Abstract: A gas turbine stator including at least a first injector providing a passage for a main cooling air stream into a pressurized chamber. An evacuation mechanism discharges air coming from an internal labyrinth gland of a first cavity towards a lower-pressure second cavity. A second injector evacuates the air contained in the second cavity towards a main duct. The stator further includes a third injector designed to generate an overpressure close to the internal labyrinth gland in the pressurized chamber.

Abstract: A flange covering a disc of a turbine blade to allow ventilation. A diverted face of the disc is provided with a labyrinth seal with lickers to form a seal. Cutters of the lickers are inclined axially and staggered axially and radially, to off-set the center of gravity of a flexible web of the disc and to encourage deformation of the web towards the disc under the effect of centrifugal forces, to reinforce the contact of a bearing face with a pressure plate of the disc. Thus, hooks usually used to unite the periphery of the web to the disc become superfluous.

Abstract: A flange (10) covering a disc (3) of a turbine blade (4) in order to allow ventilation (27, 29) and whose diverted face (24) of the disc (3) is provided with a labyrinth seal (20) with lickers (23) to form a seal, original in that the cutters (37) of the lickers (23) are inclined axially and staggered axially and radially, in order to off-set the center of gravity of the flexible web (14) of the disc and to encourage deformation of the web (14) towards the disc (3) under the effect of centrifugal forces, in order to reinforce the contact of a bearing face (15) with a pressure plate (16) of the disc (3). Thus the hooks usually used to unite the periphery of the web (14) to the disc (3) become superfluous.

Abstract: A method of reducing the gap between a liner and a turbine distributor of a turbojet engine. The method allows for the improvement of the seal on the inside of the distributor of the high pressure turbine at the lower platform. The method includes the steps of: applying a protective deposit to the lower part of the external surface of the liner, before carrying out a filling by diffusion brazing between the liner and the distributor. The protective deposit, preferably a anti-adherent ceramic, makes it possible for the braze to avoid fixing the liner onto the distributor at the lower platform level. The method also has applications to turbojet engines.

Abstract: This seal (6) running between gaps (6) between two stator sectors of a gas urbine engine is made up of several thin flexible slabs, capable of sliding one over the other, which gives a better seal.