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Tytuł:
Influence of geometry and type of cooling holes on thermal load of combustion chamber
Autorzy:
Swiatek, M.
Domański, R.
Powiązania:
https://bibliotekanauki.pl/articles/246265.pdf
Data publikacji:
2010
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engines
engine combustion chamber
combustor cooling
CFD
Opis:
The objective of this thesis is to compare various methods of combustor wall cooling and their effectiveness by numerical simulations. It was determined that the first task was to verify how much air is coming through single axial hole with 3.5% pressure drop between hot and cold part of combustion chamber. The results from this flow check serve as a base template for generating more accurate and precise models of single axial hole cooling as well as calculation of hole diameter for multihole cooling. Second task was to generate more sophisticated single hole model with boundary layer in order to better simulate the conditions in areas near the combustion chamber walls and get more accurate results. The same method was used to create multihole model. In order to compare efficiency, all created domains in every model have the same volume, model settings, operating and boundary conditions. Geometry of all models described above is created using SIMENS NX4 and SIMENS NX5 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization into a structural finite volume grid took place in commercial pre-processor GAMBITŽ (GAMBIT and FLUENT - commercial CFD codes from Ansy s Inc). The airflow andheat exchange will be calculated using program FLUENTŽ. The results were shown in the thesis in terms of several comparative pictures of the temperature fields in the combustion chamber domain, and graphs representing difference in temperature fields on cooling wall of the combustion chamber.
Źródło:
Journal of KONES; 2010, 17, 4; 485-494
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Combustor liner cooling methods - numerical simulation
Autorzy:
Lazarczyk, M.
Domański, R.
Powiązania:
https://bibliotekanauki.pl/articles/247755.pdf
Data publikacji:
2010
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engines
engine combustion chamber
combustor cooling
CFD
Opis:
The objective of this thesis is to compare various methods of combustor wall cooling and to evaluate advantages and disadvantages of each applied cooling methods. It was determined that the flrst task was to verify how much air is coming through singe radial hole with 2.5% pressure drop between hot and cold part ofcombustion chamber. Flowcheck was calculated also to see how geometry of cooling hole affects hole effective area. Second task was to generale 3d model and mesh of both calculated types of cooling. Each model mesh was covered with boundary layer in order to better simulate conditions near the combustion chamber walls and obtain accurate results. In order to run back-to-back analysis, all created models have the same number of mesh elements, same materials used, samefluent settings, same operating and boundary conditions. Geometry of all models described above was created using Unigraphics NX4 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization was done in commercial pre-processor GAMBITŽ. The airflow and conjugated heat transfer analysis was calculated in program FLUENTŽ. The goal of this thesis was to obtain temperature fields and distribution in the combustion chamber domain (lip and panel wall) and to evaluate if applied cooling is sufficient to cool down heat loaded part of the combustor chamber.
Źródło:
Journal of KONES; 2010, 17, 4; 277-286
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Teoretyczna analiza wpływu systemu aktywnej pokrywy komory silnika na obliczenia prędkości kolizyjnej samochodu, który potrącił pieszego
Theoretical analysis of the active hood system effect on the calculation of the impact speed of a car hitting a pedestrian
Autorzy:
Wach, Krzysztof
Powiązania:
https://bibliotekanauki.pl/articles/26917664.pdf
Data publikacji:
2022
Wydawca:
Wydawnictwo Instytutu Ekspertyz Sądowych
Tematy:
potrącenie pieszego
prędkość kolizyjna
prędkość uderzenia
komora silnika
pedestrian accident
speed collision
impact speed
engine chamber
Opis:
Celem pracy była analiza wpływu systemu aktywnej pokrywy komory silnika na obliczenia prędkości kolizyjnej samochodu, który potrącił pieszego. Jednym z coraz częściej stosowanych tego typu systemów jest tak zwana aktywna pokrywa komory silnika (ang. Active Hood, Pop-up Bonnet). Po wykryciu kontaktu przedniej części nadwozia z pieszym, sterownik systemu generuje sygnał inicjujący uniesienie pokrywy, najczęściej jej tylnej części. Działanie to zapewnia zwiększenie dystansu pomiędzy pokrywą a twardymi elementami znajdującymi się w komorze silnika, redukując obrażenia pieszego (zwłaszcza głowy). Zmiana położenia pokrywy w trakcie zderzenia może mieć wpływ na wartość zmierzonego na samochodzie zasięgu wrzucenia oraz rozwinięcia pieszego, czyli wielkości wykorzystywanych do szacowania prędkości kolizyjnej samochodu. W artykule dokonano teoretycznej analizy wpływu zadziałania systemu na wartość przyrostu rozwinięcia pieszego, a w konsekwencji na szacowaną wartość minimalnej prędkości uderzenia. Uzyskane wyniki wskazują, iż w niektórych przypadkach uniesienie pokrywy komory silnika może nieznacznie wpływać na szacowaną wartość prędkości kolizyjnej, nie powinno to mieć jednak istotnego wpływu na rezultaty prowadzonej analizy.
