Temat: gas turbine engine - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Modelling the characteristics of axial compressor of variable flow passage geometry, working in the gas turbine engine system
Autorzy:: Wirkowski, P.
Powiązania:: https://bibliotekanauki.pl/articles/259564.pdf
Data publikacji:: 2007
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: marine gas turbine engine
Opis:: This paper concerns application of mathematical modelling methods to analyzing gas-dynamic processes in marine gas turbines. Influence of geometry changes in axial compressor flow passage on kinematical air flow characteristics, are 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:: Polish Maritime Research; 2007, 3; 27-32
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Usage of Cold Forcing Method for a Gas Turbine Engine of Supersonic Transport
Autorzy:: Gutakovskis, Viktors
Gudakovskis, Vladimirs
Blumbergs, Ilmārs
Sarma, Elina
Powiązania:: https://bibliotekanauki.pl/articles/2201886.pdf
Data publikacji:: 2023
Wydawca:: Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:: aviation
GTE
gas turbine engine
supersonic
plane
aircraft
Opis:: The article discusses the current state of development of supersonic transport, analyses the main limitation of the use of gas turbine engines when flying at high supersonic flight speeds, proposes a method for expanding the range of GTE limitations in these flight modes of the aircraft, using cold forcing of the engine, conducts an analytical study of the effectiveness of this approach, proposes one of the possible devices for the implementation of cold forcing, the efficiency of an engine with cold forcing is shown, which may be of significant interest for the application of cold forcing methods in gas turbine engines of supersonic transport.
Źródło:: Advances in Science and Technology. Research Journal; 2023, 17, 1; 267--273
2299-8624
Pojawia się w:: Advances in Science and Technology. Research Journal
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: The influence of multi - role aircraft mission type on the low bypass engine performance parameters
Autorzy:: Wygonik, P.
Powiązania:: https://bibliotekanauki.pl/articles/242065.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine engine design
airplane-engine integration
aircraft mission optimization
Opis:: The aim of the article is to find the relationship and dependencies between the mission parameters of the multi-role aircraft (altitude, flight velocity, thrust load) and the parameters that define the flow of the turbofan engine. The conclusions of these studies are relevant at the stage of preliminary engine design. There was built the model of thermal cycle of low bypass. The model of an airplane was simplified to its aerodynamic characteristics. The mission was divided into air tasks (stages) such as a take-off, a climb at a certain velocity, sub and supersonic flight and maneuvers (i.e. turn). Dimensionless energy criteria binding both the engine and aircraft parameters were introduced. There were conducted the simulation studies of the model airplane-engine mission to show the part of the mission that "dimensions " the engine. The results were limited to the presentation of the impact of circuit parameters such as T3, π, μ on the defined criteria. The calculations were carried out for a number of selected missions defined in the literature as Loll, HiLoHi and HiHiHi. The comparison of the energy requirements of these missions was done. There were pointed out these criteria of the mission evaluation that may affect making decisions at early design stages. There were designated the areas of design variability in an engine meeting the criteria for energy mission. The advantage of this model is universal character of dimensionless criteria, whereas the disadvantage is the need to build complex models of the engine and the assumption at the outset aerodynamic characteristics of the aircraft. The originality of the presented solution is to show an alternative, unconventional approach to the design process (not as so far) the engine itself but the entire aviation system.
Źródło:: Journal of KONES; 2013, 20, 3; 435-442
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Investigation of the combustion processes in the gas turbine module of an fpso operating on associated gas conversion products
Autorzy:: Cherednichenko, Oleksandr
Serbin, Serhiy
Dzida, Marek
Powiązania:: https://bibliotekanauki.pl/articles/259197.pdf
Data publikacji:: 2019
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: thermo-chemical heat recovery
gas turbine engine
associated gas
combustor
Opis:: In this paper, we consider the issue of thermo-chemical heat recovery of waste heat from gas turbine engines for the steam conversion of associated gas for offshore vessels. Current trends in the development of offshore infrastructure are identified, and the composition of power plants for mobile offshore drilling units and FPSO vessels is analyzed. We present the results of a comparison of power-to-volume ratio, power-to-weight ratio and efficiency for diesel and gas turbine power modules of various capacities. Mathematical modeling methods are used to analyze the parameters of an alternative gas turbine unit based on steam conversion of the associated gas, and the estimated efficiency of the energy module is shown to be 50%. In the modeling of the burning processes, the UGT 25000 serial low emission combustor is considered, and a detailed analysis of the processes in the combustor is presented, based on the application of a 35-reaction chemical mechanism. We confirm the possibility of efficient combustion of associated gas steam conversion products with different compositions, and establish that stable operation of the gas turbine combustor is possible when using fuels with low calorific values in the range 7–8 MJ/kg. It is found that the emissions of NOx and CO during operation of a gas turbine engine on the associated gas conversion products are within acceptable limits.
