Wszystkie pola: engine-compressor - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Determination of the mechanical power losses of engine-compressor GMVH for diagnostic purposes
Autorzy:: Łutowicz, M.
Powiązania:: https://bibliotekanauki.pl/articles/244039.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: combustion engines
engine-compressor
indicating
MIP
pressure sensors
Opis:: The engine-compressors GMVH types are used in the national gas transmission system in Poland. There is a danger of scuffing of the working components of the engine-compressor particular pistons and cylinders during the process of their exploitation. The growth of resistance in motion parts of the machine is the main symptom of the scuffing. In the cinematic system of the engine-compressor where the engine and compressor are fully mechanically integrated it is impossible to assess the power of mechanical friction without stopping the machine. But if the engine-compressor is equipped with a cylinder pressure measuring system it is possible to determine the indicated power of all compressor and engine cylinders and assess the friction losses as a difference between the sum of the engine 's cylinder s indicated power and the sum of the compressor's cylinders indicated power. In the differential measurements of absolute values measuring errors are accumulated so considerable uncertainty of the measured parameter is expected. The accuracy of the friction power losses assessment method is not sufficient for research purposes. However, despite the expected significant errors, assessed parameters trends observation should allow to detect ofrapid changes of machine technical condition caused by piton scuffing. To ensure the sense of this method a precise measurements and in particular the error consistency of indicated pressure assessment of all cylinders in long time period are necessary. The experience from engine-compressors monitoring and diagnostic system services, the main sources of errors and methods for their minimization are described in the paper.
Źródło:: Journal of KONES; 2010, 17, 3; 279-286
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Preliminary evaluation of effective vibration analysis for the fault diagnosis of natural gas engine-driven compressor
Autorzy:: Listewnik, K.
Polanowski, S.
Dereszewski, M.
Żukowski, J.
Powiązania:: https://bibliotekanauki.pl/articles/247212.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: natural gas motor compressors
vibration diagnostics
Opis:: In this paper were presented results of preliminary research of the fault diagnosis of natural gas engine-driven compressor by vibration analysis. Natural gas engine-driven compressors are heavily exploited during delivering natural gas to the transmission network of Poland. Every failure brings about interferences to gas system, furthermore it causes notably cost of maintenances. The major failures are piston seizures and overly level of vibration causes by exceedingly wear, an unbalanced engine after repairs and dry friction. During research investigated three natural gas engine-driven compressors. Acceleration of engine cylinders was measured in cylinder axis and perpendicularly axis and acceleration of compressor cylinders, engine fundament and gas receiver in three axes. Results obtain during investigation of engine cylinders one gas engine-driven compressor collates with results of validation of engine cylinders after their stripping. Preliminary results of investigation indicate proper trend to set up diagnostic symptoms. It was found that for increasing of information amount is necessary to carry out synchronous measurements and its envelops in domain of crankshaft rotation angle. Very important source of diagnostic information can be shaft acceleration, determined basing on existing system of signals generation. The investigation is to be continued.
Źródło:: Journal of KONES; 2011, 18, 4; 243-250
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Assumptions of a method estimation for adjustments charakteristics of an engine and turbo-compressor set in sequential turbocharging
Założenia metody oceny dopasowania charakterystyk silnika i zespołu turbosprężarkowego w doładowaniu zakresowym
Autorzy:: Danilecki, K.
Powiązania:: https://bibliotekanauki.pl/articles/245757.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: doładowanie zakresowe
całkowita sprawność układu doładowującego
sequential turbocharging
optimum power distribution of turbochargers
total efficiency of a supercharging device
Opis:: The paper presents fundamentals characterising the operation of turbochargers and the dependencies essential for the calculation (the use of balance equations of a turbocharger this purpose ) of the total efficiency of a compressor set with respect to the power balance of the respective devices of aturbine. For the assumed conditions of the engine operation - an optimum power distribution has been carried out on the basis ofa theoretical analysis as far as the total efficiency is concerned in the compressor set and in theturbine set of a supercharging device. The required pressure drops in the turbine, essential to ensure the power in the compressor have been carried out with respect to the efficiency of each device. The paper pays attention on connected problems with the choice of the suitable design system range supercharging and secures favourable conditions its cooperation with the engine. This is especially important in phase switches over modes of operation between turbo-compressors and it has principle importance for the maintenance of the continuity of engine characteristics. In particular the entire efficiency of system supercharging was appointed, the required pressure of exhaust gases, flows and profiles of intake-boxes of every turbine were calculated.
