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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
Artykuł
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
Artykuł
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
Artykuł
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
Artykuł
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
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:
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
Artykuł
Tytuł:
The influence of on-design bypass turbine engine parameters on multipurpose aircraft missions energy-consuming
Autorzy:
Wygonik, P.
Powiązania:
https://bibliotekanauki.pl/articles/243880.pdf
Data publikacji:
2010
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
military gas turbine engine
military aircraft mission analysis
multipurpose aircraft
energy consuming
Opis:
In the article there was presented a quality assessment of parameters selection of bypass turbine engine for a multipurpose aircraft. It was assumed that the assessment criterion results from the energy-consumption of a flight. The criteria of energy-consumption range were defined as the relation of sum ofenergy supplied to the aircraft on the driven stages to the distance during a mission. The second criterion of unitary energy-consumption is defined as the relation of the movement energy-consumption to the product of the aircraft mass and the route during the elementary stage of the flight. With the use of the already worked out models of the power unit (bypass turbine engine with jet mixer and afterburner) of an aircraft (already known mass and aerodynamic characteristics) there were determined the ranges of thrust which are indispensable for a flight and available for the engine at each stage of the mission: take off, climb, subsonic and supersonic flight and turn with different overload factor. On the example of three chosen aircraft missions (Lo-Lo-Lo, Hi-Lo-Hi and Hi-Hi-Hi) the models of mission energy-consumption were developed. For the accepted change ranges of the comparative cycle parameters of the turbine engine the run of energy-consumption was tested. It was stated that for the assumed data the most energy-consuming mission is Lo-Lo-Lo, wherefore the increase of the compression and the rate of bypass reduces the energy-consumption of the mission.
Źródło:
Journal of KONES; 2010, 17, 1; 499-506
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Investigations of the emission characteristics of a dual-fuel gas turbine combustion chamber operating simultaneously on liquid and gaseous fuels
Autorzy:
Serbin, Serhiy
Diasamidze, Badri
Gorbov, Viktor
Kowalski, Jerzy
Powiązania:
https://bibliotekanauki.pl/articles/1573591.pdf
Data publikacji:
2021
Wydawca:
Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:
gas turbine engine
dual-fuel combustion
combustion chamber
liquid and gaseous fuels
Opis:
This study is dedicated to investigations of the working process in a dual-fuel low-emission combustion chamber for a floating vessel’s gas turbine. As the object of the research, a low-emission gas turbine combustion chamber with partial premixing of fuel and air inside the outer and inner radial-axial swirls was chosen. The method of the research is based on the numerical solution of the system of differential equations which represent the physical process of mass and energy conservation and transformations and species transport for a multi-component chemically reactive turbulent system, considering nitrogen oxides formation and a discrete ordinates model of radiation. The chemistry kinetics is presented by the 6-step mechanism of combustion. Seven fuel supply operating modes, varying from 100% gaseous fuel to 100% liquid fuel, have been analysed. This analysis has revealed the possibility of the application of computational fluid dynamics for problems of dual-fuel combustion chambers for the design of a floating vessel’s gas turbine. Moreover, the study has shown the possibility of working in different transitional gaseous and liquid fuel supply modes, as they satisfy modern ecological requirements. The dependencies of the averaged temperature, NO, and CO concentrations along the length of the low-emission gas turbine combustion chamber for different cases of fuel supply are presented. Depending on the different operating modes, the calculated emission of nitrogen oxides NO and carbon monoxide CO at the outlet cross-section of a flame tube are different, but, they lie in the ranges of 31‒50 and 23‒24 mg/nm3 on the peak of 100% liquid fuel supply mode. At operating modes where a gaseous fuel supply prevails, nitrogen oxide NO and carbon monoxide CO emissions lie in the ranges of 1.2‒4.0 and 0.04‒18 mg/nm3 respectively.
Źródło:
Polish Maritime Research; 2021, 2; 85-95
1233-2585
Pojawia się w:
Polish Maritime Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Mathematical modelling of marine power plants with thermochemical fuel treatment
Autorzy:
Cherednichenko, Oleksandr
Serbin, Serhiy
Tkach, Mykhaylo
Kowalski, Jerzy
Chen, Daifen
Powiązania:
https://bibliotekanauki.pl/articles/32907384.pdf
Data publikacji:
2022
Wydawca:
Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:
marine power plants
thermochemical fuel treatment system
gas turbine engine
mathematical modeling
Opis:
The article considers the methodological aspects of the theoretical investigation of marine power plants with thermochemical fuel treatment. The results of the study of the complex influence of temperature, pressure, and the ratio of steam / base fuel on the thermochemical treatment efficiency are presented. The adequacy of the obtained regression dependences was confirmed by the physical modelling of thermochemical fuel treatment processes. For a gas turbine power complex with a thermochemical fuel treatment system, the characteristics of the power equipment were determined separately with further merging of the obtained results and a combination of material and energy flow models. Algorithms, which provide settings for the mathematical models of structural and functional blocks, the optimisation of thermochemical energy transformations, and verification of developed models according to the indicators of existing gas turbine engines, were created. The influence of mechanical energy consumption during the organisation of thermochemical processing of fuel on the efficiency of thermochemical recuperation is analysed.
