The present invention relates to a heating system (50) for a cabin (2) of an aircraft (1) comprising an annular heat exchanger (10) positioned around an exhaust duct (21) of a turbine engine (20) and through which circulate a heat transfer fluid (14) and ambient air (25). Said exchanger (10)…

In an exhaust gas heat exchanger system of a combustion engine, having a bypass duct 9 and a heat exchanger duct 5 with a heat exchanger 7, a valve 10 is controlled by a method comprising the following steps: First, it is determined that heat is to be transferred from exhaust gas flowing through…

The construction group includes an induction manifold, an exhaust manifold, a heat exchanger channel (12) and a bypass channel, these channels being in parallel between the induction manifold and the exhaust manifold and sealed to them. The heat exchanger channel contains a sealed-in heat exchanger…