Źródło:: Polish Maritime Research; 2019, 4; 149-156
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Model dynamiczny wytwornicy spalin z symulowanymi uszkodzeniami
Dynamic model of gas generator with faults simulations
Autorzy:: Grządziela, A.
Powiązania:: https://bibliotekanauki.pl/articles/211170.pdf
Data publikacji:: 2010
Wydawca:: Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:: silnik turbinowy
drgania
modelowanie
gas turbine engine
vibration
modelling
Opis:: W artykule przedstawiono metodę modelowania wirnika wytwornicy spalin silnika turbinowego wraz z wprowadzonymi obciążeniami pochodzącymi m.in. od niewyrównoważenia wirnika. Model umożliwia wprowadzenie wirtualnego przemieszczenia osi wału wirnika, statycznego i dynamicznego niewyrównoważenia w zakresie parametrów eksploatacyjnych charakterystycznych dla rzeczywistego silnika. Równania ruchu uwzględniające oddziaływania zewnętrzne zaimplementowano do środowiska Matlab Simulink. Model wirnika pozwala na transmisję momentu napędowego zarówno w symulowanym procesie rozruchu zimnego jak i gorącego. Podstawowymi oddziaływaniami dynamicznymi występującymi w modelu są: moment napędowy, aerodynamiczne momenty oporowe, pionowe i poziome siły działające na wsporniki łożysk, oddziaływania wynikające z niewyrównoważenia mającego swoje źródło w zmianie stanu technicznego wirnika. Uzyskane wyniki przebiegów czasowych parametrów drganiowych oraz ich widma zostały zidentyfikowane z wynikami badań rzeczywistego silnika pracującego na okręcie, co było jednym z głównych celów badań. Wyniki wykazały wysoką zgodność oraz wrażliwość na wprowadzane wartości brzegowe potwierdzające przydatność modelu w diagnostyce technicznej. Ważnym atutem modelu jest brak jego wrażliwości na zewnętrzne oddziaływania zakłócające środowiska morskiego. Uzyskany model podczas identyfikacji potwierdził swoją wrażliwość zarówno na zmienne parametry ruchu jak i zadane oddziaływania zmieniające jego stan techniczny.
The paper presents a method of modelling of gas generator rotors at the presence of virtually introduced dynamics loads, like unbalancing effects. The rotors model provides opportunities for introducing shaft displacements, static and dynamic unbalancing and rotations similar to those observed in a real object. The equations of motion, taking into account the action of external agents, were implemented to the Matlab Simulink software. In the rotors model, the driving torque is transmitted from the cold and hot start processes. The following actions were introduced to the proposed dynamic model: main engine driving torque, aeorodynamic antitorques, horizontal and vertical forces, the action resulting from changes in relative positions of load-carrying bearings and thrust bearings in the rotors line, the action of the unbalancing coming from changes of technical state. The obtained time-histories and their spectra were compared with the experimental results of the tests performed on the marine testing ground. A basic goal of modelling is the identification of the diagnostic model. In the reported case, comparing the results of the empirical studies and the simulations has proved good applicability of the proposed model. The obtained results confirmed model sensitivity to changes of technical state of the object and varying input parameters. A vital property of the model was the insensibility of the unbalancing symptom to the action of assumed environmental disturbances, such as sea environment forces. The performed model identification confirmed its sensitivity to changing parameters of motion and external actions.
