Temat: axial compressor - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Development of flow and efficiency characteristics of an axial compressor with an analytical method including cooling air extraction and variable inlet guide vane angle
Autorzy:: Trawiński, Paweł
Powiązania:: https://bibliotekanauki.pl/articles/1955039.pdf
Data publikacji:: 2021
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: axial compressor
compressor characteristics
compressor map
IGV
bleed air
Opis:: The development of a reliable mathematical model of an axial compressor requires applying flow and efficiency characteristics. This approach provides performance parameters of a machine depending on varying conditions. In this paper, a method for developing characteristics of an axial compressor is presented, based on general compressor maps available in the literature or measurement data from industrial facilities. The novelty that constitutes the core of this article is introducing an improved method describing the performance lines of an axial compressor with the modified ellipse equation. The proposed model is extended with bleed air extraction for the purposes of cooling the blades in the expander part of the gas turbine. The variable inlet guide vanes angle is also considered using the vane angle correction factor. All developed dependencies are fully analytical. The presented approach does not require knowledge of machine geometry. The set of input parameters is based on reference data. The presented approach makes it possible to determine the allowed operating area and study the machine’s performance in variable conditions. The introduced mathematical correlations provide a fully analytical study of optimum operating points concerning the chosen criterion. The final section presents a mathematical model of an axial compressor built using the developed method. A detailed study of the exemplary flow and efficiency characteristics of an axial compressor operating with a gas turbine is also provided.
Źródło:: Archives of Thermodynamics; 2021, 42, 4; 17-46
1231-0956
2083-6023
Pojawia się w:: Archives of Thermodynamics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Numerical study of stall inception in a transonic axial compressor rotor based on the throttle model
Autorzy:: Zhu, X.
Liu, B.
Hu, J.
Shen, X.
Powiązania:: https://bibliotekanauki.pl/articles/280516.pdf
Data publikacji:: 2015
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: stall
axial compressor
throttle
tip clearance flow
Opis:: The goal of the current paper is to investigate inner flow behavior on stall inception in a transonic compressor rotor. The stall inception process is numerically carried out by unsteady 3-D simulations based on the throttle model. The current study shows that stall starts from the tip of the blade, and stall cell extends to the axial, circumferential and radial directions. Through the comparison of flow transition characteristics at different flow rate conditions, the interface between the incoming flow and tip clearance flow shifts forward to the upstream as the mass flow decreases. Eventually, the shock detaches from the blade leading edge, and tip clearance flow spills into the adjacent blade passage, thus stall happens in the affected blade passages.
Źródło:: Journal of Theoretical and Applied Mechanics; 2015, 53, 2; 307-316
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Modelling research of the characteristics of gasturbine axial compressor with changeable flow passage geometry
Autorzy:: Wirkowski, P.
Powiązania:: https://bibliotekanauki.pl/articles/246179.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine
axial compressor
variable stator vanes
Opis:: In real exploitational conditions marine gasturbine engine works at different rotation speeds determined by the required parameters of ship's movement. Conversion from one rotation speed to another is related to realization of unsteady energetic processes, determined by the gasodynamic mutual influence of compressor configurations. The values of working medium flow thermodynamic parameters undergo significant changes in time. To work out the qualitative and quantitative estimation of these changes it is necessary to define the dynamic equations, describing working medium flow through the gas passage of engine. In the next step it is necessary to resolve the defined equations for disturbances of steady cooperation of compressor configurations. This paper concerns the application of mathematical modelling methods to analyzing gas-dynamic processes in marine gas turbines. The influence of geometry changes in axial compressor flow passage on kinematical air flow characteristics is presented. The elaborated mathematical model will make it possible to realize - in the future -simulative investigations of gas-dynamic processes taking place in a compressor fitted with controllable guide vanes. Individual parametric features of every engine in service are identified by using expensive experimental tests, which are conditioned by many constructional and operational limitations. The dynamic development of computer technology, enables using it for numerical simulation of changeable technical state processes.
Źródło:: Journal of KONES; 2011, 18, 3; 507-514
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:: Modelling the characteristics of axial compressor with variable stator vanes
Autorzy:: Wirkowski, P.