The aim of the work was an analysis of the currently used solutions that ensure pedestrian protection at the time of collision. Selected systems from the area of external passive safety of a car are presented. One of the increasingly used systems of this type is the so-called Active Hood (Pop-up Bonnet). As a result of detecting the contact of the front part of the car body with a pedestrian, the system controller generates a signal initiating the lifting of the engine cover (usually its rear part) upwards. This increases the distance between the bonnet and the hard components in the engine compartment, reducing the severity of injuries to pedestrians (especially the head). The change of the position of the engine cover during a crash may have an impact on the value of wrap around distance. This quantity is used to estimate the collision speed of the car. The article presents a theoretical analysis of the impact of the Active Hood safety system on the value of the pedestrian wrap around distance increment and, consequently, on the estimated value of the minimum impact velocity. The obtained results indicate that in some cases the lifting of the bonnet may have a slight influence on the estimated value of the collision velocity, however, this should not have significant influence on the results of the analysis.
Źródło:
Paragraf na Drodze; 2022, 2; 63-71
1505-3520
2956-3631
Pojawia się w:
Paragraf na Drodze
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Przycinanie falkowe w analizie sygnału ciśnienia zarejestrowanego w komorze spalania silnika
Wavelet shrinking in an analysis of pressure signal recorded in engine combustion chamber
Autorzy:
Górski, K.
Lotko, W.
Gielniewski, G.
Powiązania:
https://bibliotekanauki.pl/articles/312046.pdf
Data publikacji:
2013
Wydawca:
Instytut Naukowo-Wydawniczy "SPATIUM"
Tematy:
szumy pomiarowe
redukcja szumów
komora spalania silnika
dyskretna transformata falkowa
przycinanie falkowe
noise measureement
noise reduction
engine combustion chamber
discrete wavelet transform
wavelet shrinking
Opis:
W artykule przedstawiono możliwości wykorzystania dyskretnej transformaty falkowej w przetwarzaniu sygnału ciśnienia zarejestrowanego w komorze spalania silnika. W szczególności skupiono uwagę na opisaniu techniki przycinania falkowego, którą można wykorzystać w celu redukcji szumów pomiarowych. W analizie wykorzystano sygnał o znanych parametrach energii oraz określonej amplitudzie wysokoczęstotliwościowych oscylacji ciśnienia charakterystycznej dla zjawiska stuku w silniku. Oceniono zmianę tych parametrów w zależności od rodzaju falki, którą wykorzystano w celu redukcji szumów pomiarowych.
Paper presents the discrete wavelet transform in processing of pressure signal recorded in engine combustion chamber. In particular the wavelet shrinking technique was described for reducing of signal noise. In showed analysis the signal with known parameters of energy and maximum amplitude of knock oscillation was used. Variations of these parameters in relation to selected wave used in present analysis were also discussed.
