Abstract: An annular turbine engine combustion chamber configured so that in an axial half-section, values of first acute angles formed between a line that is effectively the median of the half-section located between an external axial wall and an internal axial wall, and the principal directions, in this half-section, of the holes in an external portion of a chamber base, decrease as a function of the distance between the holes and this line that is effectively the median. Further, values of second acute angles formed between the line that is effectively the median and the principal directions, in this half-section, of the holes in an internal portion of the chamber base, decrease as a function of the distance between the holes and this line that is effectively the median.

Abstract: The invention applies to the field of turbomachines and relates to a novel device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine. The injection device has symmetry of revolution about an axis (33) and comprises, arranged from upstream to downstream in the gas flow direction, radial swirl inducers (42, 43) of outside diameter D2, a bowl (30) spaced axially from the radial swirl inducers (42, 43), and a support ring (50) for supporting the injection device, which is arranged around the bowl (30). The bowl (30) has a cylindrical wall (32) extended by a flared wall (31), the flared wall (31) being provided with air intake holes (34).

Abstract: The invention relates to the field of combustion chambers for aviation turbomachines. It relates to a combustion chamber having a chamber end wall that presents a plurality of air and fuel injector devices, each of the devices comprising a bowl and a deflector mounted on a main axis forming a heat shield disposed around the bowl which flares in the gas flow direction and possesses an annular portion, the interface between the bowl and the deflector being situated on this annular portion, at least a portion of said interface being situated towards the end of the annular portion that is downstream in the gas flow direction, such that an annular cavity is defined between the deflector and the downstream annular portion of the interface. First bowl holes are formed in the annular portion to open out in register with the edge of the chamber end wall that is in contact with the deflector in order to sustain a flow of air from upstream to downstream in the annular cavity.

Abstract: Device (48) for guiding an element in an orifice in a wall of a turbomachine combustion chamber (10), comprising a ring (50) and a bush (52), the ring being traversed axially by the element and comprising an external annular rim (60) guided transversely in an internal annular channel (52) of the bush, the ring and the bush delimiting around the element a cylindrical annular passage (76) opening into the chamber, air circulation means being formed in the ring and/or in the bush and distributed about their axis so as to establish an air circulation in the cylindrical passage from the outside of the combustion chamber toward the inside.

Abstract: An annular turbine engine combustion chamber configured so that in an axial half-section, values of first acute angles formed between a line that is effectively the median of the half-section located between an external axial wall and an internal axial wall, and the principal directions, in this half-section, of the holes in an external portion of a chamber base, decrease as a function of the distance between the holes and this line that is effectively the median. Further, values of second acute angles formed between the line that is effectively the median and the principal directions, in this half-section, of the holes in an internal portion of the chamber base, decrease as a function of the distance between the holes and this line that is effectively the median.

Abstract: A system for injecting an air/fuel mixture into a combustion chamber of a turbomachine, the system having an injector comprising: an axial internal volume opening out at one end via an axial outlet for the air/fuel mixture; a first fuel feed stage having a plurality of first fuel feed orifices which open out into the internal volume, which are distributed around an axis of the injector, and which are connected by fuel feed channels to an inlet for admitting fuel into the injector; and at least one air feed channel which opens out into the internal volume and which is connected to an inlet for admitting air into the injector. The injector further comprises at least one second fuel feed stage with a plurality of second fuel feed orifices which open out into the internal volume, which are distributed around the axis of the injector, and which are connected to said inlet for admitting fuel into the injector via fuel feed channels which coincide at least in part with the fuel feed channels of said first stage.

Abstract: A system for injecting an air/fuel mixture into a combustion chamber of a turbomachine, the system having an injector comprising: an axial internal volume opening out at one end via an axial outlet for the air/fuel mixture; a first fuel feed stage having a plurality of first fuel feed orifices which open out into the internal volume, which are distributed around an axis of the injector, and which are connected by fuel feed channels to an inlet for admitting fuel into the injector; and at least one air feed channel which opens out into the internal volume and which is connected to an inlet for admitting air into the injector. The injector further comprises at least one second fuel feed stage with a plurality of second fuel feed orifices which open out into the internal volume, which are distributed around the axis of the injector, and which are connected to said inlet for admitting fuel into the injector via fuel feed channels which coincide at least in part with the fuel feed channels of said first stage.