Źródło:
Polish Maritime Research; 2022, 3; 99-108
1233-2585
Pojawia się w:
Polish Maritime Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Application of thermo-chemical technologies for conversion of associated gas in diesel-gas turbine installations for oil and gas floating units
Autorzy:
Cherednichenko, Oleksandr
Serbin, Serhiy
Dzida, Marek
Powiązania:
https://bibliotekanauki.pl/articles/260620.pdf
Data publikacji:
2019
Wydawca:
Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:
thermo-chemical heat recovery
gas turbine engine
diesel engine
associated gas
steam reforming
efficiency
methane number
Opis:
The paper considers the issue of thermo-chemical recovery of engine’s waste heat and its further use for steam conversion of the associated gas for oil and gas floating units. The characteristics of the associated gas are presented, and problems of its application in dual-fuel medium-speed internal combustion engines are discussed. Various variants of combined diesel-gas turbine power plant with thermo-chemical heat recovery are analyzed. The heat of the gas turbine engine exhaust gas is utilized in a thermo-chemical reactor and a steam generator. The engines operate on synthesis gas, which is obtained as a result of steam conversion of the associated gas. Criteria for evaluating the effectiveness of the developed schemes are proposed. The results of mathematical modeling of processes in a 14.1 MW diesel-gas turbine power plant with waste heat recovery are presented. The effect of the steam/associated gas ratio on the efficiency criteria is analyzed. The obtained results indicate relatively high effectiveness of the scheme with separate high and low pressure thermo-chemical reactors for producing fuel gas for both gas turbine and internal combustion engines. The calculated efficiency of such a power plant for considered input parameters is 45.6%.
Źródło:
Polish Maritime Research; 2019, 3; 181-187
1233-2585
Pojawia się w:
Polish Maritime Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Analysis of vibration parameters of ship gas turbine engines
Autorzy:
Grządziela, A.
Powiązania:
https://bibliotekanauki.pl/articles/259671.pdf
Data publikacji:
2006
Wydawca:
Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:
turbiny gazowe
diagnostyka techniczna
drgania
bazy danych
gas turbine engine
technical diagnostics
vibrations
database
Opis:
This paper presents a method of vibroacoustic control of ship gas turbine engines. Analysis of recorded parameters makes it possible to identify unbalance of rotors, as well as sources of the unbalance. The presented software ANALIZA makes measured data storing and processing for engine diagnosing purposes possible.
Źródło:
Polish Maritime Research; 2006, 2; 22-26
1233-2585
Pojawia się w:
Polish Maritime Research
Dostawca treści:
Biblioteka Nauki
Artykuł
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
Artykuł
Tytuł:
Evaluation of marine gas turbine engine parameters in terms of exhaust harmful emissions
Autorzy:
Wirkowski, P.
Kniaziewicz, T.
Powiązania:
https://bibliotekanauki.pl/articles/133436.pdf
Data publikacji:
2017
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
harmful compounds
emission
exhaust gases
marine gas turbine engine
związki szkodliwe
emisja
spaliny
okrętowy silnik turbinowy
Opis:
The article presents an analysis of the use of gas turbine engine in the propulsion and marine power plant of vessels, taking into account environmental aspects. The preliminary results of emission tests of harmful exhaust emissions of the laboratory gas turbine engine were presented. Also an analysis was also undertaken on the possibility of carrying out measurements of concentrations of pollutants in the marine gas turbine engine propulsion systems in terms of its operation on the vessel.
Źródło:
Combustion Engines; 2017, 56, 4; 87-91
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The cascade pressure exchange reactive rotation disk engine creation reasons
Predposylki sozdanija diskovogo dvigatelja reaktivnogo vrashhenija kaskadnogo obmena davleniem
Autorzy:
Krajniuk, A.
Danileychenko, A.
Powiązania:
https://bibliotekanauki.pl/articles/793344.pdf
Data publikacji:
2012
Wydawca:
Komisja Motoryzacji i Energetyki Rolnictwa
Tematy:
cascade pressure exchanger
mass exchange
reactive rotation
working process
combustion engine
turning moment
hydrocarbon fuel
gas turbine engine
wave rotor turbine
engine torque
Opis:
The theoretical reasons of creation the reactive rotation disc engine on cascade pressure exchanger base (ERR CEP) have been stated. The particularities of ERR CEP working process in collation with wave disc engine on wave pressure exchanger base have been considered. It is in particular shown that cascade pressure exchange principles use allows vastly to increase the pressure of preliminary compression of charge and also to reduce the loss of expanding products of combustion in useful work turning moment of engine.
Ан н от ация. изложены теоретические предпосылки создания дискового двигателя реактивного вращения на базе каскадного обменника давления (ДРВ КОД). Рассмотрены особенности рабочего процесса ДРВ КОД в сопоставлении с волновым дисковым двигателем на базе волнового обменника давления. В частности показано, что использование принципов каскадного обмена давлением позволяет значительно увеличить давление предварительного сжатия заряда, а также снизить потери расширяющихся продуктов сгорания в полезную работу крутящего момента двигателя.
Źródło:
Teka Komisji Motoryzacji i Energetyki Rolnictwa; 2012, 12, 3
1641-7739
Pojawia się w:
Teka Komisji Motoryzacji i Energetyki Rolnictwa
Dostawca treści:
Biblioteka Nauki
Artykuł
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