Abstract: A deflector takes the form of a plate provided with a hole. The plate is a portion of a conical surface of revolution about a cone axis with a concave face and a convex face. The plate includes a contour with four sides. Two of these the sides are concentric circular arcs centered on the cone axis. The other two sides are segments of generatrices of the cone which connect the first sides. The invention is applicable to a deflector of a chamber endwall of a combustion chamber of a turbine engine.

Abstract: A turbomachine including an annular combustion chamber is disclosed. The combustion chamber includes a radially inner wall and a radially outer wall exhibiting symmetry of revolution. An annular chamber end wall equipped with a fuel injection device connects upstream ends of the inner and outer walls. A suspension device suspends the upstream end of the combustion chamber from an outer casing.

Abstract: An annular turbomachine combustion chamber comprising an inner wall, an outer wall, and a chamber end wall disposed between said inner and outer walls in the upstream region of said chamber, the chamber end wall presenting a central portion and an outer assembly flange, and the outer wall presenting an upstream assembly flange, the chamber end wall and the outer wall being assembled together by their assembly flanges, in which the free edge of said outer assembly flange is curved inwards. In addition, the outer face of the outer assembly flange presents a shoulder.

Abstract: A turbomachine combustion chamber has primary and dilution air inlet orifices formed by die stamping to have edges that project into the inside of the combustion chamber, and stress relaxation and/or reduction means in the edges or in the vicinity of the edges of said orifices, said means comprising, for each orifice, one, two, or three slots formed in the edge or around a fraction of the edge of said orifice.

Abstract: A system for ventilating a combustion chamber wall in a turbomachine is disclosed. The system includes a centrifugal compressor, a diffuser, a combustion chamber, and an annular case arranged radially between the combustion chamber and a downstream end-piece of the diffuser. The annular case includes a radially external wall for the guidance of an air flow coming out of the diffuser, and a radially internal wall delimiting with the end-piece of the diffuser a channel for the air coming out of the diffuser to pass through.

Abstract: An annular combustion chamber for a gas turbine engine includes radially inner and outer walls connected together by a chamber end wall including openings, each of which receives a fuel injection system. Heat protection deflectors are fastened to the chamber end wall. Holes are formed through the chamber end wall to pass cooling air onto an upstream face of each deflector. The inner or outer edge of a deflector presents a sealing rim engaging the respective inner or outer wall of the chamber.

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: A diffuser for a turbine engine that includes two annular webs extending inside one another and connected between them by substantially radial vanes, wherein the downstream peripheral edge of at least one of the webs includes indentions evenly distributed about the longitudinal axis of the diffuser.

Abstract: A combustion chamber of a turbomachine is disclosed. The combustion chamber includes at least one bowl with a substantially frustoconical wall that is formed with an annular row of air injection orifices and a fuel injector arranged upstream of the bowl. The annular row of air injection orifices includes smaller-diameter orifices and larger-diameter orifices which are arranged in alternating fashion and with a uniform distribution around the axis of the bowl to produce two annular air/fuel mixture layers.

Abstract: An injection device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine is disclosed. The injection device includes two fuel circuits and a Venturi which improves the carburation.

Abstract: A system for ventilating a combustion chamber wall in a turbomachine is disclosed. The system includes a diffuser mounted at the inlet of the combustion chamber, an annular end-piece that extends downstream to an injection device for injecting ventilation air, and an annular convecting metal sheet being arranged radially between the combustion chamber and the end-piece of the diffuser in order to delimit, with an internal wall of the chamber, an annular stream for the flow of air that is stable and without separation supplying holes in the chamber and the injection device.

Abstract: A gas turbine engine diffuser defined between an external casing and an internal casing of the engine and supplied with air via an upstream annular diffuser duct is disclosed. The diffuser includes a combustion chamber of the convergent type, forming an external annular duct with the external casing and an internal annular duct with the internal casing, and a cowling partially closing off the external annular duct. The cowling is positioned toward the closed end of the combustion chamber.

Abstract: A device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine is disclosed. The injection device has symmetry of revolution about an axis and includes radial swirl inducers of outside diameter D2, a bowl spaced axially from the radial swirl inducers, and a support ring for supporting the injection device, which is arranged around the bowl. The bowl has a cylindrical wall extended by a flared wall, the flared wall being provided with air intake holes. The support ring includes a first cylindrical portion of outside diameter D3, connected to a second cylindrical portion of outside diameter D4 spaced axially from the first cylindrical portion, the first cylindrical portion being connected to the cylindrical wall of the bowl by a plurality of support tabs.

Abstract: Turbomachine comprising an annular combustion chamber (48) comprising two, a radially inner (24) and a radially outer (26), walls exhibiting symmetry of revolution, which are connected at their upstream ends by an annular chamber end wall (28) equipped with fuel-injection means, which turbomachine comprises suspension means (50) for suspending the upstream end of the combustion chamber (48) from an outer casing (18).

Abstract: Turbomachine with an annular combustion chamber including at its upstream end an annular chamber bottom, and attached at its downstream end by annular flanges to a radially inner casing and outer casing, wherein the upstream end of the chamber is connected to the inner casing or outer casing by elastically deformable bridges.

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: The invention applies to the field of turbomachines and relates to a combustion chamber in which the supply of dilution air and cooling air is optimized. The invention is concerned more particularly with optimizing the position of the dilution holes present on the walls of the combustion chamber.

Abstract: Turbomachine with an annular combustion chamber (46) comprising at its upstream end an annular chamber bottom (28), and attached at its downstream end by annular flanges (24, 26) to a radially inner casing (14) and outer casing (18), wherein the upstream end of the chamber (46) is connected to the inner casing (14) or outer casing (18) by elastically deformable means (48, 49) of variable stiffness.

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 present invention relates to a baffle (10) for the bottom of a combustion chamber of a gas turbine engine, comprising a flat portion of wall (10a) with an opening for an injector of the combustion chamber to pass through, two longitudinal edges (10c, 10d) for the assembly to two adjacent baffles and two transverse edges (10e, 10f), wherein at least one of the edges comprises a joint cover (10d1) arranging a housing (10d10) along said edge for an edge (10?c) of an adjacent baffle (10?) so as to seal the junction between the two edges. The invention also relates to a combustion chamber incorporating said baffles.