Abstract: A combustion chamber for a gas turbine made up of outer and inner side walls, the combustion chamber being received in a casing so as to define an annular space between the combustion chamber and the casing in which there flows air for combustion, for dilution, and for cooling the combustion chamber, the side walls of the combustion chamber being pierced by a plurality of holes in which bushings of substantially elliptical right section are fixed to define air injection passages for injecting air into the combustion chamber, each bushing having a peripheral wall in which at least one additional orifice is formed opening out into the combustion chamber in the immediate vicinity of the side wall of the combustion chamber in which said bushing is fixed so that the air passing through said orifice flows substantially along said peripheral wall, the peripheral wall of each bushing having at least one groove opening out into the annular space and into which the or each orifice opens out so as to be fed with air and

Abstract: A combustion chamber is disclosed for a turbojet engine in which the combustion chamber has a forward intake, a rear exit and a perforated casing extending between the intake and exit. The combustion chamber also has at least two rows of insulating tiles arrayed on the casing in forward and rear rows with both rows extending circumferentially around the inner surface of the casing bounding the combustion chamber. Each rear tile has a forward edge portion with a sloping wall and each forward tile has a tapered rear edge portion overlapping the forward edge portion with a clearance therebetween such that the tampered rear edge portion and the sloping wall bound a slot opening into the combustion chamber and slanting towards the rear of the combustion chamber to facilitate the formation of an air cooling film on inner surfaces of the tiles.

Abstract: A combustion chamber is disclosed for a gas turbine engine having a feeder owl interposed between the forward end wall of the combustion chamber and an associated air and fuel injection device, the feeder bowl having a generally annular configuration with spaced apart outer and inner walls forming a chamber. A baffle is formed integrally with the feeder bowl and extends outwardly from a merging zone in a direction generally parallel to the forward end wall of the combustion chamber. The outer wall of the feeder bowl has a plurality of air intake orifices communicating with the chamber and located adjacent to the merging zone. The inner wall of the feeder bowl has a plurality of first and second air outlet orifices, both communicating with the chamber and the second air outlet orifices being spaced from the first air outlet orifices.

Abstract: A pre-mixing injection system to feed a fuel/air mixture to a combustion zone in a turbojet engine combustion chamber is disclosed having a pre-mixing tube defining a convergent pre-mixing zone and a diverging intermediate zone between the fuel and air injection devices, and the combustion zone of the combustion chamber. The convergent pre-mixing zone has an inlet adjacent to the fuel injector and air swirlers to accept the fuel/air mixture into the pre-mixing tube. The pre-mixing zone converges in a direction from the inlet to an outlet which is in communication with the inlet of the divergent intermediate zone. The divergent intermediate zone has an outlet which is, in turn, in communication with the combustion zone of the turbojet engine combustion chamber. The divergent intermediate zone is defined by an inner wall and an outer wall spaced from the inner wall so as to define a generally frusto-conical chamber between them.

Abstract: The present invention relates to a system for cooling a high power fuel injector of a dual fuel injector wherein the system comprises a first fuel supply circuit having a first conduit connecting a fuel feed supply and the high power fuel injector, the first conduit having a terminal end adjacent to a distal end of the high power fuel injector, and a second conduit connecting the terminal end of the first conduit to the low power fuel injector such that all of the fuel supplied to the low power injector first passes through the high power fuel injector. The system also has a second fuel supply circuit, separate from the first fuel supply circuit, which comprises a third conduit connecting the fuel feed supply and the fuel injection orifices of the high power fuel injector so as to supply fuel to the fuel injection orifices.