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:: 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: 4.

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: 5.

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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Skocz do pozycji: 6.

Tytuł:: Simulation investigation of rotor loads and blade deformations in steady states and at boundaries of helicopter flight envelope
Autorzy:: Stanisławski, J.
Powiązania:: https://bibliotekanauki.pl/articles/246484.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: helicopter
rotor loads
blade deformation
Opis:: Results of calculation of the helicopter main rotor loads and deformations of rotor blades are presented. The simulations concern level flight states and cases of boundary flight envelope such as wind gust, dive recovery and pull-up manoeuvre. The calculations were performed for data of the three-bladed articulated rotor of light helicopter. The method of analysis assumes modelling the rotor blades as elastic axes with sets of lumped masses of blade segments distributed along radius of blade. The model of deformable blade allows flap, lead-lag and pitch motion of blade including effects of out-of-plane bending, in-plane bending and torsion due to aerodynamic and inertial forces and moments acting on the blade. Equations of motion of rotor blades are solved applying Runge-Kutta method. Parameters of blade motion, according to Galerkin method, are considered as a combination of assumed torsion and bending eigen modes of the rotor blade. The rotor loads, in all considered cases of flight states, are calculated for quasi-steady conditions assuming the constant value of the following parameters: rotor rotational speed, position of the main rotor axis in air and position of swashplate due to rotor axis which defines the collective and cyclic control pitch angle of blades. The results of calculations of rotor loads and blade deflections are presented in form of timeruns and as distributions on rotor disk due to blade elements radial and azimuthal positions. The simulation investigation may help to collect data for prediction the fatigue strength of blade applying results for steady flight states and for definition the extreme loads for boundaries of helicopter flight envelope.
Źródło:: Journal of KONES; 2017, 24, 2; 239-246
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Modelling of helicopter main rotor aerodynamic loads in manoeuvres
Autorzy:: Kowaleczko, Grzegorz
Leśniczak, Andrzej
Powiązania:: https://bibliotekanauki.pl/articles/241695.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: helicopter
main rotor
aerodynamic loads
Opis:: The article discusses the method of modelling of the helicopter main rotor aerodynamic loads during steady state flight and manoeuvres. The ability to determine these loads was created by taking into account the motion of each blade relative to the hinges and was a result of the applied method of aerodynamic loads calculating. The first part of the work discusses the basic relationships that were used to build the mathematical model of helicopter flight. The focus was also on the method of calculating of the aerodynamic forces generated by the rotor blades. The results of simulations dedicated to the "jump to hover" manoeuvre were discussed, showing the possibilities of analysing aerodynamic loads occurring in unsteady flights. The main rotor is considered separately in an “autonomous” way and treated as a source of averaged forces and moments transferred to the hub. The motion of individual blades is neglected, and their aerodynamic characteristics are radically simplified. The motion of individual blades is neglected, and their aerodynamic characteristics are radically simplified. This can lead to significant errors when attempting to model dynamic helicopter manoeuvres. The more complex model of helicopter dynamics is discussed.
Źródło:: Journal of KONES; 2019, 26, 4; 273-284
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Simulation of boundary states of helicopter flight
Autorzy:: Stanisławski, Jarosław
Powiązania:: https://bibliotekanauki.pl/articles/245041.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: helicopter
boundary flight
rotor loads
Opis:: Results of simulation of main rotor blade loads and deformations, which can be generated during boundary states of helicopter flight, are presented. Concerned cases of flight envelope include hover at maximum height, level flight at high velocity, pull-up manoeuvres applying cyclic pitch and mixed collective and cyclic control. The simulation calculations were executed for data of light helicopter with three-bladed articulated rotor. For analysis, the real blades are treated as elastic axes with distributed masses of blade segments. The model of deformable blade allows for out-of-plane bending, in plane bending, and torsion. For assumed flight state of helicopter, the equations of rotor blades motion are solved applying Runge-Kutta method. According to Galerkin method, for each concerned azimuthal position of blade the parameters of its motions are assumed as a combination of considered bending and torsion eigen modes of the blade. The loads of rotor blades generated during flight depend due to velocity of flight, helicopter mass, position of rotor axis in air and deflections of swashplate that correspond to collective and cyclic pitch angle applied to rotor blades. The results of simulations presenting rotor loads and blade deformations are shown in form of timeruns and as plots of rotor-disk distributions. The simulations of helicopter flight states may be useful for prediction the conditions of flight-tests without exceeding safety boundaries or may help to define limitations for manoeuvre and control of helicopter.
Źródło:: Journal of KONES; 2019, 26, 2; 137-144
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: A simulation analysis of behaviour of ship-borne helicopter main rotor due to ship motion
Autorzy:: Stanisławski, J.
