Snecma

Safran Aircraft Engines

Snecma Moteurs

Patrice Andre Commaret

Didier Hippolyte Hernandez

Romain Nicolas Lunel

David Locatelli

Denis Jean Maurice Sandelis

Mario Cesar De Sousa

Michel Andre Albert Desaulty

Pascale Rollet

Jacques Marcel Arthur Bunel

Thomas Olivier Marie Noel

Antoine Robert Alain Brunet

Denis Gabriel Trahot

Sylvain Duval

Florian Andre Francois Bessagnet

Yann Francois Jean-Claude Vuillemenot

Dominique Guezengar

Jean-Michel Serge Marcel Duret

An annular turbine engine combustion chamber wall including air admission orifices to create zones of steep temperature gradient, and cooling orifices to enable the air flowing on the cold side to penetrate to the hot side in order to form a film of cooling air along the annular wall, the annular wall being further includes, in the zones of steep temperature gradient, multi-perforation holes having respective bends of an angle &#x3b1; greater than 90&#xb0;, the angle &#x3b1; being measured between an inlet axis Ae and an outlet axis As of the multi-perforation hole, the outlet axis of the multi-perforation hole being inclined at an angle &#x3b8;relative to the normal N to the annular wall through which the multi-perforation holes with bends are formed, in a 'gyration' direction that is at most perpendicular to the axial flow direction D of the combustion gas.

Annular wall of a combustion chamber with optimised cooling

A combustion chamber for an aviation turbine engine, the combustion chamber being annular about a longitudinal axis and including an outer side wall, an inner side wall, and an annular chamber end wall connecting one end of the outer side wall to one end of the inner side wall. The outer side wall includes, distributed along its circumference, spark plugs, primary holes, and dilution holes situated downstream from the primary holes in the direction of the longitudinal axis. The primary holes situated in each of the adjacent zones adjacent to one of the spark plugs present a configuration that is different from the configuration of the primary holes situated outside the zones, such that the supply of air in the adjacent zones is different from the supply of air outside the zones.

Combustion chamber of an aeronautical turbine engine with combustion holes having different configurations

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.

Diffuser for turbine engine including indented annular webs

A baffle for the bottom of a combustion chamber of a gas turbine engine is disclosed. The baffle includes a flat portion of wall with an opening for an injector of the combustion chamber to pass through, two longitudinal edges for the assembly to two adjacent baffles and two transverse edges. At least one of the edges includes a joint cover arranging a housing along the edge for an edge of an adjacent baffle so as to seal the junction between the two edges. A combustion chamber incorporating the baffles is also disclosed.

Chamber-bottom baffle, combustion chamber comprising same and gas turbine engine fitted therewith

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.

Annular combustion chamber for a gas turbine engine

An annular combustion chamber for a turbomachine is disclosed. The chamber includes an inner wall, an outer wall, and a chamber end wall disposed between the inner and outer walls in the upstream region of the chamber. The chamber end wall presents an outer fastener rim and/or an inner fastener rim, and the outer and/or inner wall presents a respective upstream fastener rim. The chamber end wall and the outer and/or inner wall are fastened together via their fastener rims. Cooling channels are made between the fastener rims and open out to the inside of the combustion chamber. Advantageously, a spacer is placed between the fastener rims, and the channels are formed in the thickness or in the sides of the spacer.

Annular combustion chamber for a turbomachine

A turbomachine including an annular combustion chamber, a centrifugal compressor, an annular diffuser enabling the flow of gas leaving the compressor to be diffused and directing this flow of gas towards the combustion chamber, and an outer casing surrounding the outside of the combustion chamber is disclosed. The diffuser includes an upstream portion oriented radially and presenting diffusion passages connected to the outlet from the compressor, an intermediate portion that is elbow-shaped, and a downstream portion having a series of circularly spaced-apart flow-straightening vanes. The flow stream in the downstream portion is delimited externally by the outer casing. The outer casing presents a shoulder against which the outer downstream edge of the intermediate portion comes into abutment.

Turbomachine with a diffuser

A turbomachine comprising an annular combustion chamber () with injection orifices (); a centrifugal compressor () having a centrifugal downstream stage and an annular diffuser () comprising: a radially-oriented upstream portion ()with diffusion passages () connected to the outlet of the compressor and an elbow-shaped intermediate portion ()and a downstream portion () comprising a series of flow-straightening vanes () 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 (), the curvilinear abscissa distance along a flow line (L) between the middle (0) of the flow path at the trailing edges of the flow-straightening vanes () and said center (C) is greater than or equal to three times the height (h) of said flow path.

Turbomachine diffuser

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.

Deflector for a combustion chamber endwall, combustion chamber equipped therewith and turbine engine comprising them

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.

Device for attaching a combustion chamber

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.

Annular turbomachine combustion chamber

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.

Combustion chamber in a turbomachine

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.

System for ventilating a combustion chamber wall

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 &#x3b3; to the axis of symmetry of the injection device.

Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device

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.

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Rubelles, France

Patrice Andre Commaret