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Wyświetlanie 1-2 z 2
Tytuł:
Temperature effect on explosion parameters of hydrogen-air deflagrations in presence of water vapor
Autorzy:
Grabarczyk, M.
Żbikowski, M.
Mężyk, Ł.
Teodorczyk, A.
Powiązania:
https://bibliotekanauki.pl/articles/115947.pdf
Data publikacji:
2016
Wydawca:
Fundacja na Rzecz Młodych Naukowców
Tematy:
explosion pressure
hydrogen
closed vessel
elevated temperature
water vapor
deflagration
ciśnienie wybuchu
wodór
naczynie zamknięte
podwyższona temperatura
para wodna
deflagracja
Opis:
Results of investigation of hydrogen-air deflagrations phenomenon in closed vessel in various initial temperatures and volume fraction of water vapor are presented in following paper. Tests were performed in apparatus which construction complies with EN 15967 recommendations—20-litre sphere. Studied parameters were explosion pressure (Pex) and maximum explosion pressure (Pmax). Defining the influence of the initial conditions (temperature and amount of water vapor) on the maximum pressure of the hydrogen-air deflagration in a constant volume was the main aim. Initial temperatures were equal to 373K, 398K and 413K. Initial pressure was ambient (0.1 MPa). Hydrogen volume fraction differed from 15% to 80%, while humidity volume fraction from 0% to 20%. Ignition source was placed in geometrical center of testing chamber and provided energy between 10-20J from burnout of fuse wire with accordance to abovementioned standard. Common features of all experimentally obtained results were discussed. Maximum explosion pressure (Pmax) decreases with increasing the initial temperature. Furthermore, addition of the water vapor for constant initial temperature decreases value of Pmax and shifts the maximum peak to the direction of lean mixtures. Data provided in paper can be useful in assessment of explosion risk of industry installations working with hydrogen-air atmospheres with high water vapor addition.
Źródło:
Challenges of Modern Technology; 2016, 7, 3; 39-44
2082-2863
2353-4419
Pojawia się w:
Challenges of Modern Technology
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Resistojet thruster with a power system based on supercapacitors
Autorzy:
Mezyk, L.
Kobiera, A.
Boruc, L.
Biczel, P.
Wolanski, P.
Powiązania:
https://bibliotekanauki.pl/articles/115727.pdf
Data publikacji:
2014
Wydawca:
Fundacja na Rzecz Młodych Naukowców
Tematy:
resistojet
thruster
satellite
ster strumieniowy
satelita
Opis:
This paper presents research into a resistojet model that can be powered by supercapacitors for satellite propulsion applications. The performance of the system, calculated including a preliminary study of mass and power budget, shows that this solution has potential for a certain range of space missions. The main problem when designing a pulsed resistojet is the compromise between the thermal capacity of the resistojet and the heat transfer efficiency of the device. When the heater is used in pulsed mode, it should have low mass and thermal capacity in order to reduce the energy required to heat the devices. On the other hand, the main technical restriction in resistojet thrusters is heat transfer due to the laminar regime of the flow in the heater. The heat transfer area should be as large as possible, but the mass of the device limits any such increase in area. In this research several design options were considered in an attempt to find the optimal solution. After research on the oscillating element and porous heater, capillary tubes directly heated by the current were determined to be the most effective solution. A power supply based on supercapacitors was constructed. It consists of 30 supercapacitors of 300 F each, connected to deliver 70 V of voltage, 10F of total capacitance and maximum peak power of 5 kW. Research for three different gases – ammonia, propane and butane – was conducted and the results are presented in this paper.
Źródło:
Challenges of Modern Technology; 2014, 5, 3; 13-21
2082-2863
2353-4419
Pojawia się w:
Challenges of Modern Technology
Dostawca treści:
Biblioteka Nauki
Artykuł
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