W pracy przedstawione zostały zasadnicze wielkości charakteryzujące pracę turbosprężarek oraz zależności niezbędne do obliczenia całkowitej sprawności zespołu sprężarkowego przy uwzględnieniu równowagi mocy z odpowiednimi urządzeniami zespołu turbinowego, wykorzystując do tego celu równania bilansowe turbosprężarki. Następnie, dla założonych warunków pracy silnika, na drodze analizy teoretycznej, dokonano optymalnego pod względem sprawności całkowitej podziału mocy w zespołach sprężarkowych oraz turbinowych urządzenia doładowującego. Określone zostały wymagane spadki ciśnienia po stronie turbin konieczne do zapewnienia mocy potrzebnej po stronie sprężarek przy uwzględnieniu sprawności każdego urządzenia. W artykule zwrócono uwagę na problemy związane z wyborem odpowiedniej konstrukcji układu doładowania zakresowego i zapewnieniem korzystnych warunków jego współpracy z silnikiem. To jest szczególnie ważne w fazie przełączania trybów pracy pomiędzy turbosprężarkami i to ma zasadnicze znaczenie dla zachowania ciągłości charakterystyki silnika. W szczególności całkowita sprawność układu doładowującego wyznaczona została, wymagane ciśnienie spalin, wydatki oraz przekroje skrzyń wlotowych każdej turbiny były obliczone.
Źródło:: Journal of KONES; 2009, 16, 4; 59-66
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Influence of the incorrect settings of axial compressor inlet variable stator vanes on gas turbine engine work parameters
Autorzy:: Wirkowski, P.
Powiązania:: https://bibliotekanauki.pl/articles/246843.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine
axial compressor
variable stator vanes
Opis:: The paper deals with the problem of influence of changes variable stator vanes axial compressor settings of gas turbine engine on work parameters of compressor and engine. Incorrect operation of change setting system of variable vanes could make unstable work of compressor and engine. This paper presents theoretical analysis of situation described above and results of own research done on real engine. When in the compressor construction there is assembled system of setting change of variable stator vanes its task is to make optimal cooperation engine units during the permanent improvement of compressor characteristic. Perturbations in the operation of this system could cause changes in work of compressor and engine similarly as in the case of changes caused by changes of rotational speed or polluted interblades ducts of compressor. The purpose of investigations, which was carried out on real engine was determination influence of incorrect operation of axial compressor inlet guide variable stator vanes control system of gas turbine engine on compressor and engine work parameters. The object of research is type DR 77 marine gas turbine engine, which is a part of power transmission system of war ship. In compressor construction configuration of this engine there are used inlet guide stator vanes which make possibilities to change the setting angle incidance (change of compressor flow duct geometry) in depend on engine load. On the base of results of experiment there were determined the mathematical equations modelling the changes of particular engine work parameters in the function of variable inlet guide stator vanes setting angle.
Źródło:: Journal of KONES; 2012, 19, 3; 483-489
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Work parameters of the gas turbine engine during the change of flow passage geometry on the inlet of axial compressor
Autorzy:: Wirkowski, P.
Powiązania:: https://bibliotekanauki.pl/articles/245768.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine
axial compressor
variable stator vanes
modelling
Opis:: The paper deals with the problem of influence of changes variable stator vanes axial compressor settings of gas turbine engine on work parameters of compressor and engine. Incorrect operation of change setting system of variable vanes could make unstable work of compressor and engine. This paper presents theoretical analysis of situation described above and results of own research done on real engine. When in the compressor construction is assembled system of setting change of variable stator vanes its task is to make optimal cooperation engine units during the permanent improvement of compressor characteristic. Perturbations in the operation of this system could cause changes in work of compressor and engine similarly as in the case of changes caused by changes of rotational speed or polluted interblades ducts of compressor. The purpose of investigations, which was carried out on real engine was determination influence of incorrect operation of axial compressor inlet guide variable stator vanes control system of gas turbine engine on compressor and engine work parameters. The object of research is type DR 77 marine gas turbine engine, which is aport of power transmission system of war ship. In compressor construction configuration of this engine there are used inlet guide stator vanes which make possibilities to change the setting angle incidence (change of compressor flow duet geometry) in depend on engine load. On the base of results of experiment there were determined the mathematical eguations modelling the changes of particular engine work parameters in the function of variable inlet guide stator vanes setting angle.
Źródło:: Journal of KONES; 2009, 16, 3; 505-510
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

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: 7.

Tytuł:: The study on algorithm for identification the fatigue crack length of compressor blade based on amplitude-frequency resonant characteristics
Autorzy:: Lichoń, D.
Bednarz, A.
