Temat: GAs - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Utilization possibility of marine trent 30 gas turbine as prime mover on vessels
Autorzy:: Herdzik, J.
Cwilewicz, R.
Powiązania:: https://bibliotekanauki.pl/articles/241954.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: marine prime mover
gas turbine
propulsion
gas-electric plant
gas turbine utilization
Opis:: Gas turbines are used as marine prime movers but the market is dominated by the diesel engines (of course turbocharged but they are still diesels). The share of gas turbines is on a level of 4-5% in the worldwide shipping. It was presented the chosen parameters of Rolls-Royce gas turbine MT30 with nominal power 36 MW or 40 MW prepared for marine utilization. It is a good example of development of marine gas turbines with the trial to eliminate the effect of ambient temperature especially on turbine load. It was discussed the significance presented data for possibility of utilization on vessels. It was indicated the advantages and disadvantages of gas turbine sharing. It was mentioned the installation problems: pressure drop in inlet and outlet ducts on the accessible turbine power and specific fuel consumption. It was discussed what important parameters ought to be known for safe turbine operation and maintenance. There is a little information lack. The gas turbine ought not to be treat as a black box. In the end, some final remarks are presented.
Źródło:: Journal of KONES; 2017, 24, 3; 95-100
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Remarks on utilization of Marine Trent 30 gas turbine as prime mover on vessels
Autorzy:: Herdzik, J.
Cwilewicz, R.
Powiązania:: https://bibliotekanauki.pl/articles/246672.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: marine prime mover
gas turbine
propulsion
gas-electric plant
gas turbine utilization
Opis:: Utilization of gas turbines on vessels is a reality. It was presented the examples of utilization on ships of United States Navy and the Rolls-Royce suggestion for sharing on merchant shipping. It was mentioned the advantages of gas turbine MT30 with nominal power 36 MW or 40 MW prepared for marine utilization. It was stated the characteristics of specific fuel consumption, the shaft power rating, the MT30 operating envelope with propeller characteristics as a power receiver. It was given propositions of vessel types for MT30 utilization. It was discussed the remarks on maintenance requirements and needed systems for upkeep the turbine in good technical state for the possibility of full nominal power independent on ambient temperature. It was discussed the requirements of emissions from exhaust gasses to the atmosphere in comparison gas turbines to diesel engines as a one of important problems for utilization engines as prime movers on vessels in merchant shipping. In the end, some final remarks with Rolls-Royce statements are presented.
Źródło:: Journal of KONES; 2017, 24, 2; 91-97
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: The impact of unevenness and instability of flue gas temperature on the technical condition of gas turbine blades
Autorzy:: Błachnio, J.
Kułaszka, A.
Perczyński, J.
Powiązania:: https://bibliotekanauki.pl/articles/243064.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: flue gas temperature
gas turbine
blade
diagnostics
technical condition
Opis:: Gas turbines are used in the power sector, aviation, pump houses, and other technical systems. Such a broad range of application is associated with favourable indicators: high power, rather low weight per unit of power, significant efficiency, as well as high durability. All of these indicators greatly depend on the combustion chamber flue gas temperature. It is important for the flue gas temperature to be uniform around the turbine perimeter and stable over time. This condition is extremely important also in the case of frequent temperature variations associated, e.g. with a variable operating range of a manoeuvre aircraft turbojet engine. The paper analyses the causes for the unevenness and instability of combustion chamber flue gas temperature. The impact of the fuel quality, the technical condition of the fuel supply system, as well as the operating conditions of the combustion chamber-turbine assembly was shown. The issues regarding the presence of various types of damage to turbine elements, their blades in particular, were defined. The main cause behind the damage is the unevenness and instability of flue gas temperature, resulting in the presence of overheating, creeping, thermal fatigue, high-temperature corrosion of blade material. The forms of that damage, especially the first turbine stages, were presented. Blade material microstructure test results showed increased layer thickness, grain-size, and especially, adverse modification of the strengthening γ' phase in the temperature function. It was concluded periodic diagnostics of turbine blades with the optical method enables the non-invasive evaluation of their technical condition and drawing conclusions in terms of their durability.
