinson R22. The reason for considering this topic is the analysis of different flight properties and helicopter behaviour as well as easy entering into dangerous flight manoeuvre. In the article different flight properties and loss of control during the pull-up, manoeuvre or vertical gusts of wind and mast bumping accidents were analysed. Analysis shows that problem may be caused by construction of three-hinged rotor hub, designed and patented by F. Robinson. Article presents model of rotor hub and review of main rotor and rotor hub construction in light helicopters. Because of number of accidents, caused by the unusual behaviour of Robinson R22, restrictive pilotage rules were introduced: prohibition of flight in certain weather conditions, the necessity of attending additional training conducted by trained instructors. To reduce the probability of an accident a special instruction for specific Robinson R22 properties was created. Moreover, the statistics of accidents resulting from loss of control and review of legal changes caused by Robinson R22 accidents are presented.
Źródło:: Journal of KONES; 2019, 26, 4; 235-239
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Power characteristics of inline rotor-stators with different head designs
Autorzy:: Hannam, Alex
Sparks, Trevor
Özcan-Taşkın, N. Gül
Powiązania:: https://bibliotekanauki.pl/articles/2034042.pdf
Data publikacji:: 2021
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: in-line rotor-stators
power characteristics
rotor-stator design
charakterystyka mocy
wirnik
Opis:: n-line rotor-stators are widely used for power intensive industrial applications, such as deagglomera- tion, emulsification. There is limited information on characteristic power numbers for different designs which can be used to calculate the average power input as a means to evaluate process performance. This study made use of 18 different rotor-stators, 17 of which were toothed designs with different geometry, and also a commercially available design, with the objectives of evaluating the applicability of different expressions for characteristic power numbers and establishing the effects of geometric variations on the power input. The expression P = Po1 ρN3 D5 + Po2 ρN2 D2Q is found to account for the experimental data over a wide range of operating conditions. Rotor diameter was found to have the most prominent effect on the power input: an increase in rotor diameter from 119.6 to 123.34 mm resulted in an increase in the average power draw. The effect of rotor diameter examined with geometrically similar set ups reducing the diameter from 123.34 to 61.44 mm, for which the mixing chamber was also proportionately smaller, showed a decrease in the power input at a given speed and flowrate as well. The effects relating to the percentage of open area of the stator and number of rotor teeth were less obvious. Increasing the open area resulted in an increase in the power input – an effect which could be observed more clearly as the flowrate (1 to 4 l/s) and rotor speed (at 2000 and 3000 rpm) were also increased. Increasing the number of stator teeth increased the power input and this effect was more prominent when operating at the highest rotor speed of 3000 rpm and at low flowrates (1–2 l/s).
Źródło:: Chemical and Process Engineering; 2021, 42, 2; 91-104
0208-6425
2300-1925
Pojawia się w:: Chemical and Process Engineering
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Vibration testing of a helicopter main rotor composite blade
Próby wibracyjne kompozytowej łopaty wirnika śmigłowca
Autorzy:: Parafiniak, M.
Skalski, P.
Powiązania:: https://bibliotekanauki.pl/articles/212647.pdf
Data publikacji:: 2011
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: próby rezonansowe wirników
kompozytowe elementy wirnika
rotor vibration tests
composite rotor elements
Opis:: The research presented in this paper focuses on a composite structure test. The object of the investigation is a blade from main rotor of the IS-2 helicopter. The basic methodology which is used is the Experimental Modal Analysis (EMA). The EMA technique is an established tool for the identification of dynamic properties of structure. Based on the experimental data collection, dynamic properties of a research object were estimated. The modal parameters have been estimated using PolyMAX – module of LMS Test.Lab software.
Badania przedstawione w pracy odnoszą się do prób struktury kompozytowej. Badany obiekt to kompozytowa łopata wirnika śmigłowca IS-2. Metoda badawcza jaka została użyta w próbach to eksperymentalna analiza modalna (ang. EMA). Technika ta jest uznanym narzędziem do identyfikacji własności dynamicznych konstrukcji. Na podstawie danych eksperymentalnych, własności dynamiczne zostały wyznaczone, za pomocą PolyMAX – modułu programu LMS Test.Lab.
Źródło:: Prace Instytutu Lotnictwa; 2011, 9 (218); 72-76
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Mechanical analysis process of a coaxial counter rotor for applications in unmanned ultra-light units
Proces konstrukcyjnej analizy mechanicznej współosiowego wirnika przeciwbieżnego do zastosowań w jednostkach ultralekkich
Autorzy:: Czajkowski, Łukasz
Powiązania:: https://bibliotekanauki.pl/articles/36402761.pdf
Data publikacji:: 2019
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: rotor analysis
coaxial rotor
ultra-light
analiza wirnika
wirnik współosiowy
ultra lekki
Opis:: As the rotor configuration has the most impact on helicopter properties, the process of determination the assumptions for rotor design is a very important factor in the early stage of rotorcraft development. The following paper presents a mechanical analysis process used at the Institute of Aviation to quickly develop a coaxial rotor prototype applicable in ultra-light unmanned helicopter which has the potential for further improvement of its flight parameters. The article describes the rotor analysis process due to its feasibility based on commercially available solutions, the process of formulating assumptions for the entire structure, MES analysis of the rotor parts all leading to creation of the rotor prototype.
