Safran Helicopter Engines

Turbomeca

Olivier Lamaison

Nicolas Roland Guy Savary

Hubert Pascal Verdier

Nicolas Savary

Stéphane Lavignotte

Guillaume Taliercio

Yvan Ludovic Lameignere

Denis Luc Alain Chanteloup

Jean Marc Dubourdieu

Christian Vally

Chritophe Nicolas Henri Viguier

Claude Marie Michel Berat

Christophe Lailhacar

A combustion assembly for a gas turbine includes a flame tube and a fuel supply including a flow rate limiter supplying an injector. The flow rate limiter and the fuel injector are formed in one piece.

Integral flow rate limiter and fuel injector for a gas turbine combustor

The invention relates to a pre-vaporizing pipe () for a combustion chamber of a turbomachine, comprising a generally elongate main body (), comprising a first end portion () delimiting an inlet duct () in which a fuel injector is to be mounted, the body () having an external surface () having a first length (L) that extends from the portion () to at least one first fuel outlet end piece (), and a second length (L) that extends the first length (L) from the end piece () and that extends from the end piece () to a second fuel outlet end piece (). According to the invention, inside the body () there is a first channel () connecting the duct () to the end piece () and a second channel () which is distinct from the first channel () and which connects the duct () to the end piece ().

Pre-vaporizing pipe, combustion assembly provided therewith and turbomachine provided therewith

An injector for a gas turbine combustion chamber, includes a fluid feed system; an injector body extending along a longitudinal axis; an injection head arranged on the injector body and configured to spray the fluid in a direction that is inclined relative to the longitudinal axis; and an actuator configured to turn the injector selectively about the longitudinal axis so as to vary the direction in which the fluid is sprayed; wherein the actuator is configured to enable the orientation of the injector to be varied by turning about the longitudinal axis through an amplitude less than or equal to 90&#xb0;.

Injectors for gas turbine combustion chamber

A laser welding head is configured to fasten under a focusing lens for focusing the laser and including at least one annular nozzle for injecting a protective gas, and a protective chamber for protecting the focusing lens with a transverse flow of air. The annular nozzle is arranged around an unobstructed optical axis passing through the laser welding head. The chamber for protecting the focusing lens with a transverse flow of air includes air admission and air exhaust in register with the air admission in a plane substantially perpendicular to said optical axis. The laser welding head is configured to be fastened against the focusing lens without any lateral opening between the focusing lens and the protective chamber. The head presents a distance of at least 100 mm between an outlet of the annular nozzle and the protective chamber.

Laser welding head and process

Growing community of inventors

Moissy-Cramayel, France

Olivier Lamaison