Powiązania:: https://bibliotekanauki.pl/articles/243038.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: helicopter
rotor blade
ship deck operation
Opis:: The paper presents a simulation method of analysis of the couplings between rotor blades motion and helicopter fuselage standing on ship deck at the phase of take-off or landing when whirling rotor generates thrust less than weight of the helicopter. The oscillating motion of the ship deck due to waves is considered. The physical model includes the helicopter fuselage treated as the stiff body supported by units of springs and dampers corresponding to landing gear characteristics. The rotor blades are modelled by elastic axes with distributed lumped masses of blade segments. The equations of fuselage and rotor blades motion are solved applying Runge-Kutta method. According to the Galerkin method, parameters of rotor blades motion are assumed as a resultant combination of considered blade torsion and bending eigen modes. Data of the light helicopter with three-bladed rotor are applied for the simulation of the rotorcraft behaviour aboard the ship. The calculations concerning helicopter standing on the fixed plane and on oscillating ship deck show influence of ship movement on fuselage motion and rotor blades deflections, flapping, and lead-lag motion. Moreover, simulations show influence of the side wind and control of the rotor swash-plate deflections. The additional unit of blade eigen modes and frequencies is applied to model the blade hitting to the flapping limiter, which can occur at the low rotation speed of the rotor. Temporary contact of the articulated blade with limiter changes its boundary conditions, which can rapidly increase the blade bending moments. The simulation method enables to determine conditions of safe operations of ship-borne helicopters without exceeding the limits and generating the excessive blade loads.
Źródło:: Journal of KONES; 2016, 23, 1; 313-320
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Numerical simulation of vortex ring state phenomenon for the Mi2 type helicopter tail rotor
Autorzy:: Zalewski, W.
Powiązania:: https://bibliotekanauki.pl/articles/245648.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: air transport
helicopters
tail rotor VRS
Opis:: The paper presents computational simulations of loss of helicopter tail rotor effectiveness (LTE) effect caused by rotor vortex ring state (VRS) phenomenon. The phenomenon is critical for safety of helicopter operations and it was an important factor in some military and civil helicopters serious accidents. Analysis was conducted on the example of the tail rotor of Mi2 and PZL Kania single main rotor medium helicopters, which are still in wide use in some parts of the world. That kind of dual blades tail rotor was designed with symmetrical NACA0012 airfoil. Full three-dimensional analysis of the flow around real geometry of the rotor blades was conducted by application of commercial solver Ansys Fluent. The simulation was made by resolving Unsteady Reynolds Averaged Navier Stokes equations by finite volume method with use of Moving Mesh and Moving Reference Frame techniques. A hover turn over a spot was chosen as flight condition of helicopter, which could induce the LTE phenomenon. Thrust and power consumption were estimated during computations. Visualization of the flow field and pathlines of the flow were presented for chosen stages of vortex ring formulation around the rotor. The sensitivity of dual blades tail rotors, which are popular in light and medium type of helicopters to LTE phenomenon, was estimated.
Źródło:: Journal of KONES; 2016, 23, 2; 437-442
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Innovative composite gyroplane rotor blades : fatigue tests
Autorzy:: Wojtas, M.
Sobieszek, A.
Szczepanik, T.
Powiązania:: https://bibliotekanauki.pl/articles/241581.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: rotor blades
fatigue tests
NDT
composite
Opis:: The paper presents test bench method for verifying the fatigue life of the rotor blades, working in operating conditions in a position steady flight (autorotation), on the aviation construction called the gyroplane. One of the critical elements of this design is the main rotor, which in its modern versions takes the form of advanced composite structures subjected to loads in flight complex variable, the nature of which differs from the well-known operating conditions of helicopter rotors. The article includes a description of the test object, which are composite rotor blades designed specifically to work in autorotation, the specificity of loads of autorotation rotor, and method of implementation of the gyroplane rotor work cycles in the test bench. The main aim of this research is to evaluate the sustainability of the composite blades under the gyroplane operating loads with the goal to allow the rotor to operate in the air. The tests were carried out for 100 hours of gyroplane flight at loads do not exceed the maximum operating loads, and for several hours under a load higher than operating. During test for the evaluation of composite structure, the infrared camera with dedicated software IRNDT was used. The reached showed structural integrity in critical mounting section of the blade.
Źródło:: Journal of KONES; 2018, 25, 4; 447-453
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: 2019Gyroplane rotor hubs strength tests
Autorzy:: Wojtas, Małgorzata
Sobieszek, Agnieszka
Powiązania:: https://bibliotekanauki.pl/articles/242059.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gyroplane
strength tests
rotor hub
aviation regulations
Opis:: In this article a review of rotor,hub constructions were presented. Discussed rotor’s hub ismade of composite or aluminum alloys materials. Two types of rotor hub were presented (four-blades and two-blades teetering rotor hub), each of them are dedicated to gyroplanes. Typical gyroplane main rotors are characterized by simple design, especially in case of rotors forlight gyroplanes. In the following part of the article thetype of strength tests required by certification process were shown. The test programs based on legal aspects of admission to the flight tests taking into account legislation such as CS 27 (Subpart C – Strength Requirements), CAP 643 British Civil Airworthiness requirements Section T Light gyroplanes, ASTM F2972. Furthermore, this articlediscusses strength tests of gyroplane rotor hub such as measured parameters, methodology of measurement, types of sensors, course of test, test stands, and limit loads. The loads during “pull-up from level flight” manoeuvreare limit loads during tests. Required additional processes, like averification the same parameters by two types of method were shown i.e.deformation of structure were tested by strain gauges and reverse engineering.Strength tests had to be made before flight test, based on results of them aircrafts are flight authorized. In conclusion,the results of tests were presented and fulfilment of legal assumptions and requirements were shown.
