Snecma

Snecma Moteurs

Delphine Roussin-Moynier

Alain Dominique Gendraud

Thierry Fachat

Anne-Marie Arraitz

Jerome M Friedel

Denis Amiot

Pascal Lefebvre

Christian Kaincz

Frederick Duny

Jérôme Friedel

Frédérick Duny

A system for controlling a flow of air applied to a gas turbine shroud in an airplane engine, the air flow being adjusted by a regulator valve of position that is controlled by a first control signal calculated on the basis of a first setpoint value corresponding to predetermined clearance between the rotor and the turbine shroud. The system further comprises means for calculating at least one second control signal based on a second setpoint value different from the first value representative of clearance in the turbine, and selector means for-selecting the second control signal to control the regulator valve in response to one or more engine parameters. With such a system, it is possible to control the air flow applied to the shroud in application of a plurality of control logic systems.

Controlling air flow to a turbine shroud for thermal control

A clearance control device for controlling clearance between rotary blade tips and a stationary bushing of a gas turbine having a casing that is provided with at least two annular ridges, the clearance control device including a circular tuning unit that includes air circulation means for circulating air, said means being made up of at least three ducts; air supply means for supplying air to the air flow ducts; and air discharge means for discharging air on the ridges in order to modify the temperature, the air discharge means for each duct being made up of at least one top row having a number N of perforations disposed facing one of the side faces of the ridges and of at least one bottom row having a number 2N of perforations disposed facing a connection radius that connects the ridges to the casing.

Gas turbine clearance control devices

A stationary ring assembly forming a rotor shroud for a gas turbine including a plurality of segments having adjacent side faces that are placed end to end with sealing means interposed therebetween. The sealing means include at least one axial sealing strip and at least one radial sealing strip respectively received in axial slots and in radial slots formed facing one another in the adjacent side faces of the segments. At least one end of each radial slot opens out into the corresponding axial slot, each axial slot of a segment presents a depth that is greater than the depth of the corresponding radial slot, and the axial sealing strip presents a width that is greater than the width of the radial strip.

Stationary ring assembly for a gas turbine

Growing community of inventors

Antony, France

Delphine Roussin-Moynier