Źródło:: Journal of KONES; 2018, 25, 2; 45-51
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Mass model of microgasturbine single spool turbojet engine
Autorzy:: Czarnecki, M.
Powiązania:: https://bibliotekanauki.pl/articles/247344.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine
micro gas turbine
mass model
Schreckling
turbojet
Opis:: Presented paper consists detailed mass model of micro gas turbine single spool turbojet in well-known Scheckling design layout (1R/1A). One of major criteria in aviation is weight that is granted by airworthiness requirements. At present, exempt from certification process are RC airplanes or UAV with total take-off weight less than 22.5 kg. From the 70's mass model was added as a part of aero engines design process. Engine weight affects airplane or UAV weight greatly, because it is a source of variety structure loads. Weight reduction efficiency factor, verifying in terms of design quality a micro gas turbine, and the flying object as a system. Developed computational model allows to estimate weight of the components (gas generator shaft, compressor rotor, compressor diffuser, combustor, turbine nozzle, turbine rotor, jet pipe, casings and housings) and whole engine as well. Model inputs are related to technological axisymmetric dimensions obtained from thermo gas dynamic and construction equations, making it easy to use. Obtained results was presented for several micro gas turbines (mSO1-designed by author, FD3-64, TK-50, JF-50, MW-54, KJ-66, AMT Olympus). Advantage of this model allows to avoid time consuming CAD modelling process at design study level. Presented algorithm can be used also in the design of UAV as well as issues related to the preliminary multidisciplinary design and optimization PMDO cases.
Źródło:: Journal of KONES; 2013, 20, 1; 49-54
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Analysis of energy storage system with distributed hydrogen production and gas turbine
Autorzy:: Kotowicz, J.
Bartela, Ł.
Dubiel-Jurgaś, K.
Powiązania:: https://bibliotekanauki.pl/articles/240427.pdf
Data publikacji:: 2017
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: Power-to-Gas-to-Power
hydrogen
gas turbine
electrolysis
wodór
turbina gazowa
elektroliza
Opis:: Paper presents the concept of energy storage system based on power-to-gas-to-power (P2G2P) technology. The system consists of a gas turbine co-ﬁring hydrogen, which is supplied from a distributed electrolysis installations, powered by the wind farms located a short distance from the potential construction site of the gas turbine. In the paper the location of this type of investment was selected. As part of the analyses, the area of wind farms covered by the storage system and the share of the electricity production which is subjected storage has been changed. The dependence of the changed quantities on the potential of the hydrogen production and the operating time of the gas turbine was analyzed. Additionally, preliminary economic analyses of the proposed energy storage system were carried out.
Źródło:: Archives of Thermodynamics; 2017, 38, 4; 65-87
1231-0956
2083-6023
Pojawia się w:: Archives of Thermodynamics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Dependence between nominal power deterioration and thermal efficiency of gas turbines due to fouling
Autorzy:: Herdzik, Jerzy
Powiązania:: https://bibliotekanauki.pl/articles/24202511.pdf
Data publikacji:: 2022
Wydawca:: Akademia Morska w Szczecinie. Wydawnictwo AMSz
Tematy:: gas turbine
gas turbine deterioration
reasons of fouling
thermal efficiency
performance
fuel consumption
Opis:: Deterioration in the performance of gas turbines is a well-known phenomenon occurring during their operation. The most important form is a decrease in the internal efficiency of the compressor and turbine due to fouling, which is the most significant deterioration problem for an operator. This article presents the effect of gas turbine fouling as a drop in airflow, pressure ratio, and compressor efficiency resulting in a reduction in power output and thermal efficiency. This resulted in a decrease in the nominal power of a gas turbine and an increase in the fuel consumption (heat rate). The fouling effects were described using the example of the MT30 marine gas turbine with a nominal power of 36 MW. The estimated profit loss during the operation of the gas turbine was within the range of 1–10% of the total fuel consumption cost. A 2% deterioration in the output of a gas turbine accounted for US$ 10,000–20,000 per year and 1 MW of gas turbine nominal power (according to marine fuel prices in 2019–2020) – this means at least US$ 300,000 annually for an MT30. Due to the low accuracy of fuel consumption measurements, another possibility was provided. The correlation between the gas turbine power deterioration and thermal efficiency was presented, which made it possible to estimate the increase in the specific and total fuel consumption when the nominal power deterioration is known. Two linear approximations were proposed to calculate increases in the annual operating costs for an MT30 due to fouling.