Powiązania:: https://bibliotekanauki.pl/articles/247506.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine
axial compressor
variable stator vanes
modelling
Opis:: One of the most important problems of exploitational use of marine gas turbine engine is knowledge about direction of changes realised unsteady processes. Individual dynamical features of each exploitated engine are determined on the way of costly experimental searches. These searches are qualifled by numerous constructional and exploitational confinements. In real exploitational conditions marine gasturbine engine works at different rotation speeds determined by the required parameters of ship's movement. Conversion from one rotation speed to another is related to realization of unsteady energetic processes, determined by the gasodynamic mutual influence of compressor configurations. The values of working medium flow thermodynamic parameters undergo significant changes in time. To work out the qualitative and quantitative estimation of these changes it is necessary to define the dynamic equations, describing working medium flow through the gas passage of engine. In the next step it is necessary to resohe the defined equations for disturbances of steady cooperation of compressor configurations. This paper concerns the application of mathematical modelling methods to analyzing gas-dynamic processes in marine gas turbines. The influence of geometry changes in axial compressor flow passage on kinematical air flow characteristics is presented. The elaborated mathematical model will make it possible to realize - in the future -simulative investigations of gas-dynamic processes taking place in a compressor fitted with controllable guide vanes.
Źródło:: Journal of KONES; 2010, 17, 2; 497-504
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Factors influencing axial compressor stalls
Autorzy:: Laskowski, P.
Powiązania:: https://bibliotekanauki.pl/articles/196204.pdf
Data publikacji:: 2017
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: stall
axial compressor
performance
stoisko
sprężarka osiowa
wydajność
Opis:: The article describes the problem regarding stalls in axial compressors, which are widely used in the engines of large and very large transportation aircrafts. The stall phenomenon, unless cleared, poses a major danger to the integrity of a compressor module, which in turn may result in uncontained engine failure and loss of thrust, thereby seriously affecting flight safety. The costs of maintenance to be performed may also be very high, due to irreversible deterioration in some components. A practical assessment of the stall problem and its countermeasures are discussed below.
Źródło:: Zeszyty Naukowe. Transport / Politechnika Śląska; 2017, 95; 89-96
0209-3324
2450-1549
Pojawia się w:: Zeszyty Naukowe. Transport / Politechnika Śląska
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

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: 8.

Tytuł:: Influence of Axial Compressor Model Simplification and Mesh Density on Surge Margin Evaluation
Autorzy:: Muchowski, Rafał
Gubernat, Sławomir Maciej
Powiązania:: https://bibliotekanauki.pl/articles/2023311.pdf
Data publikacji:: 2021
Wydawca:: Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:: CFD
axial compressor
surge margin
jet engine
compressor map
grid dependence
Opis:: The menace of surge occurrence in the compressors is taken very seriously and its avoidance became a fundamental for the design of any modern jet engines. Nowadays, a problem with appropriate evaluation of the compressor surge margin while considering different simplifications of three-dimensional CFD model is still present. For that purpose, this article presents a comparison between the measurement data and several variants of 3D CFD models characterized by a specific mesh density. To calculate all the results on which the comparisons and conclusions are based, an 8-stage axial compressor is taken into account. Flow conditions of the machine are computed for three part load speeds: The low, the mid and the high one respecting the variable guide vanes schedule fitted to the specific load. For each of speed variants a four mesh configurations were generated: coarse, medium, fine and extra-fine. All speed configurations were treated with two different turbulence models – Wilcox k-ω and Menter’s SST k-ω, giving ultimately 15 CFD models, calculated with the TRACE solver using an initialization based on a circumferentially averaged flow solution delivered by the Streamline Curvature Method. During the study an additional assessment of reference grid independence was performed and the mesh convergence has been achieved. A comparison between turbulence models and the measurement proves that SST turbulence model is not well distributed through the speeds in compare to the measurement data and the Wilcox turbulence model. Inconsistency of sensitivity in the mesh coarsening for different rotational speeds was found. Increasing the mesh roughness level has to be executed for each speed separately. Overall compressor map shows that shift of the Pressure Ratio and the Mass Flow decreases with lower rotational speed. Neglecting the system add-ons like labyrinth sealing volumes, bleed-ports and other leakages has a visible influence on deviations from the measurements. Because of intended future use in design and optimization the “Medium” grid with Wilcox k-ω turbulence model was chosen, being a good representation of the Rig characteristics with reduction of the computing time.
