Autor: Irzycki, A. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: GTD-350 engine powered by LPG : research work
Autorzy:: Kalina, P.
Niedziałek, B.
Gryglewski, W.
Irzycki, A.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/247365.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: turboshaft engine
liquefied petroleum gas (LPG)
toxicity
Opis:: The paper presents results of comparative tests of exhaust gases toxicity of GTD-350 turboshaft engine powered by Liquefied Petroleum Gas (LPG) and conventional JET-A1 fuel. Structure of GTD-350 engine’s test bed was discussed. Because of explosion danger of LPG vapour the test stand was arranged in the open air. Paper comprises specification of LPG supply system, gas injector’s construction and visualization of LPG injection. The supply system was based on the newly constructed pressurized injectors. Required LPG operating pressure was obtained by pressurizing LPG tank using nitrogen and LPG-flow was controlled using needle valve. A series of photographs presents shape of fuel streams for new injector supplied by JET-A1 and LPG. Photos of flame torches for multi-hole and conical type injectors fuelled by LPG are inserted as well. A comparative study of carbon monoxide, nitrogen oxides, hydrocarbons and carbon dioxide as well as oxygen concentration for GTD-350 equipped with new injectors fuelled by LPG and standard supplied by Jet-A1 was carried out. The study comprised turbocharger speed range between 40 and 80% of NTS. The exhaust gas temperature comparison for above-mentioned configuration is presented as well. All data shown in presented figures are mean of 6 measurements. All completed tests were carried out for standard GTD-350 engine combustion chamber.
Źródło:: Journal of KONES; 2013, 20, 3; 209-214
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

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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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:: Some problems resulting from powering of turbine engines by liquified petroleum gas (LPG)
Autorzy:: Balicki, Wł.
Kalina, P.
Snopkiewicz, K.
Irzycki, A.
Powiązania:: https://bibliotekanauki.pl/articles/244699.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: power engineering
turbine engines
alternative fuels
liquified petroleum gas (LPG)
feeding system
Opis:: There has been observed for several years a number of attempts to introduce for everyday use small power units which utilize turbine engine as propulsion unit (the U.S., Japan, and Europe). Efficiency increase of such devices is achieved by improving of turbine engine design as well as utilizing of exhaust gas thermal energy to heat the compressed air supplied to combustion chamber and, for example to heat usable water. Significant orientation of turbine engine improvements lead to the modernization of combustion processes by applying of gaseous fuels (such as compressed natural gas) or implementation of high-temperature catalytic combustion. The purpose of these changes reduction of hydrocarbons, carbon monoxide and nitrogen oxides emissions. In Propulsion Department of Aviation Institute a scientific project has been realized, in which the object of study was aircraft turbine engine powered by a liquid propane-butane mixture. The paper presents some results of engine tests carried out, especially concerning feeding system, special fuel system applied LPG pumping systems with the use of sliding-vane pump and by means of pressure reservoir and combustion process of LPG atomized with the use of original GTD-350 vortex injector, adapted for aviation kerosene Jet-A.
Źródło:: Journal of KONES; 2013, 20, 4; 17-22
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

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: 6.

Tytuł:: High speed electromechanical energy storage
Autorzy:: Rowiński, A.
Irzycki, A.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/246662.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: kinematic energy storage
electric motors
Opis:: Kinematical, electromechanical energy accumulator is a facility that converts supplied electrical energy to the kinetic one, stored in the rotating inertial system. Electric driving motors can operate both as a propulsion units, providing torque to the rotor shaft, and as generators in the course of braking. The prototype is designed to operate in a vacuum; the energy accumulator is located in a sealed pressurized vessel connected to the apparatus, which can generate vacuum pressure down to 1 Pa. The accumulator is destined for storage energy of 7.2 MJ at a speed of up to 20,000 1 / min. The energy accumulator is equipped with inert weight in the form of metal disc, connected to a composite band. In the course of operation, the rotor assembly is suspended in noncontact manner in housing assembly while the main body is fastened to the inner ring of the pressure vessel. The rotor consists of a shaft on which are mounted: a metal disc together with a band made of carbon fibre, inset into inert weight using epoxy resin; four disc rotors of two electric motors; two disks which are magnetic armature for electromagnetic bearings operating along the shaft axis; bushings of both sleeve bearings; fixing sleeves, washers and lock nuts to fix particular elements on the shaft. During normal operation the rotor is positioned in the radial direction through two electromagnetic bearings, top and bottom, located at both ends of shaft and operating in the differential arrangement, and in the axial direction - by a system of two eight-pole electromagnetic bearings. In the idle state rotor is based on the spherical tip of the mobile support and on the raceway of slide bearing located in the top cover. The prototype facility is designed to carry out performance tests, both under normal conditions of pressure and temperature and in vacuum environment, of: electromagnetic bearings, start-up/emergency devices, functional integration of all components and air tightness of tubing inside the tank. Measurement of radial and axial clearances between the rotor elements and housing for full speed range will be completed also.
Źródło:: Journal of KONES; 2012, 19, 2; 459-464
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Procedures and treatments leading to reduction of toxic components emission in diesel engines exhaust gas
Autorzy:: Kalina, P.
Irzycki, A.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/248119.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: diesel engine
pollution
reduction of emission
Opis:: The fight against global warming and Earth atmosphere pollution has been for years one of the most important tasks of governments and national economies of the European Union members. Abandonment of efforts leading to reduction mainly of carbon dioxide emission by heavy industry, electric power generation based on coal, passenger aviation and wheeled passenger transport will inevitably be leading to deterioration of health condition of our citizens. This article presents an overview of commonly used structural and technological treatments which have impact on reduction of toxic standardized exhaust pollutants in the surface transport, exemplified on SW 400 engine version of L2 / 3 and its turbocharged version 6CT 107 2/L2. The impact of: engine's adjustment parameters, catalytic afterburners, exhaust gas recirculation, modifications of injectors, turbochargers, supercharging air-cooling and particulates filter on carbon monoxide, hydrocarbons, nitrogen oxides and particulates emission was thoroughly examined. The parameters being compared were the results of toxicity tests according to ECE-R49 Regulation and a maximal smoke values on full-load characteristics. In conclusion, of the paper the limiting allowable values of toxic components emitted in Diesel engines exhaust gases in the following EU Emission Standards are presented.
Źródło:: Journal of KONES; 2012, 19, 1; 163-169
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

