The present invention relates to a heat exchanger for an aircraft. In particular, the present invention belongs to the field of heat exchangers configured for being mounted at the combustion gases outlet of a power unit of an aircraft. The present inventio...

The present invention relates to an inerting system for an aircraft and a method of inerting a hydrogen system, and in particular to an improved inerting system that reuses the inert gas already supplied to the hydrogen system through a fluid recirculation...

A gas turbine main engine (1) powered by a fuel is disclosed. It comprises a combustion chamber (2) configured to receive fuel through at least one injector (2.1), and a turbopump (3) comprising a pump (3.1), an inlet (3.4) for introducing the fuel in a fi...

The present invention relates to auxiliary power generator systems for an aircraft. More particular, the present invention relates to an auxiliary power system with a new architecture that include an essential auxiliary power unit (APU) with dual and fully...