AIRCRAFT ENGINE COMPRISING AZIMUTH SETTING OF THE DIFFUSER WITH RESPECT TO THE COMBUSTION CHAMBER

摘要

The fixed vanes of a diffuser are set to an azimuth angle setting (α) with respect to the injectors of a combustion chamber so that the paths leading from the trailing edges pass through the gaps between injectors and more preferably mid-way between same, so that these portions of the flow, which may contain condensed water, do not affect the initiation of the combustion.

主权项

1. An aircraft engine comprising a gas flow duct, a combustion chamber located on the flow duct and a diffuser also located on the flow duct upstream of the combustion chamber, with this diffuser being comprised of fixed vanes provided with an inclination in an angular direction of the engine along an axial direction of the engine, thus provided with an intrados altering the flow and arranged in a circle, with the combustion chamber comprising fuel injectors arranged in a circle coaxial to the circle of the vanes, wherein the vanes are arranged angularly with respect to the injectors in such a way that paths of the flow, coming from the trailing edges of the vanes and of the same angular inclination to said trailing edges, tangent to the intrados of the vanes, end between the injectors.