Annular deflection wall for a turbomachine combustion chamber injection system providing a wide fuel atomization zone

Abstract

A deflection wall known as <<venturi>> is disclosed to improve the air fuel mix within an injection system installed in a turbomachine combustion chamber, having a downstream edge formed by the repetition of a pattern extending on each side of a virtual circle and formed from a plurality of bosses each of which is centred relative to a corresponding plane inclined by an angle α from a corresponding median axial plane of the annular deflection wall passing through a corresponding end of the downstream edge of the annular deflection wall at the boss considered.

1 . An annular deflection wall for a turbomachine combustion chamber injection system centred on a longitudinal axis and having a free downstream edge, said annular deflection wall comprising a plurality of first bosses projecting radially outwards and a plurality of second bosses projecting radially inwards and arranged alternately with said first bosses, such that the downstream edge of the annular deflection wall, that is formed from a set of downstream ends from said first and second bosses respectively, forms an undulation about a virtual circle, said downstream edge being thus formed by the repetition of a pattern extending on each side of the virtual circle, wherein each of said first and second bosses is centred relative to a corresponding plane inclined by an angle α from a corresponding median axial plane of the annular deflection wall passing through a corresponding extremum of the downstream edge of the annular deflection wall at the boss considered. 
     
     
         2 . The annular deflection wall according to  claim 1 , wherein said virtual circle is inscribed inside a virtual extension of a portion of revolution of the annular deflection wall. 
     
     
         3 . The annular deflection wall according to  claim 1 , in which the downstream edge of the annular deflection wall is inscribed in a transverse plane orthogonal to the longitudinal axis of the annular deflection wall. 
     
     
         4 . An annular air inlet for an injection system of a combustion chamber of a turbomachine, comprising an annular separation wall that divides the annular air inlet into an upstream air circulation space and a downstream air circulation space and that is prolonged radially inwards by an annular deflection wall according to  claim 1 . 
     
     
         5 . A turbomachine, particularly for an aircraft, comprising at least one combustion chamber comprising at least one injection system comprising an annular air inlet according to  claim 4 .