Safran Helicopter Engines

Turbomeca

Patrick Berteau

Nicolas Savary

Hubert Pascal Verdier

Guy Grienche

Bernard Joseph Jean Pierre Carrere

Lorenzo Huacan Hernandez

Bernard Carrere

Ludovic Andre Joel Naudot

Bernard Joseph Jean-Pierre Carrere

Claude Berat

Jean-Marc Dubourdieu

Ludovic Naudot

Ludovic Andre Naudot

Bernard Joseph Carrere

An annular wall for a combustion chamber of a turbomachine. The wall presents a hot side and a cold side and includes at least one primary hole for enabling a first flow of air flowing on the cold side of the wall to penetrate to the hot side of the wall to feed combustion of fuel inside the combustion chamber, and together with a plurality of cooling holes, each having a diameter no greater than 1 mm, to enable a second flow of air flowing on the cold side of the wall to penetrate to the hot side of the wall to cool the hot side of the wall. The plurality of cooling holes can also dilute combustion gas resulting from the combustion by using the flow of air penetrating to the hot side of the wall through the cooling holes.

Combustion chamber wall

An annular combustion chamber () for a turbomachine (), the combustion chamber presenting an axial direction (X), a radial direction, and an azimuth direction, and comprising a first annular wall () and a second annular wall (), each wall delimiting at least a portion of the volume of the annular combustion chamber (), the first and second walls () presenting complementary fitting elements (), the first wall () presenting at least one first through hole (), while the second wall () presents at least one second through hole (), the combustion chamber () also having at least one pin () engaged in a pair of holes comprising a first hole () and a second hole (), said pin () locking the fitting of the first and second walls ().

Annular turbomachine combustion chamber

A low-cost combustion chamber injector device that has sturdier construction and is safer for use. Parts are configured specifically to be nested, to dispense with welding between the cellular parts. The device for injecting a fuel-air mix includes, centered on a single axis, a swirl chamber including at least two annular air suction parts, a centering guide, and a retainer ring. The annular parts have cellular conduits connecting to axial inner and outer Venturi tubes. The parts are coaxially mounted, the inner part being configured to be self-centered in the outer part by engagement of the axial and radial walls and then, after assembly, the outer part is welded to the retainer ring and to the inner part in a single radial plane.

Injector device and combustion chamber for a turbomachine provided with such injector device

Growing community of inventors

Arbus, France

Patrick Berteau