Safran Helicopter Engines

Safran Electronics & Defense

Turbomeca

Stephen Langford

Nicolas Marti

Celine Liu

Camel Serghine

Romain Thiriet

Patrick Marconi

Jean-Michel Bazet

Pierre Harriet

Michael Montoya

Fabien Lescher

Rafaël Samson

Jérôme Irigoyen

Rafael Samson

Céline Liu

Jerome Irigoyen

A flight control system of an aircraft including a first processing unit, a second processing unit, communication means configured to establish a first two-way digital link and as second two-way digital link between the first processing unit and the second processing unit. The second link is redundant with the first link, and the first link and second link are likely to be active concomitantly. The system further includes backup communication means enabling data exchanges between the first processing unit and the second processing unit in the case of a failure in the first link and second link. The backup communication means includes an array of sensors or actuators and/or a secure onboard network for the avionics.

Two-way architecture with redundant CCDL's

A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.

Device and method for testing the integrity of a helicopter turbine engine rapid restart system

The invention relates to an overspeed protection device of an aircraft engine.

Overspeed protection device of an aircraft engine

A turbine engine includes a compressor, a combustion chamber, first and second turbines downstream from the combustion chamber, a first rotary shaft constrained to rotate at least with the compressor and the first turbine, a second rotary shaft constrained to rotate with the second turbine, the second rotary shaft nevertheless being free to rotate relative to the first rotary shaft, and a regulator for controlling the feed of fuel to the combustion chamber. The regulator cuts off the feed of fuel to the combustion chamber if the speed of rotation of the second rotary shaft exceeds a maximum threshold that varies as a function of at least one indicative physical parameter associated with mechanical power being extracted from the combustion gas by the second turbine. A method of regulating the turbine engine is also presented.

Turbine engine and control method

The present invention concerns a method for switching, by a local processing unit () of a flight control system of an aircraft, configured to control at least one local actuator, connected to at least one local sensor and connected via at least one link () to an opposite processing unit () configured to control at least one opposite actuator and be connected to at least one opposite sensor, said local processing unit () being further configured to be connected to backup communication means () enabling data exchanges between the local processing unit () and the opposite processing unit () in the case of failures of the links connecting same (), said backup communication means comprising an array of sensors or actuators () and/or a secure onboard network for the avionics (), comprising steps of: &#x2022;&#x2014;sending, to the opposite processing unit (), acquisition data relative to the at least one local sensor and actuator data relative to the at least one local actuator, &#x2022;&#x2014;receiving, from the opposite processing unit (), acquisition data relative to the at least one opposite sensor and actuator data relative to the at least one opposite actuator, &#x2022;&#x2014;receiving an item of opposite health data and determining an item of local health data, &#x2022;&#x2014;switching said local processing unit () from a first state to a second state chosen from an active state (), a passive state () and a slave state (), depending on the opposite health data received and the local health data determined.

Two-way architecture

A method improving acceleration efficiency of a gas generator of a gas turbine by reducing take-up of electric power, during transition phases, to conserve a sufficiently large surge margin for an operating line. The method increases acceleration/deceleration power of the gas generator by adjusting voltage of an electric network onboard the aircraft. After a phase of starting the gas turbine, voltage of the onboard network is adjusted by a voltage set value controlled by determining unballasting/ballasting status of a main electricity generation source of the onboard network. The status-determining is executed according to demand for taking power to be supplied for propulsion of the aircraft. The status-determining is followed by selecting a voltage set value from plural levels according to the determining the unballasting/ballasting status, and applying the selected set value to a control loop of the voltage supplied to the onboard network.

Method for controlling the generation of electricity applied to an aircraft gas turbine, and device implementing such a method

Growing community of inventors

Pau, France

Stephen Langford