Źródło:: Biuletyn Wojskowej Akademii Technicznej; 2010, 59, 4; 71-83
1234-5865
Pojawia się w:: Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Influence of the gas turbine engine design parameters on the energy consumption of the multirole aircraft missions
Autorzy:: Wygonik, P.
Powiązania:: https://bibliotekanauki.pl/articles/246706.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine engine design
simulation
airplane-engine integration
aircraft mission optimization
Opis:: In the article the analysis of the influence of design parameters of the engine on the performed by the multirole aircraft mission was performed. The problem is complex as a result of performing a series of manoeuvres in various conditions of flight. A special feature of multi-role aircraft mission is a sudden (even pulse) weight change and exactly its reduction as a result of the discharge of cargo bomb, rocket or due to the consumption of ammunition during air combat manoeuvring. Reducing the airplane mass by the weight of the fuel consumed (continuously) and the used weapons radically differ the demands on the energy required to overcome gravity and drag forces. The article shows how the reduction of the aircraft mass influences on the change of the thrust load factor. It was built the mathematical model of the system engine-aircraft-air job (taking into account the flight conditions, elements of the mission - subsonic and supersonic flight, flight time, the heat-and-gasdynamic and mass model of the engine). The model enables for the simulation research of the complex flight missions and their evaluation on the basis of the constructed criteria. The model includes a parametric description of physical processes in the turbofan engine, thus provides a direct assessment of the impact of selection of engine parameters on the effectiveness of the mission. The results of calculations according to classical criteria (e.g. kilometre fuel consumption, specific fuel consumption) were presented. The paper presents new criteria, which enable to analyze the energy consumption of the complex mission of the aircraft (e.g. energy consumption: the unit range, the degree of utilization of energy resources and the carried out the mission engine). Criteria were built in by combining the parameters necessary for the flight with disposable ones. On the basis of these parameters there was done an assessment of the "quantitative" adjustment of a power unit to various missions such as subsonic, supersonic and mixed (for different their proportion), for different levels and the plane range. The results were presented in a pictorial way on numerous charts.
Źródło:: Journal of KONES; 2012, 19, 2; 569-576
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Investigations of the working process in a dual-fuel low-emission combustion chamber for an FPSO gas turbine engine
Autorzy:: Serbin, Serhiy
Diasamidze, Badri
Dzida, Marek
Powiązania:: https://bibliotekanauki.pl/articles/1585065.pdf
Data publikacji:: 2020
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: gas turbine engine
dual-fuel combustion
combustion chamber
liquid fuel
Opis:: This investigation is devoted to an analysis of the working process in a dual-fuel low-emission combustion chamber for a floating vessel’s gas turbine. The low-emission gas turbine combustion chamber with partial pre-mixing of fuel and air inside the outer and inner radial-axial swirlers was chosen as the object of research. When modelling processes in a dualflow low-emission gas turbine combustion chamber, a generalized method is used, based on the numerical solution of the system of conservation and transport equations for a multi-component chemically reactive turbulent system, taking into consideration nitrogen oxides formation. The Eddy-Dissipation-Concept model, which incorporates Arrhenius chemical kinetics in a turbulent flame, and the Discrete Phase Model describing the interfacial interaction are used in the investigation. The obtained results confirmed the possibility of organizing efficient combustion of distillate liquid fuel in a low-emission gas turbine combustion chamber operating on the principle of partial preliminary formation of a fuel-air mixture. Comparison of four methods of liquid fuel supply to the channels of radial-axial swirlers (centrifugal, axial, combined, and radial) revealed the advantages of the radial supply method, which are manifested in a decrease in the overall temperature field non-uniformity at the outlet and a decrease in nitrogen oxides emissions. The calculated concentrations of nitrogen oxides and carbon monoxide at the flame tube outlet for the radial method of fuel supply are 32 and 9.1 ppm, respectively. The results can be useful for further modification and improvement of the characteristics of dual-fuel gas turbine combustion chambers operating with both gaseous and liquid fuels.