Źródło:
Autobusy : technika, eksploatacja, systemy transportowe; 2013, 14, 3; 2081-2088
1509-5878
2450-7725
Pojawia się w:
Autobusy : technika, eksploatacja, systemy transportowe
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The effect of location on the combustion chamber for the toxicity exhaust in self-ignition engine Ursus 4390
Autorzy:
Kalina, P.
Powiązania:
https://bibliotekanauki.pl/articles/247388.pdf
Data publikacji:
2015
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
piston engine
diesel
combustion chamber
Opis:
As a part of the research work done on the engine URSUS 4390 which aimed at increasing power while reducing exhaust gas emissions, intake channels in the head, shape of the combustion chamber and compression ratio were modified. Proper injection equipment was selected and atomizer nozzles were constructed. In the first phase of the research, toroidal combustion chamber was located in factory design location. In the article there are presented results of exhaust gas emissions in selected operating points of engine URSUS 4390 for various positions of experimental combustion chamber. An innovative method of changing the position of the combustion chamber related to the piston axis was developed. A rotating insert with eccentrically extruded combustion chamber was mounted in piston axis. Rotation of the insert by a given angle resulted in displacement of combustion chamber around the axis of rotation. For each particular position of combustion chamber, concentration of toxic flue gas components and smoke index was measured at full load with rotational speed of 1400 and 2000 rpm. Proposed piston construction with rotating insert allowed to significantly decreasing duration of the research, which aimed at verification of combustion chamber relative location to injector and inlet nozzle. This way the necessity of construction of new sets of pistons and lapping them each time was avoided. As a result of the work, 11 locations of combustion chamber were tested. The study allowed picking the position of combustion chamber, which guarantees lowest emissions of toxic flue gas components.
Źródło:
Journal of KONES; 2015, 22, 2; 97-102
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Internal combustion micro-chambers and micro-engines
Autorzy:
Kraszewska, H.
Rusin, M.
Powiązania:
https://bibliotekanauki.pl/articles/244746.pdf
Data publikacji:
2008
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
internal combustion engine
microengine
shaft less engine
combustion chamber
Opis:
Technological progress caused miniaturization of internal-combustion engines. They found application in many areas. The acquaintance of the ignition and combustion processes in the small volumes, the solution of the problem of piston movement under the influence of a pulse combustion in chambers, the choice of materials and problems related with the mixtures and exhaust creation, all these issues require a exact acquaintance for the purpose of optimization of the micro engine performance. In the paper, some issues are talked over on the base of investigations performed on the small volume chambers in single compression machines and in the shaftless two-cycle engine. Researched was the influence of the micro chamber size and of the area/volume ratio value on the processes of combustion occurring in the very small volumes and with the large values of area/volume ratio. Together with raise of the area/volume ratio, the value of the combustion pressure impulse becomes lower. The influence of the chamber material type on the combustion processes was defined, both in the single compression machine as in the micro engine. The existence of micro chamber size influence on the combustion limits of the fuel/air mixtures was designated. It has been determined that the range of the combustion limit is decreased with diminishing of the combustion chamber diameter, at the same time these changes are not the function of the area/volume ratio value changes. The maximum values of the combustion pressure appeared when chamber was supplied with stoichiometric mixture, irrespective of the chamber dimensions.
Źródło:
Journal of KONES; 2008, 15, 4; 283-288
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The influence of the shape of the combustion chamber on exhaust gases toxicity in T370 engine
Autorzy:
Kalina, P.
Kawalec, M.
Powiązania:
https://bibliotekanauki.pl/articles/243782.pdf
Data publikacji:
2015
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
diesel engine
combustion chamber
geometry
toxicity
Opis:
An important issue in construction of combustion chamber in compression-ignition engines is proper selection of its shape and size. Both features are dependent on several factors such as fuel injector location and angle, spray atomizer selection (amount of holes, their diameter and angular position), location of inlet valve and air turbulence. By doing research on prototype engine T370, an analysis of influence of combustion chamber size and its modifications going towards lip construction on flue gas toxicity was done. The diameter and depth of combustion chamber was being changed while maintaining the same compression ratio. After that, a modification of tested combustion chambers was made by creating so called “lip”, which aim was to create a swirl of injected fuel in the vertical plane. To visualize the changes in swirl, a numerical analysis of fuel injection into combustion chamber was made. In discussed study, emission tests were performed according to ECE-R49. During the research six combustion chambers with diameters 60, 63 and 66 mm (and their modification) were investigated. Tests were performed for several types of injectors and different injection timing. However, for analysis of combustion chamber size the results are presented for the same injectors but with optimized injection timing.
