Temat: rotating detonation - Katalog OPAC zbiorów

Skocz do pozycji: 1.

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

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Skocz do pozycji: 2.

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

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Skocz do pozycji: 3.

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

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Skocz do pozycji: 4.

Tytuł:: The study of the continuously rotating detonation combustion chamber supplied with different types of fuel
Autorzy:: Łukasik, B.
Czyż, S.
Irzycki, A.
Rowiński, A.
Powiązania:: https://bibliotekanauki.pl/articles/246684.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: rotating detonation
air/Jet-A detonation
detonation combustion chamber
internal combustion engine
Opis:: The paper summarizes research that was conducted last year as part of the project of “Turbine engine with detonation combustion chamber”. In this project, throughout 2012 and early 2013, tests were carried out on a test stand connected to the compressed air system. Research, of the rotating detonation phenomena, was carried out for a number of detonation chambers with different interior channel geometry. In addition, for each geometry configuration, tests were carried out for different levels of choking of the chamber outlet and hence for different pressures conditions inside the detonation chamber. This article presents the results of tests carried out for gaseous (hydrogen), hybrid (hydrogen + kerosene) and liquid (Jet-A) fuels, using different types of fuel injectors and for different fuel injection configuration settings (inside the chamber, or in front of the chamber). During these tests, parameters such as pressure behind the detonation wave (using piezoelectric sensors), the static pressure in front of and inside the detonation chamber and temperature: before, inside and at the outlet of the chamber, were measured. Research was performed for the various mass flow rates of air and fuel injected into the chamber that means for the different air-fuel equivalence ratios (Lambda). The main achievement of this study was to obtain a stable and reproducible rotating detonation of air and heated kerosene (Jet-A) mixture, thus the results presented in this paper presents mainly these tests as the most interesting to the reader
Źródło:: Journal of KONES; 2013, 20, 3; 259-266
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

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

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