Źródło:: Journal of KONES; 2019, 26, 3; 265-270
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Prototype test stand for testing insolated rotor systems
Autorzy:: Wojtas, Małgorzata
Czajkowski, Łukasz
Powiązania:: https://bibliotekanauki.pl/articles/242886.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: test stand
main rotor
design
construction resonance
Opis:: The article discusses assumptions for a prototype test stand designed for testing rotors in the conditions of work at their nominal speed, in particular gyrocopter and helicopter rotors. In the work presents an overview of similar solutions of test stand presented in the available literature and solutions proposed by companies, such as Swangate International or Luftfahrttechnik GmbH. Beyond these solutions the article also contains test stand used so far at the Institute of Aviation, these solutions were prepared for testing one type of rotor (for example: only for gyroplane rotors). The article provides the steps of designing a new test stand, which one of the basic assumptions is that it will be a universal test stand, giving the possibility to test different types of rotors. The article discusses two concepts of the stand with electric engine as a drive, gives the advantages and disadvantages of each concept, and indicates the selected solution. In addition to design and applied drive solution of the stand, the measuring part and data acquisition were also discussed. Moreover, the article focus on the advantages of rotor testing using the presented solution, as well as problems encountered during tests, in particular related to construction free vibrations and resonance. Vibration and resonance of the test stand are very important aspect of the entire design process, because it affects the quality and safety of the tests.
Źródło:: Journal of KONES; 2019, 26, 3; 257-264
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Diagnosing of rotor systems of marine gas turbine engines in nonstationary states
Autorzy:: Grządziela, A.
Powiązania:: https://bibliotekanauki.pl/articles/246906.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: dynamics
gas turbines
rotor vibration
run-up process
Opis:: Vibration tests of marine gas turbine engines are performed as researches on-line and off-line types. Systems on-line type generally monitored one or two vibration symptoms, which asses the limited and/or the critical values of parameters and they potentially can warn and/or shutdown engines. Systems off-line types are usually used for vibration analyzing during non-steady state of work. The paper presents comparison of different methods of analyzing vibration symptoms measured under run-up and shut-down processes of marine gas turbine engines. Results of tests were received on gas turbine engine DR76 type of the COGAG type propulsion system. The engine was not fitted with vibration monitoring system. Main goal of researches was qualified of help fulness 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). Second purpose was estimation of the possibility of implementation presented methods of vibration analyses of gas turbine engines for on-line monitoring system. Application of periodical or on-line diagnostic procedures makes it possible to operate ship propulsion systems in accordance with their current technical state. The realization of the investigations made reliable verification of the investigation results possible.
Źródło:: Journal of KONES; 2010, 17, 2; 121-127
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Aeroelastic analysis of helicopter rotor using virtual blade model and equivalent beam model of a blade
Autorzy:: Sieradzki, A.
Powiązania:: https://bibliotekanauki.pl/articles/242703.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: rotorcraft
helicopter
blade
aeroelasticity
rotor
aerodynamics
CFD
VBM
Opis:: Modern helicopter rotor blades design requires taking into account complex aeroelastic phenomena. Sophisticated computational fluid dynamics and structural dynamics models, available on the market, coupled together enable such analysis with very high fidelity. However, the computational cost of this type of simulation is usually very high and for this reason, it cannot be used in interactive design process or optimization run. Complex Fluid Structure Interaction models are excellent tools for validation purposes, but the design process requires simpler models with lower computational cost and still relatively high accuracy and capabilities. The paper presents a new efficient methodology for calculating helicopter rotor loads, deformations and performance. It uses the well-known Navier-Stokes equations aerodynamic solver – ANSYS Fluent, and modified Virtual Blade Model (based on Blade Element Theory) for rotor flow calculation. This connection guarantees exceptional capabilities and fidelity in comparison with simulation time. The dedicated structural dynamics solver, based on equivalent beam model of a blade and Finite Difference Method, was developed and coupled with CFD part using User Defined Functions in Fluent software. The accuracy of created module was validated with wind tunnel tests data of IS-2 helicopter rotor model, performed in Institute of Aviation. The results of calculations were compared with experimental data for a hover state and a forward flight with three different flight velocities. The comparisons showed very good agreement of the data in most of the analysed cases and pointed out new research possibilities. The presented aeroelastic helicopter rotor model combines all advantages of using three-dimensional Navier-Stokes solver with relatively low computational costs and high accuracy, confirmed by wind tunnel tests. It could be used successfully in helicopter rotor blades design process.
Źródło:: Journal of KONES; 2016, 23, 1; 297-304
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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