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: 9.

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: 10.

Tytuł:: Investigation of blade piston compressor
Autorzy:: Kalina, P.
Wodyński, P.
Irzycki, A.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/245549.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: mechanics
compressor
seals
Opis:: The paper presents the results of scientific research of the blade-type piston compressor which were conducted on the test rig built especially for this purpose. The construction concept of the compressor, design calculation of its main elements and tests of contact- and contactless sealing types were discussed in papers published at subsequent KONES-symposia 2009 and 2010. The results shown in present document are focused on studies of compressor having the piston equipped with labyrinth or contact seals. When testing on test bench, the intake air flow to the compressor as well as temperature and pressure of air compressed in the tank of 0.1 m3 were measured. Quick-changing pressure in the compression chamber and air temperature at the compressor's outlet were recorded and analyzed, also. The research was carried out for contact-type seals made of various materials which do not require lubrication and for contactless-type seals (labyrinth). In the course of studies the proper backlash between the piston and the cylinder wall was matched to ensure trouble-free operation of installation. The results of compressor power demand were presented in this article, too. This research work is performed under the framework program "Inicjatywa Technologiczna I" No 12218.
Źródło:: Journal of KONES; 2011, 18, 3; 143-148
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Study on kerosene atomization process under a high speed air stream
Autorzy:: Perkowski, W.
Irzycki, A.
Snopkiewicz, K.
Grudzień, Ł.
Kawalec, M.
Powiązania:: https://bibliotekanauki.pl/articles/247137.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aircraft engine
combustion chamber
fuel atomization
Opis:: For the needs of fuel-injection system development for the experimental detonation combustion chamber with a rotating detonation (PoiG - Project: "Turbine engine with detonation combustion chamber") a series of experiments with injection of kerosene under a high speed air stream was performed at the Institute of Aviation. The proper preparation of combustible mixture is very important for the initiation and sustenance of a rotating detonation. The task in case of kerosene-air mixture is far more difficult than for mixtures of hydrogen-air or kerosene-oxygen. A simple stream injector has been tested as a base system, and the kerosene was injected perpendicular to the air stream vector directly from the plane wall of the constant cross-section channel. The process of injection and atomization of kerosene was observed in the special transparent visualization chamber, enabling the spray observation of two mutually perpendicular directions. In subsequent experiments air pressure, air temperature and air flow velocity as well as and injection pressure of kerosene were varied. The tested process was photographed and, in case of chosen experiments, filmed using a high-speed digital camera. The surveys were aimed at identifying and assessing of following parameters of fuel atomization process: the range of the fuel stream and filling grade of research channel with aerosol, aerosol homogeneity and the size of forming it droplets, the possible presence of fuel streams flowing down the walls of channel. The resulting photos allowed for more comprehensive, but only a qualitative assess of the spraying process, while the filmed small regions of visualization chamber allowed the counting down and dimensioning of droplets. This paper presents a test facility and measuring techniques applied during the research activity and selected results of carried out tests.
Źródło:: Journal of KONES; 2011, 18, 4; 341-347
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Blade-type piston compressor investigation of seals
Autorzy:: Kalina, P.
Chomczyk, W.
Irzycki, A.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/246203.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: piston machines
piston compressor
seals testing
Opis:: The paper presents the test results of selected seals applied in the blade-type piston compressor designed and realized in Propulsion Department of Institute of Aviation according to Patent No 6822 specification. Principle of operation of the compressor and the construction of test stand utilized to the seals testing were presented in the paper published in the Journal of KONES 2009. The special blade-type piston realizes a pendulous movement in the circular cylinder divided into two bulkheads. Each of bulkheads, fitted out with a set of bidirectional operating valves, creates by sequential opening and closing of them two compression chambers for one blade. Comprehensive tests of different kinds of seals were carried out on a single-compression machine driven by pneumatic actuator. The pressure rise vs. blade movement and drop of pressure when the piston was stayed at top dead centre were measured. The results of leak tightness of other structures of blade-type piston were analyzed as well and are subject to the following paper. The new design of piston relied on fitting-out of piston with side disc was prepared with intention of eliminating the loss of usable pressure in compression chamber, especially in area of top dead centre. The proposed design eliminated the leaks on the drive shaft and lateral seals, but not on the cylindrical surface of disco.
Źródło:: Journal of KONES; 2010, 17, 1; 199-204