Źródło:: Polish Maritime Research; 2020, 3; 89-99
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Thermal degradation process of semi-synthetic fuels for gas turbine engines in non-aeronautical applications
Autorzy:: Sarnecki, Jarosław
Białecki, Tomasz
Gawron, Bartosz
Głąb, Jadwiga
Kamiński, Jarosław
Kulczycki, Andrzej
Romanyk, Katarzyna
Powiązania:: https://bibliotekanauki.pl/articles/258646.pdf
Data publikacji:: 2019
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: gas turbine engine
thermal stability
bio-fuels
thermal degradation process
Opis:: This article concerns the issue of thermal degradation process of fuels, important from the perspective of the operation of turbine engines, especially in the context of new fuels/bio-fuels and their implementation. The studies of the kerosenebased jet fuel (Jet A-1) and its blends with synthetic components manufactured according to HEFA and ATJ technology, were presented. Both technologies are currently approved by ASTM D7566 to produce components to be added to turbine fuels. Test rig investigations were carried out according to specific methodology which reflects the phenomena taking place in fuel systems of turbine engines. The mechanism of thermal degradation process was assessed on the basis of test results for selected properties, IR spectroscopy and calculation of activation energy. The results show that with the increase of the applied temperature there is an increment of the content of solid contaminants, water and acid for all tested fuels. Thermal degradation process is different for conventional jet fuel when compared to blends, but also semi-synthetic fuels distinguished by different thermal stability depending on a given manufacturing technology.
Źródło:: Polish Maritime Research; 2019, 1; 65-71
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Snizhenie intensivnosti pul'sacionnogo gorenija v kamere sgoranija GTD ispol'zovanijem plazmennykh stabilizatorov
Reduction in the intensity of the pulsation burning in gas turbine combustion chamber using plasma stabilizers
Autorzy:: Serbin, S.
Mostipanenko, A.
Kozlovskiy, A.
Powiązania:: https://bibliotekanauki.pl/articles/76712.pdf
Data publikacji:: 2015
Wydawca:: Komisja Motoryzacji i Energetyki Rolnictwa
Tematy:: reduction
gas turbine engine
combustion chamber
pulsating combustion
mathematical modelling
Źródło:: Motrol. Motoryzacja i Energetyka Rolnictwa; 2015, 17, 2
1730-8658
Pojawia się w:: Motrol. Motoryzacja i Energetyka Rolnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Przedłużanie okresu eksploatacji okrętowych turbin gazowych w oparciu o modele predykcyjne
Extension of Marine Gas Turbine Engine Operation Time Based on Predictive Models
Autorzy:: Adamkiewicz, A.
Tomaszewski, F.
Powiązania:: https://bibliotekanauki.pl/articles/358935.pdf
Data publikacji:: 2006
Wydawca:: Akademia Morska w Szczecinie. Wydawnictwo AMSz
Tematy:: okrętowa turbina gazowa
diagnoza
model
predykcja
marine gas turbine engine
diagnosis
prediction
Opis:: Do klasyfikacji stanów turbin zastosowano relacje pomiędzy parametrami sygnału diagnostycznego oraz dopuszczalnymi i granicznymi wartościami parametrów pracy. Do prognozowania czasu poprawnego działania silników zastosowano predykcyjne modele regresji wielokrotnej, opisujące wartości obserwowanych parametrów diagnostycznych jako funkcje mocy i czasu użytkowania czynnego silników. Pokazano przykład weryfikacji modeli dla wyznaczonego czasu użytkowania. Oszacowano dokładność prognozy.
Relations between diagnostic signal parameters and acceptable limit values of operational parameters were used to classify the states of gas turbine engines. For predicting the time of faultless operation of engines we used predictive models describing the values of observed diagnostic parameters as a function of power and active operation time of engines. An example was presented to show the verification of models for a preset operation time. The accuracy of predictions was estimated.
Źródło:: Zeszyty Naukowe Akademii Morskiej w Szczecinie; 2006, 10 (82); 21-30
1733-8670
2392-0378
Pojawia się w:: Zeszyty Naukowe Akademii Morskiej w Szczecinie
Dostawca treści:: Biblioteka Nauki

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