Źródło:: Advances in Science and Technology. Research Journal; 2021, 15, 3; 243-253
2299-8624
Pojawia się w:: Advances in Science and Technology. Research Journal
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Multiple spike stall cells in low speed axial compressor rotor blade row
Autorzy:: Taghavi-Zenouz, R
Abbasi, S.
Powiązania:: https://bibliotekanauki.pl/articles/279770.pdf
Data publikacji:: 2015
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: axial compressor
spike stall inception
tip leakage flow
frequency spectrum
Opis:: Inception and development of multiple stall cells of short length scales are numerically investigated in an axial compressor rotor blade row. The method of investigation is based on time accurate three-dimensional full annulus simulations. Time dependent flow structure results revealed that there are two criteria responsible for inception of a special kind of stall, introduced as spike stall in the literature. These criteria are defined as leading edge spillage and trailing edge backflow, which occur at specific mass flow rates near to stall conditions. The numerical results revealed that once the spike stall cells appear, they cover roughly two blade passages in the circumferential direction and cover about 25% of the blade height. By further revolution of the blade row, the number of cells tends to increase. For the present case study, the number of stall cells increased to three after 8.5 rotor revolutions from the moment of the initial spike stall occurrence. Even at this moment, both of the above mentioned criteria for the spike stall inception have been observed within the blades passages. These events caused the inlet relative flow angle to the blade rows, and therefore the flow incidence angle and consequent blockage to the main flow, to increase. The tip leakage flow frequency spectrum has been studied through surveying instantaneous static pressure signals imposed on pressure side of the blades and also on the casing walls. These latter results showed that any further revolving of the rotor blade row, exceeding 8.5 revolutions, causes the spike stall to disturb the flow structure significantly.
Źródło:: Journal of Theoretical and Applied Mechanics; 2015, 53, 1; 47-57
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Investigation of inlet distortion effects on axial compressor performance based on streamline curvature method
Autorzy:: Abbasi, S.
Pirnia, A.
Taghavi-Zenouz, R.
Powiązania:: https://bibliotekanauki.pl/articles/281973.pdf
Data publikacji:: 2018
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: axial compressor
performance map
inlet distortion
surge margin
streamline curvature
Opis:: In this paper, the effects of inlet flow distortion on performance maps and details of the flow field are investigated using the Streamline Curvature Method. The results are presented for both design and off-design conditions and compared with experimental data, which shows good agreement. The effects of inlet flow distortion are investigated by inlet total pressure variation in three different cases in the way that the average total pressure remains constant and equal to the design value. The results show that a relative increase in the total pressure at tip causes an increase in the pressure ratio and efficiency as well as a better performance in the choking region. Alternatively, a relative increase in the total pressure in hub causes opposite behavior and a better performance at the surging region.
Źródło:: Journal of Theoretical and Applied Mechanics; 2018, 56, 4; 1005-1015
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Investigation of Design Features of Compressor Casing Treatment
Badanie charakterystyk projektowych obróbki obudowy kompresora
Autorzy:: Nezym, V
Powiązania:: https://bibliotekanauki.pl/articles/950694.pdf
Data publikacji:: 2014
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: axial compressor
stall range
efficiency
casing treatment
grooves
kompresor
rowki obwodowe
wydajność
Opis:: Casing treatment in the form of circumferential grooves over a rotor blade tips is used for improvement of an axial compressor performance. Usually, these grooves extend compressor’s stall range (stable operational range) but decrease its efficiency. In the paper, there are presented main results of investigations on grooves that influence positively efficiency of compressor. There were investigated traditional (typical) and newly developed groove configurations. Certain grooves combine increase in efficiency with extension in stall range.
