Turbomeca

Safran Helicopter Engines

Edgar H Haehner

Eric Royer

Gerald Senger

Yann Mouze

Frederic Ferdinand Jacques Batlle

Frederic Segura

Gérald Senger

Roger H Barbe

Alain M Dufau

Frédéric Segura

Frederic Ferdinand Batlle

A method of starting a turbomachine, performed by an electronic unit, the turbomachine including a gas turbine engine including at least one rotor and a starter to drive the rotor in rotation, the method including: receiving an order to start the turbomachine, and executing in response to receiving the order to start: a primary acceleration during which the starter is operated to increase speed of rotation of the rotor; a thermal homogenization during which the starter is operated to keep the speed of rotation of the rotor constant or to decrease it until a predetermined condition is satisfied; after the predetermined condition is true, a secondary acceleration in which the starter is operated to increase the speed of rotation of the rotor; and an ignition in which ignition of the engine is ordered.

Method of starting a turbomachine while reducing thermal unbalance

A method for calibrating a torsion torquemeter including: placing a torsion torquemeter in a first state; performing first measurements determining first and second angular offsets, and measuring torque output by the power shaft using a reference torquemeter; placing the torsion torquemeter in a second state; performing second measurements determining the first and second angular offsets, and measuring torque output by the power shaft; placing the torquemeter in a third state; performing third measurements determining the first and second angular offsets, and measuring the torque output by the power shaft; placing the torquemeter in a fourth state; performing fourth measurements determining the first and second angular offsets, and measuring the torque output by the power shaft; calibrating the calculation unit based on the first, second, third, and fourth measurements.

Method for calibrating a torsion torquemeter

A de-icer device for de-icing an air inlet of a gas turbine, such as a helicopter turbine engine. The de-icer device includes an essentially metallic enclosure for admitting air into the engine, the enclosure including a first opening for admitting air into the enclosure, the first opening including a first essentially metallic grid, the enclosure further including a second opening for directing the air towards a compression stage of the gas turbine. The de-icer device further includes a wave generator for generating electromagnetic waves in the enclosure at a frequency suitable for causing ice to melt.

Device for de-icing the air intake of a gas turbine

A turbine engine for a helicopter, including a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator is disclosed. The turbine engine further includes a motor/generator coupled to a shaft of the gas generator, to provide a quantity of additional rotational kinetic energy to the shaft during a stage of turbine engine acceleration, or to draw a quantity of rotational kinetic energy from the shaft during a stage of turbine engine deceleration.

Assistance device for transient acceleration and deceleration phases

According to this method the linear expansion (.DELTA.L) of a reference shaft is measured with reference to that of the power shaft. The linear expansion of the reference shaft (R.sub.3) is converted into a movement of rotation of an annular phonic wheel (B.sub.3) by means of the free end (J) of this shaft engaged in a helical groove in the inner surface of the annular wheel (B.sub.3).

Growing community of inventors

Bizanos, France

Edgar H Haehner