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Liquefied petroleum gas (LPG), known by its ecological qualities, making Algeria has since the 1980s carried out a policy of development of LPG fuel in substitution of traditional fuels and especially petrol. However, following a series of accidents (fires, explosions, etc). that occurred in 1999, 20 years after the introduction of the LPG in France these incidents led to the search for the strengthening of the safety of the installations by better or new technical and/or organizational measures. This strategy consists in establishing a balance between environmental protection and economic profitability while ensuring the safety aspect.

The approach used is quantitative risk analysis authors have identified the potential accident scenarios that consist of leakage and rupture of tanks depend on bow tie. According to the latter using PHAST software, to model these scenarios (thermal, overpressure and dispersion) and their effects on human beings and goods.

In this paper, it was noted that there are scenarios such as (jet fire, dispersion), are affected by atmospheric conditions (wind speed humidity), the stronger the wind, the higher the LPG spread unlike instant scenarios (1.3 s for the fireball and millisecond for the explosion) that have not been related to climatic conditions because they have a short duration on the one hand, and on the other hand, a safe distance is given in each phenomenon. Finally, some instructions for drivers and installers have been identified by protective and preventive action.

Based on a quantitative risk analysis, this work involves modelling potential accident scenarios such as (fireball, jet fire, flash fire and explosion) in the event of a gas leak and rupture in the tank. It aims to sensitize drivers and LPG kit installers, even to get a clear view on these accidental phenomena and how to avoid them.

This contribution describes for one particular 45/90 MVA transformer design the results of finite element calculations of its leakage field and winding forces. The results show that the forces on the end turns and the leakage flux vary significantly with position. On the basis of these results the computation is extended to consider the calculation of the a.c. losses and their distribution. The calculated and measured values are 437 kW and 407 kW.

THE rocket motor is a form of jet propulsion which is characterized by independence of the external atmosphere for combustion, relative independence of altitude and flight velocity upon thrust, small frontal area for high thrusts, simple construction and low weight, and high rate of fuel consumption. Its use was greatly developed during the war years and many applications are now familiar to all. Most of the work on rocket missiles, such as the anti‐aircraft barrages, fighter armament, etc., was performed with solid fuel rockets, but liquid fuels were developed by the Germans for the well‐known V.2, for the Me. 163 aircraft, the Henschel glide bomb and various other applications. They concentrated a great deal of effort on this work and considerable technical progress had been made with different systems. Three main systems emerged and these were distinguished by the oxygen bearing fluids they used. The fluids were: