Safran Aircraft Engines

Snecma

Sebastien Alain Christophe Bourgois

Romain Nicolas Lunel

Didier Hippolyte Hernandez

Denis Jean Maurice Sandelis

Thomas Olivier Marie Noel

Clement Bernard

Sebastien Loval

Jean-Michel Jacques Campion

Jean-Francois Cabre

Joel Yvan Marcel Robert Berton

Frederic Dos Santos

A combustion chamber for a turbomachine that includes a chamber end wall and a plurality of air and fuel injection systems distributed circumferentially about an axis of the combustion chamber. The combustion chamber includes, associated with each injection system, a guide device for guiding an airflow including at least one wall mounted on the injection system and projecting in the upstream direction, one wall acting as an obstacle to a circumferential flow of air around the axis. The one wall of the guide device for guiding the airflow has a shape substantially defining a quarter of a spheroid the interior volume of which forms a guide scoop for guiding the airflow feeding the combustion chamber.

Turbomachine combustion chamber comprising an airflow guide device of specific shape

An igniter plug for an aircraft turbomachine includes an external electrode, an internal electrode, as well as a semiconducting body arranged between the external electrode and the internal electrode and set back from these electrodes so as to define an electrical arc forming cavity, the bottom of which is formed by an axial end surface of the semiconducting body. The free end of the external electrode is equipped with at least one scoop for discharging possible fuel residues present in the cavity.

Semiconductor igniter plug for an aircraft turbomachine, comprising scoops for discharging possible fuel residues

A combustion chamber module for an aircraft turbomachine, including an annular combustion chamber in which each of primary and dilution ports of an outer annular wall, which is located at least partly in a wake of a fuel injector, has a discharge coefficient higher than that of its homologous port of an inner annular wall. A method for designing such a module includes determining wakes generated by fuel injectors, and then geometrically defining air inlet ports of coaxial walls of the combustion chamber such that an air flow rate actually entering through ports of the outer wall is substantially equal to an air flow rate entering through ports of the inner wall.

Aircraft turbomachine combustion chamber module and method for designing same

An annular combustion chamber of a turbine engine, the chamber including inner and outer coaxial walls forming two surfaces of revolution, which are connected together upstream by an annular chamber end wall including injection systems passing therethrough, each including an injector and at least one swirler for producing a rotating air stream that mixes downstream with fuel from the injector, and at least one ignition spark plug mounted in an orifice of the outer wall downstream from the injection systems. The spark plug is situated circumferentially between two adjacent injection systems that are configured to produce two air/fuel mixture sheets rotating in opposite directions.

Annular combustion chamber in a turbine engine

Annular combustion chamber () to be fitted on a turbomachine and comprising a chamber end wall (), a plurality of air and fuel injection systems () circumferentially distributed around an axis () of the combustion chamber () and mounted on said chamber end wall (), and, an air manifold () associated with each injection system (), comprising at least one wall () mounted on the chamber end wall () and projecting in the upstream direction to form an obstacle to a circumferential airflow around the axis () of the combustion chamber (), and an air inlet opening () formed at the upstream end of the air manifold () and opening radially outwards from an axis () of said injection system.

Turbomachine combustion chamber comprising improved means of air supply

An annular shroud (), having an internal face intended to cover the back end wall () of an annular combustion chamber () of a turbomachine () fitted with a centrifugal compressor, together with an external face opposite said internal face, and where said shroud includes multiple apertures () intended to allow fuel injectors () supported by said back end wall () to pass through, together with multiple bosses () which extend as projections on said external face radially towards the interior respectively from the respective radially internal edges () of said apertures (), such that each of said bosses () delimits an extension () of the corresponding aperture () open radially towards the exterior so as to form an air intake scoop.

Growing community of inventors

Saint Germain Les Corbeil, France

Sebastien Alain Christophe Bourgois