Źródło:: Zeszyty Naukowe Akademii Morskiej w Szczecinie; 2022, 69 (141); 45--53
1733-8670
2392-0378
Pojawia się w:: Zeszyty Naukowe Akademii Morskiej w Szczecinie
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Energetyczna ocena efektywności pracy elektrociepłowni gazowo-parowej z organicznym układem binarnym
Autorzy:: Nowak, W.
Powiązania:: https://bibliotekanauki.pl/articles/172827.pdf
Data publikacji:: 2011
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: spaliny odlotowe
turbina gazowa
elektrociepłownia parowa
exhaust gas
gas turbine
thermal-electric power station
Opis:: Przedstawiono analizę porównawczą efektywności wykorzystania spalin odlotowych turbiny gazowej do zasilania kilku różnych układów parowych z wykorzystaniem substancji organicznych jako czynników obiegowych. Przeanalizowano jednoobiegową elektrociepłownię parową, pracującą z wodą sieciową jako medium roboczym oraz jej sprzężenie cieplne za pomocą wymiennika typu skraplacz-parowacz z organicznym układem binarnym, w którym obieg górny zasilany jest wodą z elektrociepłowni, zaś w obiegach układu binarnego krążą odpowiednio dobrane czynniki organiczne. Opisano pracę oraz omówiono algorytm i wyniki obliczeń dla czynników organicznych, których zastosowanie pozwala na uzyskanie najlepszych efektów poprawy pracy elektrociepłowni gazowo-parowej współpracującej z układem binarnym, w odniesieniu do elektrociepłowni gazowo-parowej z jednoobiegowym układem parowym.
Źródło:: Archiwum Energetyki; 2011, 41, 1; 59-64
0066-684X
Pojawia się w:: Archiwum Energetyki
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Computer aided visual inspection of the technical condition of gas turbin blades during their operation period
Autorzy:: Błachnio, J.
Kułaszka, A.
Powiązania:: https://bibliotekanauki.pl/articles/242196.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine
blade
technical condition
diagnosing
Opis:: Due to speciflc working conditions of gas turbine blades and difficult access to them their technical condition during their operation period is generally evaluated by a visual method with the aid of advanced optical devices. This paper presents the analysis of forms and kinds of gas turbine blade damages, which affect their reliability. The paper presents features of non-destructive inspection methods used for diagnosing the technical conditions of the said blades during their operation period. Special atiention was given to methods of computer aided diagnosing of the technical condition ofgas turbine blades, which increase the reliability of evaluation of the said condition and therefore reduce costs and enhance the operational safety. The process of destruction of a gas turbine blade starts with the destruction of a protective coating, in consequence of which the initial material of a blade is subject to a direct aggressive impact of the waste gas. This causes the material to directly overheat, which manifests itself in detrimental changes in its microstructure. There is need for a more common use of non-destructive methods for a current evaluation of the state of overheated aircraft engine turbine blades.
Źródło:: Journal of KONES; 2009, 16, 3; 23-30
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Examination of changes in the microstructure of gas turbine blades with visual and thermographic methods
Autorzy:: Błachnio, J.