Obróbka obudowy kompresora, polegajacą na wykonaniu obwodowych rowków ponad szczytem łopaty wirnika, jest stosowana dla poprawy własciwosci roboczych kompresora. Zwykle rowki takie zwiekszaja zakres przeciagania kompresora (zakres stabilnego działania), ale pogarszaja sprawność. W artykule zaprezentowano główne wyniki badan nad rowkami, które wpływaja pozytywnie na sprawnosc kompresora. Badano zarówno tradycyjne (typowe) konfiguracje rowków, jak i konfiguracje ostatnio opracowane. Niektóre z nich zapewniają zarówno wzrost sprawności jak zakresu przeciągania.
Źródło:: Archive of Mechanical Engineering; 2014, LXI, 1; 153-161
0004-0738
Pojawia się w:: Archive of Mechanical Engineering
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Numerical loss analysis on slot-type casing treatment in a transonic compressor stage
Autorzy:: Zhu, M.-M.
Qiang, X.-Q.
Teng, J.-F.
Powiązania:: https://bibliotekanauki.pl/articles/280437.pdf
Data publikacji:: 2017
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: axial compressor
numerical simulation
slot-type casing treatment
loss mechanism
tip leakage flow
Opis:: To understand the loss mechanism of slot-type casing treatment, a numerical loss analysis has been carried out in a 1.5 axial transonic compressor stage with various slots. Spanwise and streamwise distribution curves of pitch-averaged entropy have been presented to survey the development of loss generation. Further, detailed entropy distributions at eight axial cuts, which have been taken through the blade row and slots, have been further analyzed to interpret the loss mechanism. The most dramatic loss growth occurred above 95% span, which directly resulted from slots injection flow upstream the leading edge. Loss generations with smooth casing have been primarily ascribed to low-momentum tip leakage flow/vortex and suction surface separation at the leading edge. CU0 slot, the arc-curved slots with 50% rotor tip exposure, has been capable of suppressing the suction surface separation loss. Meanwhile, accelerated tip leakage flow brought about additional loss near the casing and pressure surface. Upstream high entropy flow would be absorbed into the rear portion of slots repeatedly, which resulted in further loss.
Źródło:: Journal of Theoretical and Applied Mechanics; 2017, 55, 1; 293-306
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Wpływ zmian kąta ustawienia łopatek kierownicy wlotowej sprężarki osiowej na parametry pracy okrętowego turbinowego silnika spalinowego
Influence of axial compressor inlet stator vanes angle setting on marine gas turbine engine work parameters
Autorzy:: Wirkowski, P.
Powiązania:: https://bibliotekanauki.pl/articles/329068.pdf
Data publikacji:: 2007
Wydawca:: Polska Akademia Nauk. Polskie Towarzystwo Diagnostyki Technicznej PAN
Tematy:: silnik turbinowy
sprężarka osiowa
regulowane łopatki kierownicy
gas turbine engine
axial compressor
variable stator vanes
Opis:: W artykule zaprezentowano analizę teoretyczną zagadnienia wpływu zmian ustawienia regulowanych łopatek kierownicy stopnia osiowego sprężarki turbinowego silnika spalinowego na parametry pracy samej sprężarki jak i całego silnika. Przedstawiono również wyniki badań własnych na obiekcie rzeczywistym. Wprowadzane zakłócenia w prawidłowym funkcjonowaniu układu zmian nastawy regulowanych łopatek kierownic miały swoje odzwierciedlenie w wartościach mierzonych parametrów.
This paper presents theoretical analysis of problem influence of changes settings variable stator vanes axial compressor of gas turbine engine on work parameters of compressor and engine. Results of own researches on real engine are presented too. Incorrect operation of change setting system of variable vanes caused changes of measured parameters values.
Źródło:: Diagnostyka; 2007, 3(43); 41-47
1641-6414
2449-5220
Pojawia się w:: Diagnostyka
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Simulation of changes of gas turbine engine work parameters equipped with changeable geometry of axial compressor flow passage
Symulacja zmian parametrów pracy silnika turbinowego wyposażonego w sprężarkę osiową o zmiennej geometrii kanału przepływowego
Autorzy:: Wirkowski, P.
