Autor: Łukasik, A. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

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: 2.

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: 3.

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: 4.

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: 5.

Tytuł:: Three - dimensional numerical simulations of the combustion chamber of the rotating detonation engine
Autorzy:: Folusiak, M.
Swiderski, K.
Kobiera, A.
Lukasik, B.
Wolanski, P.
Powiązania:: https://bibliotekanauki.pl/articles/245644.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: rotating detonation engine (RDE)
RDE
computational fluid dynamics (CFD)
CFD
REFLOPS
Opis:: From 2010 Warsaw University of Technology (WUT) and Institute of Aviation (IoA) jointly implement the project under the Innovative Economy Operational Programme entitled ‘Turbine engine with detonation combustion chamber’. The goal of the project is to replace the combustion chamber of turboshaft engine GTD-350 with an annular detonation chamber. During the project, the numerical group that aims to develop computer code allowing researchers to simulate investigated processes has been established. Simulations provide wide range of parameters that are hardly available from experimental results and enable better understanding of investigated processes. Simulations may be also considered as a cheap alternative for experiments, especially when testing geometrical optimizations. In this paper the analysis of simulation results of the combustion chamber of the Rotating Detonation Engine (RDE) investigated at the IoA in Warsaw is presented. Primarily, REFLOPS USG which has become a fundamental numerical tool in the research of the RDE at the IoA is briefly described and governing equations and numerical methods used are shortly presented. Some aspects of numerical simulations of the RDE, related to selection of combustion mechanism, and an initiation of rotating detonation are provided. Secondly, results of simulations of inviscid gas with numerical injectors of hydrogen are compared with available experimental results. Three different wave patterns are identified in numerical solution and briefly described. Results of simulations are compared to experimental results in combustion chamber. Results presented in this paper are part of the project UDA-POIG.01.03.01-14-071 ‘Turbine engine with detonation combustion chamber’ supported by EU and Ministry of Regional Development, Poland.
Źródło:: Journal of KONES; 2013, 20, 1; 83-88
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Numerical tools for three dimensional simulations of the rotating detonation engine in complex geometries
Autorzy:: Swiderski, K.
Folusiak, M.
Kobiera, A.
Lukasik, B.
Wolanski, P.
Powiązania:: https://bibliotekanauki.pl/articles/242471.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: CFD
RDE
rotating detonation engine (RDE)
AMR
REFLOPS
hydrogen
Opis:: This paper describes the development of a computational code REFLOPS USG (REactive FLOw solver for Propulsion Systems on UnStructured Grids) based on the Favre averaged Navier-Stokes equations with chemical reactions for semi-ideal multicomponent gas to predict the structure and dynamics of three-dimensional unsteady detonation as it occurs in the Rotating Detonation Engine (RDE). This work provides an overview of second order accurate in time and space finite volume method applied to conservation equations and its implementation on unstructured self-adaptive tetrahedral or hexahedral three-dimensional cell-centred meshes. The inviscid fluxes are given by the Riemann solver and stabilization is ensured by the proper limiters inherited from the TVD theory or gradient based limiters. The stiff equations of chemical kinetics are solved by use of implicit DVODE (Double precision Variablecoefficient Ordinary Differential Equation solver, with fixed-leading-coefficient implementation) routine or by explicit Chemeq2 routine. Additional improvements are incorporated into the code such as parallelization in OpenMP and implementation of NVIDIA CUDA technology. REFLOPS USG has become a fundamental numerical tool in the research of RDE at the Institute of Aviation in Warsaw, in frame of Innovative Economy project UDA-POIG.01.03.01-14-071 ‘Turbine engine with detonation combustion chamber’ supported by EU and Ministry of Regional Development, Poland. The simulations presented in this paper are based on inviscid or viscous multicomponent semi-ideal gas flow with chemical reactions. Due to high computational costs only simple chemical reaction mechanisms are used here.
Źródło:: Journal of KONES; 2013, 20, 1; 329-336
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

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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