Abstract: A device for starting a gas turbine in an aircraft includes an electrical power supply delivering a direct current and a drive electric motor connected to the power supply, independent of the turbine to be started and having an output shaft mechanically coupled to an input shaft of the turbine to rotate with it. The drive electric motor is a three-phase alternating current synchronous motor and is controlled by an inverter connected to the power supply. Applications include situations in which the turbine to be driven is a high-power turbine.

Abstract: A hydrocarbon hydroconversion catalyst is regenerated by (a) combustion, (b) chlorination or oxychlorination and (c) treatment with an oxygen-containing gas, and the gas discharged from the regeneration zone, before re-use, is (a) cooled down to below 70.degree. C., (b) subjected to double washing and (c) dried to reduce the water content of the gas to less than 2,500 ppm. An apparatus is also disclosed, certain parts of which are made of a material strongly resistant chlorine and other parts of a less resistant material with respect thereto.