Powiązania:: https://bibliotekanauki.pl/articles/328358.pdf
Data publikacji:: 2008
Wydawca:: Polska Akademia Nauk. Polskie Towarzystwo Diagnostyki Technicznej PAN
Tematy:: silnik turbinowy
sprężarka osiowa
regulowana łopatka kierownicy
symulacja
gasturbine
axial compressor
variable stator vanes
simulation
Opis:: The paper deals with problem 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 presents results of own researches done on real engine. The next there are presented results of mathematical modelling of changes of gas turbine engine parameters during change of angle setting of axial compressor variable stator vanes but in the most wide angle range than in real researches.
Nieprawidłowe funkcjonowanie systemu zmiany ustawienia regulowanych łopatek sprężarki osiowej silnika turbinowego może powodować niestabilną pracę sprężarki przenoszoną na konstrukcję silnika. W artykule zaprezentowana została analiza teoretyczna powyższego zjawiska oraz przedstawiono wyniki badań przeprowadzonych na rzeczywistym obiekcie. Następnie na bazie przeprowadzonych badań określone zostały równania matematyczne opisujące zależności pomiędzy wartościami rozpatrywanych parametrów pracy silnika a kątem ustawienia regulowanych łopatek. Równania te posłużyły do zasymulowania zmian wartości parametrów dla zakresu zmian kąta regulowanych łopatek nieosiągalnego podczas badań na obiekcie rzeczywistym.
Źródło:: Diagnostyka; 2008, 1(45); 31-34
1641-6414
2449-5220
Pojawia się w:: Diagnostyka
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Gas turbine engine work parameters during incorrect setting of axial compressor variable stator vanes
Parametry pracy silnika turbinowego w warunkach nieprawidłowego ustawienia regulowanych łopatek kierownicy sprężarki osiowej
Autorzy:: Wirkowski, P.
Powiązania:: https://bibliotekanauki.pl/articles/257372.pdf
Data publikacji:: 2008
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Technologii Eksploatacji - Państwowy Instytut Badawczy
Tematy:: silnik turbinowy
sprężarka osiowa
regulowane łopatki kierownicy
gas turbine engine
axial compressor
variable stator vanes
Opis:: The paper deals with the problem concerning the influence of changes in the variable stator vanes axial compressor settings of a gas turbine engine on work parameters of compressor and engine. Incorrect operation of the change setting system of variable vanes could make the work of compressor and engine unstable. This paper presents a theoretical analysis of the situation described above and presents the results of research done on a real engine. Next, the results of mathematical modelling of the changes in gas turbine engine parameters during change of angle setting of axial compressor variable stator vanes are presented.
W artykule przedstawiono wpływ zmian ustawienia regulowanych łopatek kierownicy sprężarki osiowej silnika turbinowego na parametry pracy sprężarki oraz całego silnika. Nieprawidłowe funkcjonowanie systemu zmiany ustawienia regulowanych łopatek może powodować niestabilną pracę sprężarki przenoszoną na konstrukcję silnika. Sytuacja taka jest niepożądana ze względu na obciążenia mechaniczne, które w skrajnych przypadkach mogą doprowadzić do uszkodzenia silnika. W artykule zaprezentowana została analiza teoretyczna powyższego zjawiska oraz przedstawiono wyniki badań przeprowadzonych na rzeczywistym obiekcie. Następnie na bazie przeprowadzonych badań określone zostały równania matematyczne opisujące zależności pomiędzy wartościami rozpatrywanych parametrów pracy silnika a kątem ustawienia regulowanych łopatek. Równania te posłużyły do określenia zmian wartości parametrów dla zakresu zmian kąta regulowanych łopatek nieosiągalnego podczas badań na obiekcie rzeczywistym.
Źródło:: Problemy Eksploatacji; 2008, 2; 239-249
1232-9312
Pojawia się w:: Problemy Eksploatacji
Dostawca treści:: Biblioteka Nauki

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