Kułaszka, A.
Kornas, Ł.
Chalimoniuk, M.
Powiązania:: https://bibliotekanauki.pl/articles/247030.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine
vane
diagnostics
thermographic method
Opis:: The processes associated with operation of turbinę avionic engines entail the occurrence of various defects affecting turbine components, in particular turbine vanes. The main reasons for defects and deterioration of gas turbine vanes include thermal fatigue and overheating of the vane material. This paper outlines the non-destructive test methods that are currently in use and that are based on an analysis of surface images obtained from the examined parts within the visible bandwidth with the use of a ring-wedge detector. Particular attention is paid to opportunities that enable unbiased diagnostics of changes in the microscopic structure of vanes with the use of the non-destructive thermographic method. Initial examinations ofthe gas turbine vanes, both new ones and those already in operation, have demonstrated the existence of interrelations and dependency between the thermal strain during the turbine operation, changes of signals associated with the thermal response from the material and the condition of the vane microstructures. The results of these examinations have been successfully verified with the use of the metallographic method. The demonstrated interrelations and dependency shall serve as a basis to develop fundamentals for a non-destructive thermographic test method intended to assess the overheating condition of the material for gas turbine vanes.
Źródło:: Journal of KONES; 2010, 17, 2; 27-34
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Capabilities to assess health/maintenance status of gas turbine blades with non-destructive methods
Autorzy:: Błachnio, J.
Powiązania:: https://bibliotekanauki.pl/articles/259685.pdf
Data publikacji:: 2014
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: gas turbine
blade
diagnosing
technical condition
Opis:: The paper has been intended to discuss non-destructive testing methods and to present capabilities of applying them to diagnose objectively changes in the microstructure of a turbine blade with computer software engaged to assist with the analyses. The following techniques are discussed: a visual method, based on the processing of images of the material surface in visible light, active thermography, based on the detection of infrared radiation, and the X-ray computed tomography. All these are new non-destructive methods of assessing technical condition of structural components of machines. They have been intensively developed at research centers worldwide, and in Poland. The computer-aided visual method of analyzing images enables diagnosis of the condition of turbine blades, without the necessity of dismantling of the turbine. On the other hand, the active thermography and the X-ray computed tomography, although more sensitive and more reliable, can both be used with the blades dismounted from the turbine. If applied in a complex way, the non-destructive methods presented in this paper, are expected to increase significantly probability of detecting changes in the blade’s condition, which in turn would be advantageous to reliability and safety of gas turbine service.
Źródło:: Polish Maritime Research; 2014, 4; 41-47
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: What-if analysis of the labyrinth seal of the gas turbine rotor tip
Autorzy:: Wróblewski, W.
Bochon, K.
Borzęcki, T.
Powiązania:: https://bibliotekanauki.pl/articles/175228.pdf
Data publikacji:: 2017
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: gas turbine
labyrinth seal
honeycomb
CFD
Opis:: This paper presents a preliminary, numerical what-if analysis of selected geometrical parameters of the tip seal of the last stage of an aircraft engine turbine and the impact of the parameters on the leakage mass ow. The analysis is a part of the task of improving the rotor tip seal conguration in aircraft turbines. Calculations were carried out using the commercial computational uid dynamics code. A straight-through seal with two leaning ns and a honeycomb land was analysed. The computational model was prepared based on some simplications introduced to improve the eciency of the calculations. The rotor entire blade-to-blade channel was analysed, while the seal pitch was reduced to the dimensions of two honeycomb cells. The geometry of the ns themselves was simplied too. In the original variant, the n tips had caps to protect them from wear (shape deformation) due to rubbing. In the simplied model, the caps were omitted. The simplications did not change the leakage mass ow signicantly. Several variants of changes in the basic geometrical parameters of the seal were analysed to assess their eect on the leakage mass ow for altered ow conditions. Parameters such as the n thickness, the n inclination angle and the position of the ns and of the entire labyrinth were analysed. The best seal variant was selected, the ow phenomena were commented on and some points in the design of this type of the labyrinth seal were discussed.
