Snecma

Snecma Moteurs

Michel Pierre Cazalens

Romain Nicolas Lunel

Didier Hippolyte Hernandez

Thomas Olivier Marie Noel

Patrice Andre Commaret

Laurent Bernard Cameriano

Alain Rene Cayre

Matthieu Francois Rullaud

Michel Andre Albert Desaulty

Sylvain Duval

Patrice André Commaret

Olivier Kreder

Frederic Beule

Michel Roger Buret

Thomas Olivier Noel

Michel Andre Desaulty

Thomas Noël

Michel Buret

Michel André Albert Desaulty

An annular combustion chamber for a turbine engine, the chamber including an inner wall and an outer wall forming surfaces of revolution, the walls being connected together by a chamber end wall fitted with a fuel injection mechanism, each of the inner and outer walls including primary holes and dilution holes situated downstream from the primary holes in a gas flow direction, the primary and dilution holes being regularly distributed around the circumference of the inner and outer walls. The outer wall has a greater number of dilution holes than the inner wall.

Turbine engine combustion chamber

A fuel injector for injecting fuel into a turbomachine combustion chamber, the injector presenting an injector nose for connection to an injection system fastened to the end wall of said combustion chamber, the injector nose comprising:

Fuel injector for injecting fuel into a turbomachine combustion chamber

A shroud for a combustion chamber bottom designed to cover fuel injectors is provided with drillings on at least one of its sides to open up the cavity within the shroud and reduce noise that it produces and combustion instabilities. The drillings also have the effect of reducing instabilities and non-uniformity of the airflow around the shroud.

Shroud for a turbomachine combustion chamber

A turbomachine combustion chamber includes an inner annular wall, an outer annular wall surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area, a plurality of fuel injector systems including pilot injectors alternating circumferentially with full-throttle injectors, and at least one air admission opening out into the upstream end of the combustion area in a substantially longitudinal direction. The outer wall has a plurality of pilot cavities extending between the two longitudinal ends of the outer wall and extending radially towards thereof, the pilot cavities being fed with air from outside the combustion chamber in a common substantially circumferential direction. Each pilot injector opens out radially into a pilot cavity, and each full-throttle injector opens out radially between two adjacent pilot cavities.

Turbomachine combustion chamber with helical air flow

The invention relates to a turbomachine combustion chamber having an inner wall, an outer wall surrounding the inner wall so as to co-operate therewith to define a space forming a combustion area, a transverse wall interconnecting the inner and outer walls, and fuel injection systems. The inner wall has a plurality of inner steps each extending radially towards the outside of the inner wall, the circumferential spacing between two adjacent inner steps defining an inner cavity. The outer wall includes a plurality of outer steps each extending radially towards the inside of the outer wall, the circumferential spacing between two adjacent inner steps defining an outer cavity. At least some of the inner and outer cavities are fed with air from outside the combustion chamber in a common direction that is circumferential, and with fuel in a direction that is radial.

A turbomachine assembly comprising: an annular compression section; a casing formed by an outer annular shell () and an inner annular shell () secured inside the outer shell by means of a plurality of radial support arms (); an annular combustion section housed inside the casing; and an annular turbine section. The air coming from the compression section presents rotary motion with an angle of inclination relative to a longitudinal axis (X-X) of the turbomachine, and the combustion section includes angular distribution means for determining air flow direction so as to impart on the gas leaving the combustion section rotary motion with an angle of inclination that is equal to or greater than the angle of inclination of the air leaving the compression section, said angular distribution means being formed by the support arms (), each of which presents an angle of inclination relative to the longitudinal axis (X-X) of the turbomachine that is greater than or equal to the angle of inclination of the air leaving the compression section.

Turbomachine with angular air delivery

A system for injecting an air/fuel mixture into a turbomachine combustion chamber, including a hollow tubular structure for the flow of the air/fuel mixture into the combustion chamber; a fuel injection device placed at an upstream end of the hollow tubular structure, and an air injection device placed downstream of the fuel injection device. The system also includes a cold plasma generator placed downstream of the air injection device so as to generate active species in the flow of the air/fuel mixture and to cause prefragmentation of the molecules of the air/fuel mixture. The system further includes a device for controlling the cold plasma generator depending on the speed of operation of the turbomachine.

Growing community of inventors

Bourron Marlotte, France

Michel Pierre Cazalens