Źródło:
Journal of KONES; 2015, 22, 2; 104-108
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The rig stand for testing integrated rocket ramjet engine
Autorzy:
Rowiński, A.
Powiązania:
https://bibliotekanauki.pl/articles/246853.pdf
Data publikacji:
2016
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
turbine engine
combustion chamber
detonation combustion
rotating detonation engine
RDE
Opis:
Integrated rocket ramjet engine is adapted to aircraft propulsion and supersonic missiles moving at the speed of 8 Ma. The engine’s construction enables flexibly benefit from both types of drive depending on the conditions of the flight. The ejector mode of operation applicable to Mach numbers smaller than 2 cooperate with the rocket engine positioned in flow channel. Secondary air stream enters the engine through the convergent divergent nozzle and supplies the air to the ejector and booster. Rocket engine using the ejector effect would be used only in the phase of accelerating an object to the supersonic speed and then the drive would gradually shift to ramjet. The range of speed for the ramjet mode is 2-6 Mach. The prototype of the rocket ramjet engine of over 1300 N is equipped with annular combustion chamber in which phenomena of rotating detonation as well as the aero spike nozzle were used. Both the test stand as well as the engine is adapted to trials suitable to the conditions of a flight at the speed of 1.4 Ma. The test stand is powered by compress air coming from the instalment set up in the earth test bed and by oxygen and methane at a pressure of 10 bar. The rig is designed for functional tests of prototype, areas of the creation of mixture of firearms used to measuring and the range of stable functioning of the engine in the ramjet mode. Moreover, the measured parameters in gas supply installations as well as the temperature and pressure in the combustion chamber and thrust created by integrated rocket ramjet engine are measured.
Źródło:
Journal of KONES; 2016, 23, 4; 421-428
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Study on kerosene atomization process under a high speed air stream
Autorzy:
Perkowski, W.
Irzycki, A.
Snopkiewicz, K.
Grudzień, Ł.
Kawalec, M.
Powiązania:
https://bibliotekanauki.pl/articles/247137.pdf
Data publikacji:
2011
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
transport
aircraft engine
combustion chamber
fuel atomization
Opis:
For the needs of fuel-injection system development for the experimental detonation combustion chamber with a rotating detonation (PoiG - Project: "Turbine engine with detonation combustion chamber") a series of experiments with injection of kerosene under a high speed air stream was performed at the Institute of Aviation. The proper preparation of combustible mixture is very important for the initiation and sustenance of a rotating detonation. The task in case of kerosene-air mixture is far more difficult than for mixtures of hydrogen-air or kerosene-oxygen. A simple stream injector has been tested as a base system, and the kerosene was injected perpendicular to the air stream vector directly from the plane wall of the constant cross-section channel. The process of injection and atomization of kerosene was observed in the special transparent visualization chamber, enabling the spray observation of two mutually perpendicular directions. In subsequent experiments air pressure, air temperature and air flow velocity as well as and injection pressure of kerosene were varied. The tested process was photographed and, in case of chosen experiments, filmed using a high-speed digital camera. The surveys were aimed at identifying and assessing of following parameters of fuel atomization process: the range of the fuel stream and filling grade of research channel with aerosol, aerosol homogeneity and the size of forming it droplets, the possible presence of fuel streams flowing down the walls of channel. The resulting photos allowed for more comprehensive, but only a qualitative assess of the spraying process, while the filmed small regions of visualization chamber allowed the counting down and dimensioning of droplets. This paper presents a test facility and measuring techniques applied during the research activity and selected results of carried out tests.
