Abstract: A device for injecting air and fuel into a combustion chamber of a turbine engine, the device including a fuel injector, at least one first element mounted on the fuel injector, and at least one second element mounted on an end wall of the combustion chamber. The first element includes a radial rim that is movable in a radial groove of the second element, which groove is defined by a sheath and by a closure ring welded to an inside of the sheath. The closure ring includes a radial wall and a cylindrical rim extending from the radially outer periphery of the radial wall towards a radial wall of the sheath and bearing via its corresponding free end against the radial wall of the sheath.

Abstract: A device for injecting a mixture of air and fuel into a turbine engine combustion chamber, the device including a mechanism for centering a fuel injector, which mechanism is movable radially in a support mechanism fastened to a wall of the chamber, the support mechanism carrying a retaining mechanism for axially retaining the centering mechanism on a side opposite from the chamber wall, the retaining mechanism being fastened in releasable manner to the support mechanism.

Abstract: A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars.

Abstract: An assembly including a diffuser and an airflow rectifier at an outlet of a centrifugal compressor of a turbine engine, the diffuser being substantially in a shape of a radially positioned double annular disc, and the rectifier being a double toroidal part, arranged as an extension of the double disc of the diffuser and curved such as to divert the airflow in the downstream direction of the engine. The rectifier is attached to the diffuser by a connection positioned immediately adjacent to the contact surface of the two parts and is removable using a standard tool, excluding any other supporting mechanism.

Abstract: A fuel injection system for a turbojet engine including a fixed part and a sliding lead-through, the fixed part and the sliding lead-through extending along a reference axis, the fixed part including a cavity that has a bottom and a closure cup, the sliding lead-through being provided with a sole plate contained inside the cavity. The injection system has increased resistance to wearing of the injector on which it is mounted. To achieve this it further includes a spring arranged in such a way as to apply to the sole plate a force capable of preventing the vibration-induced micro-movements of the sliding lead-through with respect to the fixed part in the absence of thermal expansion.

Abstract: A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.

Abstract: A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.

Abstract: A device for injecting air and fuel into a combustion chamber of a turbine engine, the device including a fuel injector, at least one first element mounted on the fuel injector, and at least one second element mounted on an end wall of the combustion chamber. The first element includes a radial rim that is movable in a radial groove of the second element, which groove is defined by a sheath and by a closure ring welded to an inside of the sheath. The closure ring includes a radial wall and a cylindrical rim extending from the radially outer periphery of the radial wall towards a radial wall of the sheath and bearing via its corresponding free end against the radial wall of the sheath.

Abstract: A combustion chamber (110) for a turbine engine, such as an airplane turboprop or turbojet, the combustion chamber comprising two coaxial annular walls, respectively an inner wall and an outer wall, that are connected together at their upstream ends by a chamber end wall (118) having an annular row of openings (119) for mounting fuel injection devices (120), the combustion chamber being characterized in that an annular metal sheet (130) is mounted upstream from the end wall and includes mounting orifices for receiving the above-mentioned injection devices, the sheet being substantially parallel to the end wall and co-operating therewith to define an annular air flow cavity (140).

Abstract: A flame-holder device for an afterburner of a turbofan, the turbofan including a first inner annular casing and a second inner annular casing, these defining a passage for a primary flow, and an outer annular casing defining with the first inner annular casing a passage for a secondary flow, including at least one arm-support made of metallic material configured to be fixed to the outer casing by an upper plate and at least one flame-holder arm of a one-piece structure of composite material including two mutually attached walls arranged to define a groove whose profile is approximately a V. The walls support, on their upper part situated in the secondary flow, a fixing mechanism for fixing to the arm-support. The upper parts are approximately planar and are positioned facing each other.

Abstract: A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the chimney so as to project towards the inside of the chimney, and a bushing forming a spark plug guide and including an inner collar and an outer collar that are axially spaced apart from each other by a cylindrical portion. Each collar extends radially outwards. The bushing is floatingly mounted inside the chimney with its collars axially positioned between the collar of the chimney and the washer. The inner collar comes in operation to bear against the collar of the chimney. The outer collar presents an outside diameter (d1) greater than the inside diameter (d2) of the washer.

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 method for perforating a wall, includes calculating mechanical stresses applied on the wall for a use of the wall. The method further includes perforating an orifice in a first determined zone of the wall, the perforation being made using a tool with a cross-section dependent on the mechanical stresses calculated in the first determined zone.

Abstract: A device for injecting a mixture of air and fuel into a turbine engine combustion chamber, the device including a mechanism for centering a fuel injector, which mechanism is movable radially in a support mechanism fastened to a wall of the chamber, the support mechanism carrying a retaining mechanism for axially retaining the centering mechanism on a side opposite from the chamber wall, the retaining mechanism being fastened in releasable manner to the support mechanism.

Abstract: A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars.

Abstract: A fuel injection system for a turbojet engine including a fixed part and a sliding lead-through, the fixed part and the sliding lead-through extending along a reference axis, the fixed part including a cavity that has a bottom and a closure cup, the sliding lead-through being provided with a sole plate contained inside the cavity. The injection system has increased resistance to wearing of the injector on which it is mounted. To achieve this it further includes a spring arranged in such a way as to apply to the sole plate a force capable of preventing the vibration-induced micro-movements of the sliding lead-through with respect to the fixed part in the absence of thermal expansion.

Abstract: An assembly including a diffuser and an airflow rectifier at an outlet of a centrifugal compressor of a turbine engine, the diffuser being substantially in a shape of a radially positioned double annular disc, and the rectifier being a double toroidal part, arranged as an extension of the double disc of the diffuser and curved such as to divert the airflow in the downstream direction of the engine. The rectifier is attached to the diffuser by a connection positioned immediately adjacent to the contact surface of the two parts and is removable using a standard tool, excluding any other supporting mechanism.

Abstract: A rotationally symmetrical wall for an aircraft turbomachine combustion chamber, including primary holes, dilution holes positioned downstream from the primary holes, and a plug installation aperture upstream from the primary holes, wherein each first primary hole, considered as one moves away circumferentially from the median axial plane (D) in either direction is positioned at a circumferential position between the circumferential positions of the first dilution hole and of the second dilution hole considered as one moves away circumferentially from the median axial plane (D), wherein the other primary holes are distributed equidistantly, at a predefined interval P, and the distance between the two primary holes is greater than the interval P separating two of the other adjacent primary holes.

Abstract: A flame holder for an afterburner duct of a jet engine, including an arm in the form of a gutter forming a cavity, a shield for protecting the cavity of the arm from heat, and an air supply baffle housed in the cavity, is disclosed. The arm, the protective shield, and the air supply baffle are held together by a one-piece spacer shoe.

Abstract: A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.