Abstract: An annular wall for an annular turbine engine combustion chamber, including one annular row of dilution orifices including larger area orifices and smaller area orifices, and a multi-perforation formed from micro-perforations distributed as an upstream row, a downstream row, and at least one intermediate row interrupted by the orifices, a geometric ratio being defined as the quotient obtained by dividing the maximum spacing L between any two points on the edge of the orifice measured along a direction parallel to an axis of the wall by the maximum spacing l between any two points on the edge of this orifice measured along a direction perpendicular to the axis, the geometric ratio of the larger area orifices being greater than or equal to 1, and the geometric ratio of the smaller area orifices being greater than the geometric ratio of the larger area orifices.

Abstract: A turbomachine combustion chamber including at least one ignition plug carried by an outer casing and extending within guide means carried by a wall of the chamber, the wall forming a body of revolution. The guide means includes a tubular guide having the plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber, the guide extending at least in part in an air flow stream outside the chamber. The guide means includes a deflector surrounding the portion of the guide that is situated in the air flow stream so as to reduce the aerodynamic pressure on the guide and reduce the contact pressure of the guide on the plug.

Abstract: An annular wall for an annular turbine engine combustion chamber, including one annular row of dilution orifices including larger area orifices and smaller area orifices, and a multi-perforation formed from micro-perforations distributed as an upstream row, a downstream row, and at least one intermediate row interrupted by the orifices, a geometric ratio being defined as the quotient obtained by dividing the maximum spacing L between any two points on the edge of the orifice measured along a direction parallel to an axis of the wall by the maximum spacing 1 between any two points on the edge of this orifice measured along a direction perpendicular to the axis, the geometric ratio of the larger area orifices being greater than or equal to 1, and the geometric ratio of the smaller area orifices being greater than the geometric ratio of the larger area orifices.

Abstract: A turbomachine including a combustion chamber provided with systems for injecting fuel into the chamber, and with at least one spark plug is disclosed. The injection system located as close as possible to the spark plug is configured in order to produce a pool of fuel having an angle of opening of a greater value than that of the pools produced by the other injection systems, and having a flow of fuel greater than that of the other injection systems.

Abstract: An afterburner chamber includes a burner ring having housed therein an annular fuel strip that is pierced by orifices and that is mounted inside an annular thermal protection tube, and an ignition spark plug penetrating into the inside of the burner ring. The protection tube and the burner ring have orifices for passing air. The chamber also includes a device for ventilating the orifices of the fuel strip that are situated in the immediate vicinity of the spark plug.

Abstract: The invention relates to a turbomachine combustion chamber including at least one ignition plug carried by an outer casing and extending within guide means carried by a wall of the chamber, said wall forming a body of revolution, and including a tubular guide having the plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber, the guide extending at least in part in an air flow stream outside the chamber. The guide means comprise a deflector surrounding the portion of the guide that is situated in the air flow stream so as to reduce the aerodynamic pressure on the guide and reduce the contact pressure of the guide on the plug.

Abstract: The invention relates to a turbomachine combustion chamber including at least one ignition spark plug carried by an outer casing and extending in guide means carried by a wall of the chamber, the wall forming a body of revolution, the guide means comprising a tubular guide having the spark plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber. In order to reduce wear of the spark plug in operation, the spark plug is mounted by being fastened in a sheath, the tubular guide being slidably mounted around the sheath.

Abstract: Turbomachine, comprising a combustion chamber provided with systems (132, 132?) for injecting fuel into the chamber, and with at least one spark plug (144), the injection system (132) located as close as possible to the spark plug being configured in order to produce a pool (166) of fuel having an angle of opening (?) of a greater value than that (?) of the pools (166?) produced by the other injection systems (132?), and having a flow of fuel greater than that of the other injection systems (132?).

Abstract: An afterburner chamber (10) comprising a burner ring (64) having housed therein an annular fuel strip (28) that is pierced by orifices (32, 34) and that is mounted inside an annular thermal protection tube (56), and an ignition spark plug penetrating into the inside of the burner ring (64), the protection tube (56) and the burner ring (64) having orifices (46, 47) for passing air, the chamber also including means for ventilating the orifices (32, 34) of the fuel strip that are situated in the immediate vicinity of the spark plug.