Axially stepped annular combustion chamber for aircraft gas turbine

摘要

The combustion chamber comprising an independent main combustion chamber (5') and an independent pilot combustion chamber (5). The inner boundary walls (6a,6b) of the pilot combustion chamber ensure that the combustion gases thereof enter the main combustion zone in the radial direction. The inner boundary wall (6a) can comprise a deflection section (12) or the outer wall section (6b) can be inclined towards the pilot burner longitudinal axis (3a), such that the cross-section of the pilot burner zone decreases in the direction of flow.