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    Wyświetlanie 1-4 z 4
    Tytuł:
    Report on the implementation of the POIG project „turbine engine with a detonation combustion chamber”
    Autorzy:
    Kalina, P.
    Wolański, P.
    Balicki, W.
    Perkowski, W.
    Rowiński, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/241703.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    combustion
    rotating detonation
    turbine engine
    Opis:
    This article contains a description of the work carried out under the UDA-POIG 01.03.01-14-071/09-10 project titled “A turbine engine with a detonation chamber”. The work carried out during the project involved 14 construction, research and calculation tasks. Various research stands designed to analyse the process of mixture formation, initiation of detonation and research of rotating detonation in combustion chambers were constructed. Test stand for examining a turboshaft engine with detonation combustion chamber was built. Those test stands allowed powering the combustion chambers and the engine with both liquid and gaseous fuels, simultaneously or separately. At the same time, REFLOPS software, which could calculate the propagation of a detonation wave was created, and used in the design of further versions of combustion chambers. Data from the experiments was used to verify the calculations and models created in the mentioned software. GTD-350 engine was used as the base; the structure of which (combustion chamber situated outside the turbine-compressor unit) facilitated modifying the shape of the detonation combustion chamber. During the research, great emphasis was placed on the safety of researchers. Working with hydrogen in high temperatures and JET-A1 fuel, which was additionally heated, and the usage of the oxy-acetylene detonators forced extreme caution, and full compliance with developed procedures. The project was divided into 14 tasks that were often conducted simultaneously in a 20-person team implementing the project. The work was completed by performing comparative studies between conventional engine with deflagration combustion chamber, and modified engine with a detonation combustion chamber. During the completion of the project, it was the first working demonstrator engine with detonation combustion chamber in the world.
    Źródło:
    Journal of KONES; 2016, 23, 2; 177-184
    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:
    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:
    Możliwości rozwoju silników turbinowych z detonacyjną komorą spalania
    Growth opportunities for turbine engine with detonation combustion chamber
    Autorzy:
    Wolański, P.
    Kalina, P.
    Balicki, W.
    Rowiński, A.
    Perkowski, W.
    Kawalec, M.
    Łukasik, B.
    Powiązania:
    https://bibliotekanauki.pl/articles/213335.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    spalanie detonacyjne
    wirująca detonacja
    silnik turbinowy
    detonative combustion
    rotating detonation
    turbine engine
    Opis:
    W artykule zaprezentowano obszerne badania zastosowania wirującej detonacji w silniku turbinowym. Stanowisko badawcze umożliwiało dostarczenie powietrza o wydatku 2,5 kg/s i ciśnieniu 2,5 bara z możliwością jego podgrzewania do ponad 100°C. Wykonano układ zasilania stanowiska paliwem podgrzewanym do 170°C oraz dodatkowo gazowym wodorem. Stanowisko badawcze wyposażone było w układy pomiarowe i sterowania: wydatkiem powietrza i paliwa oraz w system akwizycji danych w tym szybkozmiennych przebiegów cisnień w komorze spalania. Szeroko zakrojone badania wirującej detonacji realizowane były na otwartych i zdławionych komorach spalania oraz po dołączeniu ich do turbowałowego silnika GTD-350. Przedstawiono warunki uzyskania stabilnej detonacji. Stwierdzono, że w przypadku wirującej detonacji w silniku zasilanym gazowym wodorem sprawność cieplna może być podwyższona o 5-7 % w porównaniu do sprawności silnika z deflagracyjną komorą spalania.
    Extensive and complex studies of the application of continuously rotating detonation (CRD) to gas turbine are presented. Special installation of high pressure preheated air supply system was constructed which allows to supply air at rate of a few kg/s, preheated to more than 100°C and at initial pressure up to 2,5 bar. Supply system for Jet-A fuel which could be preheated to 170°C was also constructed. Additionally gaseous hydrogen supply system was added to the installation. Also measuring system for controlling air flow and measurements of detonation parameters was installed and data acquisition and control system implemented. Extensive research of conditions in which CRD could be established and supported in open flow detonation chambers, throttled chambers and finally in detonation chambers attached to the GTD-350 gas turbine engine where conducted. Condition for which stable detonation was achieved are presented. It was found that for conditions when the GTD-350 engine was supplied by gaseous hydrogen, thermal efficiency of the engine could be improved even by 5-7% as compare to the efficiency of the base engine.
    Źródło:
    Prace Instytutu Lotnictwa; 2016, 3 (244); 202-214
    0509-6669
    2300-5408
    Pojawia się w:
    Prace Instytutu Lotnictwa
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-4 z 4

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