Abstract: The invention relates to a device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine where the supply of air is improved. The invention relates more particularly to a new type of sliding bushing.

Abstract: The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several passages (34,36,72) enabling initiation of a cooling air film (D2) along the hot inner surface (30) of the outer axial wall and initiation of a cooling air film (D1) along the hot inner surface (32) of the inner axial wall, the outer axial wall and the inner axial wall being multi-perforated roughly over their full length in order to enable reinforcement of the cooling air films. According to the invention, the outer axial wall and the inner axial wall are provided, in an upstream part, with a first zone (54,40) of perforations (38) formed such that cooling air is introduced inside the combustion chamber in reverse flow.

Abstract: A shroud for a combustion chamber bottom designed to cover fuel injectors is provided with drillings (21) on at least one of its sides to open up the cavity within the shroud and reduce noise that it produces and combustion instabilities. The drillings also have the effect of reducing instabilities and non-uniformity of the airflow around the shroud.

Abstract: The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several passages (34,36,72) enabling initiation of a cooling air film (D2) along the hot inner surface (30) of the outer axial wall and initiation of a cooling air film (D1) along the hot inner surface (32) of the inner axial wall, the outer axial wall and the inner axial wall being multi-perforated roughly over their full length in order to enable reinforcement of the cooling air films. According to the invention, the outer axial wall and the inner axial wall are provided, in an upstream part, with a first zone (54,40) of perforations (38) formed such that cooling air is introduced inside the combustion chamber in reverse flow.

Abstract: A diffuser for a turbojet engine is disclosed in which a plurality of diffuser inlets are arranged in a substantially circular array bounded by inner and outer diffuser walls and by a plurality of partitions extending generally radially from the axis of the annular diffuser. The plurality of diffuser inlets are located so as to receive air or oxidizer from the turbojet engine compressor and the radial partitions may be integrated into the compressor guide vanes. The diffuser has a plurality of sets of diffuser outlets, each set comprising a plurality of diffuser outlets arranged in a circular array about the central axis of the diffuser. The radius of each set of diffuser outlets is different from the radius of each of the other sets of diffuser outlets such that the entirety of diffuser outlets comprise a non-circular array.