Źródło:: Transactions of the Institute of Fluid-Flow Machinery; 2017, 136; 3-21
0079-3205
Pojawia się w:: Transactions of the Institute of Fluid-Flow Machinery
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Thermo-economic comparative analysis of gas turbine GT10 integrated with air and steam bottoming cycle
Autorzy:: Czaja, D.
Chmielnak, T.
Lepszy, S.
Powiązania:: https://bibliotekanauki.pl/articles/240831.pdf
Data publikacji:: 2014
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: gas turbine air bottoming cycle
air bottoming cycle
gas turbine
GT10
układ gazowo-powietrzny
turbina gazowa
Opis:: A thermodynamic and economic analysis of a GT10 gas turbine integrated with the air bottoming cycle is presented. The results are compared to commercially available combined cycle power plants based on the same gas turbine. The systems under analysis have a better chance of competing with steam bottoming cycle configurations in a small range of the power output capacity. The aim of the calculations is to determine the final cost of electricity generated by the gas turbine air bottoming cycle based on a 25 MW GT10 gas turbine with the exhaust gas mass flow rate of about 80 kg/s. The article shows the results of thermodynamic optimization of the selection of the technological structure of gas turbine air bottoming cycle and of a comparative economic analysis. Quantities are determined that have a decisive impact on the considered units profitability and competitiveness compared to the popular technology based on the steam bottoming cycle. The ultimate quantity that can be compared in the calculations is the cost of 1 MWh of electricity. It should be noted that the systems analyzed herein are power plants where electricity is the only generated product. The performed calculations do not take account of any other (potential) revenues from the sale of energy origin certificates.
Źródło:: Archives of Thermodynamics; 2014, 35, 4; 83-95
1231-0956
2083-6023
Pojawia się w:: Archives of Thermodynamics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: The effects of variable operational parameters on an aero engine labyrinth seals performance
Autorzy:: Szymański, A.
Dykas, S.
Majkut, M.
Strozik, M.
Powiązania:: https://bibliotekanauki.pl/articles/175364.pdf
Data publikacji:: 2018
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: labyrinth seals
experiment
turbomachinery
gas turbine
validation
Opis:: The paper presents the accurate assessment of the amount of gas flowing through three types of aero-engine expander sealing. Structures consisting of straight-through labyrinth seals – with one, two and three fins are considered. The study deploys two independent approaches. The first one focuses on the experimental research using high-precision test section with non-rotating labyrinth seals specimen connected to a high capacity vacuum installation. Experimentally tested seals are of actual size (model to engine scale is 1:1). High accuracy hot-wire anemometry probes, and orifice plate are deployed to evaluate the flow indicators accurately, allowing for comparison of different sealing structures. The second approach uses quasi-two-dimensional axissymmetric, steady-state Reynolds averaged Navier Stokes (RANS) computations to simulate the flow field. Various meshes and turbulence models were tested, presenting capabilities as well as limitations of specific computational approaches. The experimental and computational results were compared with literature data, showing a good agreement regarding overall trends, yet underlining some local discrepancies. This paper brings two significant findings. The 2D RANS methods tend to overestimate the leakage when compared with experimental results, and the difference is more significant for advanced arrangements. There is a notable difference between the performance of labyrinth seal with one fin and structure with two and three fins. In some operational areas, one-finned seal performs better than more advanced ones, reducing the leakage more effectively. This feature of one finned seal is not intuitive, as one would expect it to perform worse than a seal with two or three fins.
Źródło:: Transactions of the Institute of Fluid-Flow Machinery; 2018, 140; 83-104
0079-3205
Pojawia się w:: Transactions of the Institute of Fluid-Flow Machinery
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

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: 15.

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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