Gas turbine engine for aircraft, has annular air manifold comprising wall with openings through which air is entered in manifold, where manifold is arranged between annular air diffuser and combustion chamber

摘要

The engine has an annular combustion chamber supplied with combustion air by an annular air diffuser (17), and an air sampling opening (13a) arranged in a casing (13). An annular air manifold (C) is arranged between the diffuser and the combustion chamber. The manifold has a wall (20) with openings (21) through which air is entered in the manifold, where the wall is formed from an annular sheet. The sheet has a concavity turned towards a bypass channel of the chamber in passage zones of fuel injection ducts.