Powiązania:: https://bibliotekanauki.pl/articles/243684.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: fatigue failure
crack length
compressor blade
aircraft engine
failure identification algorithm
Opis:: The article is focused on building the algorithm for identification the fatigue crack length in the first stage of compressor blade of the helicopter PZL-10W turbo-shaft engine. The fatigue wear of compressor blade is a process in which the fatigue crack begins at the structural notch of the working part. For compressor blade, the crack starts at the leading edge and progress along the blade chord. Due to working conditions, the compressor blades are referred to as critical components. The helicopter rotor downwash can easily lift particles form the ground that may cause damages in the compressor section. Aircraft engines are designed so that the rotational speed of impeller remains below the resonant frequency. However, the pulsation of working medium or mechanical vibrations may cause temporary increase of vibration frequency. The appearance of structural notch combined with temporary increase of vibrations may initiate the fatigue failure. The works undertaken at the Department of Aircraft and Aircraft Engines, Rzeszow University of Technology provided a wide spectrum of research data of amplitude-frequency (A-F) characteristics of 1st stage of compressor blade. For different crack lengths, the fatigue tests of resonant frequency and asymmetry of A-F characteristics were acquired. The crack lengths were measured by fluorescent or infrared mapping method. The aim of the article is to develop the numerical method for identification of crack length of compressor blade basing on A-F characteristics. The studies on A-F characteristics in order to find correlations between crack length, resonant frequency and characteristics asymmetry were performed. The next step was to build the algorithm for identification the crack length when only A-F characteristic is known. The article contains the description of researches background, A-F characteristics unique features, algorithm detailed methods of work and sample use of algorithm in identification the crack length.
Źródło:: Journal of KONES; 2017, 24, 4; 157-164
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Influence of selected parameters on micro gas turbine compressor design
Autorzy:: Czarnecki, M.
Olsen, J.
Powiązania:: https://bibliotekanauki.pl/articles/243625.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: jet engine
gas turbine
design
trend prediction
centrifugal compressor
Opis:: The design a micro gas turbine engine is a process that requires analysis of a number of parameters. The initial stage requires consideration of more than 40 parameters [3]. The whole analysis can be made with analytical tools. However, these kinds of tools are limited to preliminary designs. After 1D-calculations and the establishment of the first CAD model, it is recommended to identify the sensitivity of the design. With a modern numerical environment such as ANSYS CFX, it is possible to predict a trend that gives the designer a 3D feedback about the initial design behaviour. For presented centrifugal compressor case, the selected parameters are vaneless diffuser space, design angle and number of stator blades. For qualitative evaluation – important results that influence design are mass flow rate, total pressure and isentropic efficiency. These results are important to turbojet engine performance and efficiency. All chosen parameters respond to given criteria. Validation and verification is still required due numerical errors that are included in CFD modelling. The advantage of 3D prediction is the possibility to eliminate gross errors before parts are sent into production.
Źródło:: Journal of KONES; 2017, 24, 3; 45-52
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Modern methods of identification design conditions for single stage micro scale centrifugal compressor
Autorzy:: Czarnecki, M.
Olsen, J.
Powiązania:: https://bibliotekanauki.pl/articles/243293.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: jet engine
gas turbine
design
off design
trend prediction
centrifugal compressor
Opis:: Micro scale gas turbine engines are low cost engines. They share their compressor impeller with automotive turbochargers. An identified design condition for the selected impeller is a critical stage of the design process. This process is had difficulties due the large number of manufacturers that provide OEM parts. It is common practice that one OEM part number provides the same impeller at different design revision. In general, parts are interchangeable but in detail, they differ slightly in terms of dimensions and performance. To avoid under predict or over predict inputs data, it is important to check the design parameters with as many methods as possible. In practice, the designer could rely on analytical methods, which are straightforward limited to the applied design. When shared its (compressor operation) it is recommended additional information be provided by computational fluid dynamics that produces a three-dimensional look into the predesign. That allows avoidance of future design failure and reduces both design time and prototype manufacturing costs.
Źródło:: Journal of KONES; 2017, 24, 2; 73-84
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Advantages of compressor downstream air partial bleed and supplying it downstream of the turbine in a turbojet engine
Autorzy:: Ćwik, D.
Kowalski, M.
Stężycki, P.
Powiązania:: https://bibliotekanauki.pl/articles/247092.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aviation engine operating parameters
jet engine designs
aviation engine air bleed
Opis:: The research article discusses the advantages of using compressor downstream air partial bleed and supplying it downstream of the turbine, which was applied in a prototype of a “bypass” turbojet engine. The objective of such a turbo engine structural solution was discussed along with its elements and principle of operation. Further part of the article determines the impact of such partial air bleed on the value of achieved basic operating parameters of the engine, i.e., unit thrust and unit power consumption. The presented attempt to compare these parameters with the parameters achieved for a turbojet, single flow engine is very important; in the first case without air bleed, and in the second, with air bleed to the environment. Further sections of the article compared these parameters relative to a turbojet, turbofan engine with a jet mixer. Such comparisons enabled to determine the actual benefits of using compressor downstream air partial bleed and supplying it downstream of the turbine, which may constitute an intermediate solution between single flow turbine engines and turbo fan engines. Wide possibilities for the application of such structural solutions were shown, which was summarised in the conclusions.