Elementem, który ma największy wpływ na właściwości śmigłowca jest jego wirnik, dlatego bardzo ważnym czynnikiem jest określenie na wczesnych etapach procesu projektowania założeń, które wirnik powinien spełniać, aby wykonać misję, do której tworzy się projektowany śmigłowiec. Poniższy artykuł przedstawia proces analizy mechanicznej stosowany przez Instytut Lotnictwa do szybkiego opracowania prototypu współosiowego wirnika, stosowanego w ultralekkim bezzałogowym śmigłowcu, który ma potencjał do dalszego rozwoju w celu zmaksymalizowania jego parametrów lotu. W artykule opisano proces analizy wirnika ze względu na jego wykonalność w oparciu o komercyjnie dostępne rozwiązania, proces formułowania założeń dla całej konstrukcji, analizę MES części składowych wirnika prowadzące do powstania prototypu.
Źródło:: Transactions on Aerospace Research; 2019, 2 (255); 44-64
0509-6669
2545-2835
Pojawia się w:: Transactions on Aerospace Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Determination of best rotor length in solid-rotor induction motor with axial slitting
Autorzy:: Jagiela, M.
Garbiec, T.
Powiązania:: https://bibliotekanauki.pl/articles/140492.pdf
Data publikacji:: 2012
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: prądy wirowe
silnik indukcyjny
solid-rotor
induction motor
rotor-end factor
eddy currents
Opis:: The efficiency of the solid-rotor induction machines depends on axial length of rotor (including the end-regions). Determination of the best axial length is problematic because of current density distribution in the end-regions and also because of absence of dedicated methods and models. This work proposes a method that circumvents this difficulty. It is based on the numerical determination of a dimensionless rotor-end factor using a combination of three- and two-dimensional finite element models restricted to the motor rotor. Such the end factor can be used in both analytical and numerical model of the machine in order to determine the typical performance characteristics. In this work, using this method, we determined an optimal length of the slitted solid rotor of a motor operating at 12 000 rpm, that maximizes the motor efficiency. The results of computations and measurements, carried out on the laboratory test-stand, are presented.
Źródło:: Archives of Electrical Engineering; 2012, 61, 2; 267-276
1427-4221
2300-2506
Pojawia się w:: Archives of Electrical Engineering
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Cogeneration in Small Scale - High Speed Microturbines Dynamic Analysis
Autorzy:: Kiciński, J.
Powiązania:: https://bibliotekanauki.pl/articles/178044.pdf
Data publikacji:: 2010
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: cogeneration
micro-turbines
rotor dynamics
Opis:: Main energy conversion machinery used and to be used in cogeneration systems are schematically described. Some assets of the distributed generation are pointed out and small-scale cogeneration systems designed for energy units of distributed cogeneration are described. In the small scale, turbines and bearings are a source of specific problems connected with securing stable rotor operation. Accepted has been two kinds of high speed micro-turbines of electric power about 3 KW with multistage axial and radial rotors supported on foil bearings. A concept which becomes more and more attractive takes into account a low-boiling agent, which is normally used in the thermal cycle of the micro-turbine, as the lubricating liquid in the bearings (so-called ORC based systems). Of some importance is the operation of these machines at a low noise emission level, sine being parts of the household equipment they could disturb the calm of the residents. The scope of the present article is limited to the discussion of dynamic characteristics of the selected design. The properties of the rotor combined with slide bearings (foil bearings in this particular case) were taken under investigation. A combination of this type is a certain novelty since a typical modal analysis of such objects refers to a rotor itself. Analysing the dynamic state of the "home" power plants requires qualitatively novel research tools.
Źródło:: Archives of Acoustics; 2010, 35, 2; 175-182
0137-5075
Pojawia się w:: Archives of Acoustics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Vibration diagnostics of marine gas turbine engines
Autorzy:: Grządziela, A.
Charchalis, A.
Powiązania:: https://bibliotekanauki.pl/articles/244616.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: dynamics
gas turbines
rotor vibration
Opis:: Vibration tests of marine gas turbine engines are performed as researches on-line and off-line types. The paper presents analyses of both methods. Results of tests were received on three types of gas turbine engines operated in the COGAG type propulsion systems. The application of periodical diagnostic procedures or on-line monitoring systems makes it possible to operate ship propulsion systems in accordance with their current technical state. In the case of ship gas turbines the hourly period of scheduled maintenance or repair surveys is presently the criterion for maintenance time determination. The Finite Element Analysis (FEA) is used for confirmation actual technical state. FEA are used successfully for a wide range of problems and it may also be used for the modelling and analysis of rotor system. Presently, the diagnostics team uses FEA and the modelling of rotordynamics in conjunction with vibration analysis for detection and identification of unbalancing. Main goal of researches was qualified of helpfulness and unequivocally results received by methods of synchronous measurement, order tracking and auto tracking. All vibration symptoms were chosen from the methodology of the diagnosing gas turbine engines operated in the Polish Navy, called BDS (Base Diagnosing System). This element of BDS is accepted and used in all ships of Polish Navy, which are powered by the COGAG power plant. Second purpose of researches was estimation of the possibility of implementation presented methods of vibration analyses of gas turbine engines fornew, modern on-line monitoring system. The proposed diagnostics method makes it possible to determine the limiting value of vibration symptoms witch, if exceeded, indicates the inadmissible axis slope value between rotated machines of gas turbine engine and, more-over, it provides an unambiguous relationship between the value of symptom of rotors unbalance and the rotors rotational speed.
Źródło:: Journal of KONES; 2011, 18, 1; 157-162
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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