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Comparison the piston air engine performance with aviation gasoline (Avgas) or the E-85 ecological fuel supply
Autorzy:: Balicki, W.
Irzycki, A.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/243897.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: nternal combustion engine
piston air engines
ecological fuels
exhaust pollutant
Opis:: The fuel presently used for feeding of aircraft piston engines (petrol including TEL) is characterized by "strong unfriendliness" for environment. Many research centres have been going on fuels investigation, which could substitute Avgas utilized in aviation. This is why are there no being in force for Europe standards defining the allowable emission of pollutions in exhaust gases of aircraft piston engines (equivalent to EURO - standards introduced for traction engines). The mixtures of gas o line and alcohols are tested as "alternative" aircraft fuels for spark ignition engines, and in case of Diesel engines - evenjet kerosene. During the research works on test bed carried out at Institute of Aviation the performance offour-stroke aircraft carburettor piston engine supplied by "classical" aircraft petrol and the E - 85 fuel (mixture of petrol and ethanol) were compared. Except for measuring the functional parameters of engine (rotational speed, torque, specific fuel consumption, pressures and temperatures) the emissions of gaseous pollutants incorporated in exhaust gas were measured and analyzed. The range of modifications of engine supply system - necessary to introduce in case of changing of fuel type within the tested engine -was worked up. There are foreseen comparative test of fuelling the engine with mixtures of petrol and alcohols in different proportions in the next phase of research works.
Źródło:: Journal of KONES; 2010, 17, 3; 25-32
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Impact of low-temperature corona discharges on gaseous pollutants level in diesel engines exhaust gas
Autorzy:: Irzycki, A.
Kalina, P.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/246916.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: exhaust gas
plasma reactor
emissions of gaseous toxins
experimental study
Opis:: This publication presents the results of research on level changes of gaseous pollutants contained in the exhaust gas in the consequence of applying of equipment taking advantage of low-temperature corona discharges. Not only influence of different plasma reactor configurations on the emission of toxins have been evaluated, but also on the main parameters of the engine under test and exhaust gas cleaning efficiency as well. The device supplied by DC voltage of 10-15 kV the operating value generated a low-temperature corona discharge in the especially formed electrostatic field. The devices were located behind the exhaust manifold of Diesel engine then operated in the high temperature zone of exhaust. The survey was realized in parallel with on-going research program at Institute of Aviation which has related to purification of Diesel engine's exhaust gas from particulates. The test results of emission of toxins obtained using the flat-arrangement and the axial-symmetric reactor systems were compared and discussed. The multi-variant designs of axial-symmetric device allowed the purposeful formation of favourable shape and intensity of electrostatic field and values of current, which induced the corona discharge. This activity has created better research capabilities for different geometric configurations of the reactors, namely linear and angular location and size of deflecting electrodes, structure of blade assembly generating a corona discharge, matching of proper distance between deflecting electrodes and blades.
Źródło:: Journal of KONES; 2010, 17, 2; 145-152
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Blade piston compressor
Autorzy:: Kalina, P.
Chomczyk, W.
Irzycki, A.
Snopkiewicz, K.
Powiązania:: https://bibliotekanauki.pl/articles/242077.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: mechanics
compressor
MES
dynamic force analysis
Opis:: The paper describes the principles of building and working of new blade piston compressor. dynamic force analysis of assembly of crankshaft and first research results are also presented. The working principle of this compressor was patented by prof. W. Chomczyk. The piston, in shape of a blade, executes a pendulum movement in a circular cylinder. The two bulkheads with valves create four compression chambers for one piston. The compressor features compactness of construction and high efficiency. The lack of side thrust of the piston on cylinder surface is a major advantage of the construction. The lack of friction between crown and cylinder makes it possible to build an oil-free compressor. The strength calculation of chosen elements was executed in MES (Cosmos WORKS program). The acceleration of piston was a parameter which was optimized. The investigation of different tightening was conducted on a single-compression machine. The single compression machine was driven by pneumatic actuator having the task of imitation of piston movement during the compression cycle. The results of investigations of labyrinth seals are described in the paper. The compressor can find use in truck and bus aggregate drives. Paper present analysis of crank and crosshead mechanism 's kinematics, and dynamic loads, strength analysis of compressor components and construction of compressor.
Źródło:: Journal of KONES; 2009, 16, 3; 157-163
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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