Snecma

Safran Aircraft Engines

Snecma Moteurs

Hispano Suiza

Jose Roland Rodrigues

Marion Michau

Emilie Charlotte Pousseo

Alain Tiepel

Robert Kervistin

Christophe Chabaille

Didier Georges Feder

Gilles Louis Rollin

Alain Lavie

Christophe Viguier

Severine Chevalier

Alain Schuler

Marion De Giacomoni

Séverine Chevalier

Stephanie Martelli

Frederic Ravet

Gwenaelle Calvez

An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing device between the inner surface of the guide and the outer casing. The sealing device includes a first part accommodated in a groove of the outer casing, the groove being delimited, in part, by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against the downstream delimiting surface; and a second part having a second sealing surface bearing radially against the inner surface of the guide.

Sealing device between an injection system and a fuel injection nozzle of an aircraft turbine engine

The present invention relates to a method for differentiating control failures in a system for controlling an actuator () determining the position of a member for modifying the state of a gas-turbine engine, the system including a single- or dual-channel electric control and a mechanical control, the electric control including one computer (') per channel, only one of which is active at any given time in order to calculate the set position of the movable member of the actuator () and to transmit a set signal to the single-channel mechanical control of the actuator, a failure being diagnosed when a deviation is detected between the set position of the movable member of the actuator and the position thereof measured during a predetermined deviation confirmation time. The method is characterised in that the speed of movement of the actuator is measured and in that the system diagnoses an electrical failure when, during said time for confirming the deviation, the measured speed of movement is other than zero and remains higher than a predetermined threshold speed; otherwise, the failure is diagnosed as being of temporary mechanical origin.

Method for differentiating control failures in a system for controlling an actuator, in particular of a stator of a gas-turbine engine

A fuel injector for a turbine engine, the injector including a body including a mechanism for admitting fuel under pressure, a stop valve for feeding a primary fuel circuit, and a metering valve mounted downstream from the stop valve for feeding a secondary fuel circuit. The injector further includes at least one leakage channel, that can be formed by a thread, that extends from a zone situated downstream from the stop valve and upstream from the metering valve to a zone situated downstream from the metering valve to generate a permanent leakage flow in the secondary circuit.

Turbine engine fuel injector with permanent leakage flow

A fuel injector for a turbine engine, the injector including a body including a primary fuel circuit and a secondary fuel circuit fed by a metering valve. A leakage channel extends from a zone in fluid flow connection with the primary circuit to a zone in fluid flow connection with the secondary circuit. The leakage channel is configured to be open in a closed position of the metering valve and to be closed by the metering valve moving.

Turbine engine fuel injector with leakage flow controlled by position of metering valve

The invention relates to a method and a device for protecting fuel injectors in a turboshaft engine. The protection is carried out by injecting compressed air directly into the injectors. The air thus directly purges the injectors and evacuates the fuel present in them into the combustion chamber.

Method and system for protecting gas turbine fuel injectors

Growing community of inventors

Nandy, France

Jose Roland Rodrigues