Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Michel R Ayache

Gerard M Mandet

Pierre A Glowacki

Daniel J Marey

Jean-Claude L Delonge

A portion of the stator of a gas turbine known as turbine shroud, which is ituated radially opposite the mobile vanes of a turbine stage includes an 'abradable' member supported by a first shell braced by a second shell and connected with turbine casing 2 by a thin, i.e. flexible, annular wall member embedded in a casing. Cooling air inflates the second shell so as to brace the exterior shell and circulates between the two shells so as to cool them and also cools the 'abradable' member by impingement. The present invention is applicable to aviation turbojets.

Temperature control device for gas turbines

A labyrinth seal mounted between a shaft and the casing of a gas turbine combustion chamber, wherein the support of an abradable sealing surface in the seal which operates in conjunction with rapidly rotating fins is cooled by an upstream airflow parallel to the envelope surface of the extremities of such fins and opening into an upstream space. The cooling air is taken in from the casing by means of a conduit which is connected with an overflow valve tied to the gas turbine load. The invention is applicable to aviation turbojets.

Labyrinth seals

A device for moving air from the jet flow of an axial compressor of a gas rbine group, to be conducted along the axis of the group to the turbine to be cooled. The air is moved by a wheel having an outer rim serving as a brace between two adjacent compressor disks and centripetal blading which moves the air through openings formed in the rim, to accelerate it and discharge it into a space surrounding the axis of the compressor.

Cooling fluid bleed for axis of turbine rotor

A turbine housing for a jet engine is provided with a ring of an abradable orous material. A supporting and mounting device consisting of a cylindricoconical monoblock having a conical internal jacket provides for the convection cooling of the external surface and a cylindrical jacket for cooling air is held over the abradable ring by means of a perforated ferrule integral with the rest of the device. The abradable ring carries transverse partitions to prevent axial leakage.

Growing community of inventors

Epinay sous Senart, France

Michel R Ayache