Źródło:
Journal of KONES; 2011, 18, 4; 341-347
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Start-up and acceleration control of the turbine engine with the detonation combustion chamber
Autorzy:
Balicki, W.
Powiązania:
https://bibliotekanauki.pl/articles/247622.pdf
Data publikacji:
2015
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
turbine engine
combustion chamber
rotating detonation engine (RDE)
start-up control
Opis:
This article presents the results of tests of helicopter turbine engine, where the classic combustion chamber was replaced with an innovative solution. In this chamber instead of the classic combustion deflagration, was generated a rotating detonation. Theoretical considerations expected to get a higher engine efficiency, because as the thermodynamic Fickett-Jacobs cycle, which can describe the working principle turbine engine detonation chamber, has a higher efficiency than a Brayton cycle, according to which the engines of conventional chamber are working. The appearance of detonation combustion was diagnosed basing on observation of the gas pressure flue in the chamber, using piezoelectric sensors. Before the detonation chamber was used in turbine engine, a series of problems on the various methods of initiation of detonation process and the procedures for controlling the flow rate into the chamber of air and fuel were solved. There was a test stand constructed, which used a helicopter turbine engine GTD-350, wherein the jugs combustion chamber was replaced with detonation chamber. A control system for the flow of fuel in the combustion chamber was developed: aviation kerosene Jet-A1 with addition of hydrogen. With its use obtained unfailing starts of chamber, also the engine running on the idle and on the flight range and accelerations at idle range to flight range. The possibility of the detonation combustion for a long time, especially in transient states - practically limited only by the capacity of fuel tanks – is the achievement of the research team.
Źródło:
Journal of KONES; 2015, 22, 4; 21-27
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Study of combustion chamber with a rotating detonation
Autorzy:
Łukasik, B.
Rowiński, A.
Irzycki, A.
Snopkiewicz, K.
Powiązania:
https://bibliotekanauki.pl/articles/246882.pdf
Data publikacji:
2012
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
internal combustion engine
turbine engines
combustion chamber
rotating detonation
Opis:
Institute of Aviation in Warsaw realizes the project concerning the application of the phenomenon of combustion with rotating detonation to the combustion chamber designed and destined for turbine engines. The test chamber is adapted for supplying both with liquid (aviation kerosene) and gaseous fuels in the form of mixture with compressed air. It is equipped with a probe for pressure and temperature measurements inside the flame tube as well as at its inlet and outlet sections. The measuring system allows measurement of physical phenomenon at low (1 kHz) and high (1 MHz) frequencies. Electric signals representing temperature and pressure sensor's measuring quantities, fuel and compressed air supply systems parameters and ignition-triggering values are collected using data acquisition system controlled by a computer. The prototype of the combustion chamber was examined at the especially designed test facility to determine at quasi-static operating conditions its following characteristics: speed of inside shock wave, exhaust gas thermodynamic parameters and ignition and going-out limits of gaseous fuel. In this article construction of test bench, schematic diagrams of measurement and power supply systems as well as the research process, the way of measurement data analysis recorded during the carried-out experiments and data validation manner are detailed described. The method of measurement data processing, the resulting graphs, and the conclusions of the study are presented as well.
Źródło:
Journal of KONES; 2012, 19, 2; 313-320
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Testing of initiation of rotating detonation process in hydrogen - air mixtures
Autorzy:
Balicki, W.
Irzycki, A.
Łukasik, B.
Snopkiewicz, K.
