Safran Helicopter Engines

Turbomeca

Institut Francais Du Pe'trole

Safran Aircraft Engines

Snecma

Hubert Pascal Verdier

Guy Grienche

Etienne Lebas

Matthieu Francois Rullaud

Gérard Martin

Nicolas Savary

Nicolas Roland Guy Savary

Olivier Lamaison

Yvan Ludovic Lameignere

Patrick Berteau

Philippe Etchepare

Patrick Olivier Duchaine

Bernard Joseph Jean-Pierre Carrere

Claude Berat

Tidjani Niass

Claude Marie Michel Berat

Chritophe Nicolas Henri Viguier

Gérard Schott

Luc Reberga

Pierre Giralt

Matthieu François Rullaud

Jean-Pierre Badet

Philippe Roger Courtie

Bernard Joseph Carrere

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 annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall.

Annular wall of a combustion chamber with improved cooling at the level of primary and/or dilution holes

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

A method of starting a turbine engine, including a re-try performed if a main injector has not ignited when a shaft has reached a first predetermined speed value, the re-try including: a stopping during which a starter and the ignitor device are stopped; a second ignition during which fuel is injected into the combustion chamber, the ignitor device being actuated, the second ignition being performed when a speed of rotation of the shaft reaches a second predetermined speed value; and a second starting during which the starter is actuated once more to drive the shaft in rotation.

Method for starting a turbomachine

The present invention relates to a device for injecting a liquid fuel into a pressurized air flow (), in particular for a combustion chamber, comprising a hollow cylindrical body () of longitudinal axis (YY') delimiting a substantially cylindrical central volume (), fluid veins () substantially radial in relation to the longitudinal axis of body () and arranged on the periphery of said body to allow passage of said flow, and axial fuel injection pipes () arranged inside said fluid veins and connected to at least one fuel inlet () by at least one supply point (). According to the invention, pipes () are pierced with openings () that open onto central volume () of said body () and which are oriented substantially in the direction of the flow in fluid veins ().

Device and method for injecting a liquid fuel into an air flow for a combustion chamber

Growing community of inventors

Nay, France

Hubert Pascal Verdier