Abstract: A turbomachine comprising an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage and an annular diffuser (20) comprising: a radially-oriented upstream portion (21)with diffusion passages (22) connected to the outlet of the compressor and an elbow-shaped intermediate portion (24)and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (0) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.

Abstract: A device for injecting an air/fuel mixture into a combustion chamber mounted within a restricted space is disclosed. This injection device includes a bowl having an external cylindrical wall continued at its downstream end by a divergent section provided, downstream, with a collar having the form of a ring extending radially outward. The divergent section of the bowl is connected, immediately upstream of the flange, by a connecting wall to a cylindrical ring. The cylindrical ring and the connecting wall form a connection rim oriented in the upstream direction. At least one row of vortex holes is formed in the external cylindrical wall, close to its upstream end, and the connecting wall of the connection rim of the bowl is provided with a row of cooling orifices inclined axially at an angle ? to the axis of symmetry of the injection device.

Abstract: The invention relates to the field of turbomachines and concerns a combustion chamber (4) for which the dilution supply is optimised. The invention relates more particularly to optimisation of the position of the dilution holes (30a, 30b) present on the walls (7a, 7b) of the combustion chamber.

Abstract: A turbomachine comprising: an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage; and an annular diffuser (20) comprising: a radially-oriented upstream portion (21) with diffusion passages (22) connected to the outlet of the compressor; an elbow-shaped intermediate portion (24); and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (O) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.

Abstract: The invention relates to a device for injecting an air/fuel mixture into a combustion chamber, which is to be mounted within a restricted space. This injection device (20) comprises a bowl (70) having an external cylindrical wall (73) continued at its downstream end by a divergent section (74) provided, downstream, with a collar (75) having the form of a ring extending radially outward, the divergent section of the bowl being connected, immediately upstream of the flange, by a connecting wall (76) to a cylindrical ring (77), the cylindrical ring and the connecting wall forming a connection rim oriented in the upstream direction. At least one row of vortex holes (79) is formed in the external cylindrical wall, close to its upstream end, and the connecting wall of the connection rim of the bowl is provided with a row of cooling orifices (81) inclined axially at an angle y to the axis of symmetry of the injection device.