Autor: Leżański, T. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Influence of compression ratio on combustion, turbulence, swirls into model combustion chamber of SI engines
Autorzy:: Leżański, T.
Sęczyk, J.
Wolański, P.
Powiązania:: https://bibliotekanauki.pl/articles/246616.pdf
Data publikacji:: 2015
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: internal combustion engines
spark ignition
combustion processes
new combustion systems
combustion process visualisation
Opis:: The results of the visualization researches, with the pressure measurement results are presented in the paper. Researches deal with the combustion system with semi-open combustion chamber for spark ignition engines. This system was elaborated in Aircraft Engine Department of Heat Engineering Institute of Warsaw University of Technology. During researches the influence of CR on a flame front propagation and turbulences into combustion chamber, when CR and ignition advance are varied, was determined. The model combustion chamber was made with the constant volumes ratio (the prechamber volume to the prechamber plus main combustion chamber volumes) of 28%. The CR were varied: 6:1, 8:1, 10:1 and 12:1, by changing of combustion chamber length and establish high. The researches were performed using rapid compression machine (RCM). The combustion sequences were recorded using high-speed digital camera with speed of 5000 frames per second. Simultaneously with combustion sequences recording, the high-speed pressure courses were registered. The research results show that the growth of compression ratio causes an improvement of combustion system performances; an increase of maximum cycle pressure and useful work field. The improvement of the performances is caused mainly by shortening of the combustion time and intensification of the turbulences and approaching of supposed combustion course.
Źródło:: Journal of KONES; 2015, 22, 4; 179-186
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Research effects of novel combustion system with semi-open combustion chamber using rapid compression machine
Autorzy:: Leżański, T.
Sęczyk, J.
Wolański, P.
Powiązania:: https://bibliotekanauki.pl/articles/245605.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: internal combustion engines
spark ignition
combustion processes
engine combustion systems
combustion process visualization
Opis:: The combustion system with semi open combustion chamber (SOCC) was originally elaborated in Aircraft Engine Department of Warsaw University of Technology. In this system the original combustion chamber of the standard SI engine, was divided by partition in prechamber and main combustion chamber, but yet this division exists only when the piston is close to TDC, on the contrary by the rest of the cycle the chambers are fully open. The system operation mechanism, the visualization research results, the high speed changed of the pressure measurements, was presented in this paper. The influence on the system performances of the different combustion systems parameters: the prechamber volume, the nozzle hole diameter in the partition, the ignition place, the compression ratio, and the ignition advance angle (IAA), on the basis of the research results, using rapid compression machine was presented in this paper. All research results show, that the best results of the system operation can be obtained if the stream outflow from prechamber to main combustion chamber starts when the piston is at TDC, and if the stream energy will be so big to displace all main combustion chamber before the clearance between partition and piston crown was opened. If the system operated correctly, the combustion time shortening, the growth of the maximum cycle pressure, and the combustion efficiency increase were obtained.
Źródło:: Journal of KONES; 2014, 21, 4; 297-310
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Control strategy combustion of system with semi – open combustion chamber of spark ignition engines
Autorzy:: Leżański, T.
Sęczyk, J.
Wolański, P.
Powiązania:: https://bibliotekanauki.pl/articles/241853.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: combustion engines
spark ignition engines
combustion processes
new combustion system
new strategy of combustion control
Opis:: The attempts to increase the engine combustion efficiency of the spark ignition (SI) engines have led to development of the new combustion system with semi-open combustion chamber. This system is similar to flame jet ignition systems, which were applied in many production internal combustion engines. The similar pulsed jet combustion system was elaborated by Professor A. K. Oppenheim. In the system developed at Aircraft Engine Department of Warsaw University of Technology (AED) the standard combustion chamber of SI engine was divided on prechamber and main combustion chamber using partition. The ignition in prechamber is more reliable and repeatable but total burning time in the prechamber and main combustion chamber is shorter than in standard combustion chamber. The principal problem of efficient operation of this system and obtaining of the required performance is securing the relevant control strategy. The performances of this system are dependent from: the rate of this prechamber volume to total combustion chamber volume, the orifice diameter in a partition, the ignition place and the ignition advance angle (ignition timing). Among these parameters the ignition timing only may be varied in the continuous manner during the engine operations without of the engine disassembling. Therefore constant values separate parameters (prechamber volume, orifice diameter, ignition place) should be selected in comprehensive, time consuming researches for different engine operation conditions (engine speed, load and environment conditions) and subsequently the map of ignition advance angles should be determined at state remaining separate parameters. The values of the ignition advance angle should be selected and programmed in electronic control unit, which will be control the ignition advance angle at different engine operating conditions. The dependences between engine operating parameters and the ignition timing are not linear and therefore mechanical control system is not effective. Some research results concerning the best engine operating parameters has been presented in this paper.
Źródło:: Journal of KONES; 2012, 19, 4; 367-377
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Flame front propagation in combustion system with semi - open combustion chamber with different compression ratio
Autorzy:: Leżański, T.
Sęczyk, J.
Wolański, P.
Powiązania:: https://bibliotekanauki.pl/articles/242590.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: internal combustion engines
spark ignition
combustion processes
new combustion systems
combustion process visualisation
Opis:: Researches of the combustion system with semi-open combustion chamber for spark ignition engines. This system was elaborated in Aircraft Engine Department of Heat Engineering Institute of Warsaw University of Technology. The researches concern the determination of influence CR on a flame front propagation into combustion chamber when CR and ignition advance are varied. The model combustion chamber make up with the constant volumes ratio of the prechamber volume to the prechamber plus main combustion chamber volumes, of 28%, but the CR were varied: 6:1, 8:1, 10:1 and 12:1, by changing of combustion chamber length. The researches were performed using rapid compression machine (RCM). The combustion sequences were recorded using high-speed digital camera with speed of 5000 frames per second. Simultaneously with combustion sequences recording, the high-speed pressure measurements were performed. The results of the visualization researches, with the pressure measurement results are presented in the paper. The research results show that the growth of compression ratio caused an improvement of combustion system performances; an increase of maximum cycle pressure and useful work field. The improvement of the performances is caused mainly by shortening of the combustion chamber length and approaching of supposed combustion course.
Źródło:: Journal of KONES; 2013, 20, 4; 227-235
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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