Źródło:: Journal of KONES; 2018, 25, 4; 501-508
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Impact of the vibration amplitude on the fatigue life of compressor blades with mechanical defects
Autorzy:: Witek, L.
Bednarz, A.
Powiązania:: https://bibliotekanauki.pl/articles/245666.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: turbine engine
compressor blade
v-notch
resonant vibrations
fatigue life
Opis:: In this paper, the results of an experimental fatigue analysis of the compressor blades with the mechanical defects were presented. Before the fatigue test, the blades were damaged in order to simulate the foreign object damage. In this operation, the v-notch was created by hitting the hard object into leading edge of the blade. The similar kind of damage occurs when the small particles as stones or sandy grains are sucked to the engine inlet and next have a collision with the rotated blade. As a result of the impact, both the plastic strains and also the initial stresses occur in the vicinity of the notch. These stresses have a large influence on the number of load cycles to crack initiation. During the experiment, the blades were entered into transverse vibration with the use of Unholtz-Dickie TA-250 vibration system. The crack propagation process was conducted in resonance conditions. During the fatigue test the blades were periodically bent. In investigations, the different vibration amplitudes of the blade were considered. During the fatigue test, the crack length was monitored with the use of non-destructive fluorescent penetrant method. The amplitude of the blade tip displacement was controlled using the Polytec PSV H-400S laser scanning vibrometer. The main aim of this work is analysis of influence of the vibration amplitude on the fatigue life of the compressor blade of the turbine engine. The results of presented investigations are important from the research and also from the practical point of view and have an influence on safety and reliability of the turbine engine.
Źródło:: Journal of KONES; 2016, 23, 3; 571-576
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Analysis of vibroacoustic properties of the 250-C20R/2 RRC (Allison) engine in the support surface of the compressor
Autorzy:: Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/247973.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: vibroacoustic properties
engine vibration analysis
Opis:: The paper presents an analysis of the levels of vibration on the compressor in the support surface of the American RRC Allison 250-C20R engine built into the SW-4 Puszczyk helicopter. Then, it presents the association of occurring vibrations with their source of origin, and also the comparison of their values with the limit values specified in the operating manual of the helicopter. The methodology of the conducted research and analyses are explained. The essential elements preceding the research, such as determining time courses, on the basis of which the most important parts to conduct the detailed analyses of changes of the basic parameters and compliance with technical conditions, are defined. Moreover, the theoretical issues in terms of determination and description of the characteristic parameters of mechanical vibrations are briefly presented. The typical terms used in the procedures of vibration, description and measurements are explained. The importance of the interpretation of measurements is quite significantly emphasised and the components of the main engine, which were subject to measurement, are indicated. The difficulties in the identification of the vibration due to the high probability of overlapping of vibrations coming from several elements are emphasised. Next, the methodology of measurement is described, in which, among others, mounting points of vibration sensors are presented. The final part of the paper is mainly a graphical presentation of the results, on the basis of which the conclusions are developed. The conclusions show a lack of decisive symptoms indicating the danger at the level of vibrations, and present the future directions of work, which will allow for a more detailed analysis.
Źródło:: Journal of KONES; 2014, 21, 4; 281-288
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

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

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Skocz do pozycji: 14.

Tytuł:: Research on influence of condition elements the supercharger system on the parameters of the marine diesel engine
Autorzy:: Witkowski, K.
Powiązania:: https://bibliotekanauki.pl/articles/244429.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: ship diesel engine
turbocharger system
active experiment
air filter
compressor
air cooler
Opis:: This paper presents the issues related to the impact of the technical condition elements of the turbocharger system on the parameters of marine diesel engine. Turbocharger system, in addition to the injection system has a significant impact on the quality of the working process, the economics and reliability of the engine. Contamination of elements of the turbocharger system are the most common faults (24.7% of all damage to marine engines). Contamination the following relates to elements: air filters, compressor, air cooler, scavenging system elements and turbine. The detailed data follows that the contamination are usually in: flow channels supercharger – 56%, turbine flow channels – 22%, air cooler – 11%, air filter – 6%, scavenging system elements – 4%, other elements – 1%. The technical condition influence of air filter, compressor and air cooler was analyzed. The analysis was supported by the results of their own research, carried out in the laboratory on the marine diesel engine, four– stroke 3AL25/30 SULZER, supercharged turbocharger VTR160N Brown Boveri. The research was performed in the form of an active experiment to simulate contamination of particular elements of the turbocharging system. Technical condition change of the air filter, the air compressor and the air cooler have been investigated.
Źródło:: Journal of KONES; 2013, 20, 1; 375-380
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

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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