Powiązania:
https://bibliotekanauki.pl/articles/247318.pdf
Data publikacji:
2012
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
internal combustion engine
turbine engines
combustion chamber
rotating detonation
Opis:
The paper presents results of some research work done in the project, which aims to apply of an innovative combustion chamber to the turbine engine. Expected benefits of using of a new chamber in which classical deflagration type combustion process would be replaced with a detonation combustion type, arise from greater efficiency of FickettJacobs cycle, which corresponds to rotating detonation combustion, in comparison to "classical" Brayton cycle, characteristic of deflagration combustion. The presented task concerned fundamental research carried out on test bench designed and built at the Institute of Aviation in Warsaw. To initiate the detonation combustion in the fuel-air mixtures the ignition device of appropriately high energy is necessary. The released energy should be directed to the area where the mixture has proper constitution - preferably close to stoichiometric one. Four different ignition manners were examined in the course of research: electrical ignition system adapted from turbine engine (semiconductor spark plug), powder charge ignition (handgun cartridges), detonation primer ignition using pentryt, and high voltage discharge (plasma jet). The appearance of detonation type combustion was identified on the basis of combustion gas pressure run, measured using piezoelectric sensors at a frequency of 1 MHz.
Źródło:
Journal of KONES; 2012, 19, 2; 25-34
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
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
Artykuł
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
Artykuł
Tytuł:
Analiza wybranych wskaźników pracy silnika dwuprzepływowego z dwiema komorami spalania
Analysis of chosen work parameters of two-comustor turbofan engine
Autorzy:
Jakubowski, R.
Kuźniar, M.
Powiązania:
https://bibliotekanauki.pl/articles/254334.pdf
Data publikacji:
2016
Wydawca:
Instytut Naukowo-Wydawniczy TTS
Tematy:
silnik dwuprzepływowy
spalanie
komora spalania
turbofan engine
combustion
combustion chamber
Opis:
W artykule przedstawiono wyniki badań numerycznych porównujących efektywność pracy klasycznego silnika dwuprzepływowego oraz silnika dwuprzepływowego z dwiema komorami spalania. Na wstępie podano istotne informacje dotyczące konstrukcji silnika dwuprzepływowego z dodatkową komorą spalania usytuowaną pomiędzy turbiną wysokiego i niskiego ciśnienia i wynikające stąd korzyści eksploatacyjne silnika. Przedstawiono zasadnicze różnice w modelu silnika z dwiema komorami spalania oraz przeanalizowano ich wpływ na osiągi silnika. Wykonano symulacje komputerowe pracy silnika z dwiema komorami spalania i porównano je z wynikami dla klasycznego silnika dwuprzepływowego. Wskazano na istotne cech silnika dwukomorowego, które są związane z doborem parametrów obiegu silnika. Wykazano, że w odróżnieniu od klasycznego silnika dwuprzepływowego można wyznaczyć spręż całkowity silnika, dla którego spełnione będzie jednocześnie kryterium osiągnięcia minimum jednostkowego zużycia paliwa i maksimum ciągu jednostkowego. W wyniku obliczeń parametrów eksploatacyjnych wyznaczono przebiegi podstawowych parametrów pracy silnika dla różnych warunków lotu i wskazano występowanie zakresów konstrukcyjnych i eksploatacyjnych, w których silnik z dwiema komorami spalania będzie rozwiązaniem korzystniejszym niż klasyczny silnik dwuprzepływowy. Na podstawie wykonanych analiz sformułowano wnioski dotyczące porównania cech eksploatacyjnych obydwu typów silników.
The results of numerical investigation of perfor-mance of the classical turbofan engine and a two-combustor turbofan are presented in the paper. The basic information of the two-combustor turbofan are presented in the beginning. The differences in the model of two-combustor turbofan engine vs. classical turbofan were presented and their influence on engine performance was discussed. The numerical simulation of compared engine performance was done. By this way it was presented that it was possible to establish two-combustor engine parameters that specific thrust is maximum and specific fuel consumption is minimum. This is impossible to fulfillment for classical turbofan engine. The simulation of engine performance vs. altitude and flight velocity was done. By this way it was demonstrated that two-combustor turbofan engine performance are close to performance of classical turbofan and that there are some flight condition, for with two-combustor engine could be better than classical turbo-fan.
Źródło:
TTS Technika Transportu Szynowego; 2016, 12; 100-105
1232-3829
2543-5728
Pojawia się w:
TTS Technika Transportu Szynowego
Dostawca treści:
Biblioteka Nauki
Artykuł
Wyświetlanie 1-15 z 39

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