Institut Francais Du Pe'trole

Other

Safran Helicopter Engines

Turbomeca

Guy Grienche

Hubert Pascal Verdier

G&eacute;rard Henri Martin

Jean-Herv&eacute; Le Gal

G&eacute;rard Schott

Etienne Lebas

Patrick Flament

Gérard Martin

Nicolas Savary

Patrick Berteau

Claude Berat

Gérard Schott

Patrice Laborde

Tidjani Niass

Rapha&euml;l Spagna

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

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

A combustion chamber of a gas turbine working on liquid fuel includes a tubular enclosure ( ) having at least one pressurized air inlet, a liquid fuel injection means ( ) positioned on or in proximity to the longitudinal axis (XX&prime;) of the tubular enclosure, and an outlet to the turbine. The fuel injection means ( ) includes a series of orifices ( ) arranged so as to create separate fuel jets, the jets being arranged in the direction of the generatrices of a cone with an angle ranging between 30&deg; and 60&deg; at the vertex thereof. The chamber includes at least two types of pressurized air inlets placed close to each other, the first one ( ) taking in the air helically around the longitudinal axis of the combustion chamber, the second air inlet ( ) being tangential to enclosure ( ) so as to create, around the fuel jets, counterrotating flows intended to improve mixing of the air and of said fuel. The assembly preferably works at a pressure ranging between 2 and 30 bars and with a fuel/air ratio ranging between 0.4 and 0.8.

Combustion chamber of a gas turbine working on liquid fuel

The present invention relates to a gas-turbine combustion chamber comprising at least a zone (,) referred to as pilot combustion zone into which at least a first pilot fuel injection means (,) and an associated first oxidizer injection means (,) open; a main combustion zone (,) into which at least a second main fuel injection means (,) and an associated second oxidizer injection means (,) open, all of it being maintained under a pressure P,inside an enclosure (,). According to the invention, said chamber further comprises a mechanical means (,) for controlling the second flow of oxidizer, which reacts to the pressure difference between the inside (P,) and the atmospheric pressure (Po) outside enclosure (,), said pressure difference being directly linked with the engine speed.

Variable-throat gas-turbine combustion chamber

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Coarraze, France

Guy Grienche