Autor: Łukasik, W. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Full-electric, hybrid and turbo-electric technologies for future aircraft propulsion systems
Autorzy:: Łukasik, B.
Wiśniowski, W.
Powiązania:: https://bibliotekanauki.pl/articles/243487.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: full electric
turbo-electric
hybrid systems
distributed propulsion systems
Opis:: Recently a huge progress in the field of electrical machines makes them more available for aviation. Assuming a big leap forward of electric technology in the near future, many research institutes around the World examine a revolutionary propulsion system which employs electrical machines. This idea can be a perfect response to a drastically growing air traffic and its demands about emission and fuel consumption reduction. There are already manufactured full electric, ultralight airplanes, which show that the technology is promising and future-proof. What is more it seems to be a key enabler for the development of the other technology that will influence the future of aircraft design and will allow introducing completely new airplane architectures. That is why Institute of Aviation in collaboration with The Ohio State University conducts investigation and analysis on feasibility of using such systems for aircraft propulsion. For this task a completely new tool based on Numerical Propulsion System Simulation (NPSS) environment is being developed. It will enable to analyse the electric devices conjugated with turbine engine as a whole propulsion system in the matter of its performance characteristics. The purpose of this paper is to present some of the most promising ideas and already accomplished analysis of different kinds of architectures. The analysis and optimization of the system, as well as cost effectiveness will be presented.
Źródło:: Journal of KONES; 2016, 23, 4; 305-310
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

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

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Skocz do pozycji: 3.

Tytuł:: Measurements of pressure in front of shock wave : assessment of methodology influence on the measurement results on the basis of experiments with the shock tube
Autorzy:: Perkowski, W.
Irzycki, A.
Kawalec, M.
Łukasik, B.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/242676.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: shock wave
shock tube
pressure measurements
Opis:: The experiments, described in the article, are related to research of a rotating detonation that has been conducted in the Institute of Aviation in Warsaw since 2009, under the OPIE project: “Turbine engine with detonation combustion chamber”. Measurements of the shock wave parameters, are among the most difficult in the art. This is due to high speed of the wave transition, and above all, a very small thickness of the shock wave. For the purposes of the mentioned project, a methodology for measuring pressure on the rotating detonation wave was developed. It included the type of sensors, their location and their protection from heat and flames. In order to determine the capabilities, limitations and accuracy of the method that was used, a series of experiments were planned and carried out. They enabled the assessment of the impact, on the measurement of pressure in the shock wave, of the following factors: the location of the sensor (frontal and lateral) relative to the shock wave front, protrusion or retraction of the sensor in its housing, the covering of the sensor with a protective layer (such as a high temperature silicon). This paper presents the results of the experiments that were carried out with use of a small shock tube of a simple design. The high-pressure part of the tube (so-called “driver”) was charged with the compressed nitrogen gas. The membrane was designed to be torn by pressure and pressure magnitude of the shock wave were measured by a “twin pair” of the Kistler 603B type piezoelectric sensors, one of which was always the reference sensor.
Źródło:: Journal of KONES; 2013, 20, 4; 333-340
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Initiation of rotating detonation in experimental combustion chamber : practical realization
Autorzy:: Kawalec, M.
Perkowski, W.
Irzycki, A.
Snopkiewicz, K.
Wróblewski, W.
Bilar, A.
Łukasik, B.
Powiązania:: https://bibliotekanauki.pl/articles/246536.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: engines
shock wave
shock tube
pressure measurements
Opis:: Since 2009 in the Institute of Aviation, Warsaw a project that aim is to develop combustion chamber with rotating detonation for turbine engine has been carried out. Desired fuel is aviation kerosene (Jet-A) detonated in air. One of the most important problems to be solved was the initiation of rotating detonation in combustible mixture, which requires the fulfilment of several conditions: 1) good mixing of combustible mixture components, 2) properly fast flow of combustible mixture in the cylinder-shaped channel, 3) the appropriate height of the flow channel, associated with detonation cell size for the combustible mixture, 4) use of a source of detonation initiation with an appropriate energy and power for a given combustible mixture. There were considered and tested, in practice several different types of initiators: a) spark electric discharge in air, b) plasma electric discharge (the so-called "exploding wire"), c) micro-explosive charges, d) blank ammunition, e) gas initiator (with detonation of acetylene-oxygen stoichiometric mixture induced by spark electric discharge). The paper summarizes the theoretical energy parameters of several types of initiators, and the results of their comparative research on the test bench. In the course of these researches, the pressures of the shock wave generated by the initiators and recorded by a fast pressure sensor located at a distance from the initiator were compared.
Źródło:: Journal of KONES; 2013, 20, 4; 163-168
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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