Abstract: An injector for a gas turbine combustion chamber, includes a fluid feed system; an injector body extending along a longitudinal axis; an injection head arranged on the injector body and configured to spray the fluid in a direction that is inclined relative to the longitudinal axis; and an actuator configured to turn the injector selectively about the longitudinal axis so as to vary the direction in which the fluid is sprayed; wherein the actuator is configured to enable the orientation of the injector to be varied by turning about the longitudinal axis through an amplitude less than or equal to 90°.

Abstract: An injector for a gas turbine combustion chamber, includes a fluid feed system; an injector body extending along a longitudinal axis; an injection head arranged on the injector body and configured to spray the fluid in a direction that is inclined relative to the longitudinal axis; and an actuator configured to turn the injector selectively about the longitudinal axis so as to vary the direction in which the fluid is sprayed; wherein the actuator is configured to enable the orientation of the injector to be varied by turning about the longitudinal axis through an amplitude less than or equal to 90°.

Abstract: An annular wall for a combustion chamber of a turbomachine. The wall presents a hot side and a cold side and includes at least one primary hole for enabling a first flow of air flowing on the cold side of the wall to penetrate to the hot side of the wall to feed combustion of fuel inside the combustion chamber, and together with a plurality of cooling holes, each having a diameter no greater than 1 mm, to enable a second flow of air flowing on the cold side of the wall to penetrate to the hot side of the wall to cool the hot side of the wall. The plurality of cooling holes can also dilute combustion gas resulting from the combustion by using the flow of air penetrating to the hot side of the wall through the cooling holes.

Abstract: An annular combustion chamber (10) for a turbomachine (100), the combustion chamber presenting an axial direction (X), a radial direction, and an azimuth direction, and comprising a first annular wall (12) and a second annular wall (14), each wall delimiting at least a portion of the volume of the annular combustion chamber (10), the first and second walls (12, 14) presenting complementary fitting elements (12d, 14d), the first wall (12) presenting at least one first through hole (12f), while the second wall (14) presents at least one second through hole (14f), the combustion chamber (10) also having at least one pin (18) engaged in a pair of holes comprising a first hole (12f) and a second hole (14f), said pin (18) locking the fitting of the first and second walls (12, 14).

Abstract: A combustion chamber of a turbine engine, including at least one wall defining the combustion chamber and including an aperture for enabling a through-part to pass therethrough. The through-part includes, in the portion thereof located within the combustion chamber, at least one opening able to create an air film to cool the area downstream of the through-part.

Abstract: The invention relates to a turbine engine combustion assembly (20), which includes: an annular flame tube (21) including a front wall (23), a rear wall (24) and a bottom (22) arranged facing an engine shaft (30); an injection wheel (41) rotated by said engine shaft (30), partially projecting into the bottom (22) of the flame tube (21) and configured such as to spray fuel into the flame tube by centrifugation; and at least one injector (35), capable of depositing a film of fuel on said injection wheel (41), said combustion assembly being characterised in that said injector (35) is arranged so as to pass through said upstream area of the front wall (23) or the rear wall (24) of the flame tube (21), so that the injection opening thereof (37) opens into said tube (21), opposite the portion (43) of said injection wheel (41) which is located inside said flame tube (21).

Abstract: An air/fuel mixer system of a combustion chamber of a gas turbine includes at least one compressed air intake swirler, the swirler having a central axis of symmetry, and a fuel injector including an injection head having an axis of symmetry. Each injector is mounted in the corresponding swirler with aid of a guide mechanism, so that the axis of symmetry of the injection head is off-center with respect to the central axis of symmetry of the swirler. The system can reduce, or even eliminate, combustion instabilities, by injecting the fuel along a particular axis which is off-center relative to the axis of the air/fuel mixer system, inducing a flow of fuel which is no longer perfectly axially symmetrical.

Abstract: An annular combustion chamber (10) for a turbomachine (100), the combustion chamber presenting an axial direction (X), a radial direction, and an azimuth direction, and comprising a first annular wall (12) and a second annular wall (14), each wall delimiting at least a portion of the volume of the annular combustion chamber (10), the first and second walls (12, 14) presenting complementary fitting elements (12d, 14d), the first wall (12) presenting at least one first through hole (12f), while the second wall (14) presents at least one second through hole (14f), the combustion chamber (10) also having at least one pin (18) engaged in a pair of holes comprising a first hole (12f) and a second hole (14f), said pin (18) locking the fitting of the first and second walls (12, 14).

Abstract: An annular combustion chamber for a turbomachine presenting an axial direction, a radial direction, and an azimuth direction, the combustion chamber including a first annular wall and a second annular wall, each annular wall defining at least a portion of an enclosure of the combustion chamber. The first annular wall and the second annular wall present complementary assembly mechanisms that co-operate by engagement in azimuth.

Abstract: An annular wall for a combustion chamber of a turbomachine. The wall presents a hot side and a cold side and includes at least one primary hole for enabling a first flow of air flowing on the cold side of the wall to penetrate to the hot side of the wall to feed combustion of fuel inside the combustion chamber, and together with a plurality of cooling holes, each having a diameter no greater than 1 mm, to enable a second flow of air flowing on the cold side of the wall to penetrate to the hot side of the wall to cool the hot side of the wall. The plurality of cooling holes can also dilute combustion gas resulting from the combustion by using the flow of air penetrating to the hot side of the wall through the cooling holes.

Abstract: An air/fuel mixer system of a combustion chamber of a gas turbine includes at least one compressed air intake swirler, the swirler having a central axis of symmetry, and a fuel injector including an injection head having an axis of symmetry. Each injector is mounted in the corresponding swirler with aid of a guide mechanism, so that the axis of symmetry of the injection head is off-center with respect to the central axis of symmetry of the swirler. The system can reduce, or even eliminate, combustion instabilities, by injecting the fuel along a particular axis which is off-center relative to the axis of the air/fuel mixer system, inducing a flow of fuel which is no longer perfectly axially symmetrical.

Abstract: An annular combustion chamber for a turbomachine presenting an axial direction, a radial direction, and an azimuth direction, the combustion chamber including a first annular wall and a second annular wall, each annular wall defining at least a portion of an enclosure of the combustion chamber. The first annular wall and the second annular wall present complementary assembly mechanisms that co-operate by engagement in azimuth.