Abstract: In a turbomachine stator vane having a leading edge, a trailing edge, and pressure side and suction side faces, and including a perforated open liner defining an annular cavity between an outside wall of the liner and an inside wall of the vane, an air admission opening for feeding cooling air to the inside of the liner, and an air exhaust opening for exhausting a fraction of this cooling air out from the vane, the liner being secured to the vane at one end and being free at another end to slide along an inside edge of the vane under the effects of relative thermal expansion between the liner and the inside wall of the vane, provision is made for the open liner to comprise a plurality of holes distributed over only two determined zones of said liner, a first series of holes being disposed facing the inside wall of the leading edge and a second series of holes being disposed facing the inside wall of the trailing edge, the holes through the liner in the second series of holes also being disposed in such a mann

Abstract: The invention relates to a part (110) of the distributor of the first stage of a turbojet low-pressure turbine. A part of this type comprises an outer platform segment (104) and an inner platform segment (102) between which a plurality of hollow blades (106), intended to be supplied with cooling air, extend, a cap (132) covering a base portion (138) of the outer platform segment (104) so as to define with this base portion a chamber (140), which communicates with the interior of said blades (106) via communication openings (130), air inlets (137) being provided in said cap (132) in order to allow said chamber (140) to be supplied with cooling air.

Abstract: An annular platform for the nozzle of a low-pressure turbine in a turbomachine, said nozzle having a longitudinal axis and comprising at least one fixed vane disposed downstream from at least one moving blade of a high-pressure turbine, said platform comprising a downstream portion supporting said fixed vane radially defining an aerodynamic channel which extends longitudinally between a leading edge of said fixed vane and a trailing edge of said moving blade, said platform further comprising an upstream portion extending longitudinally beyond the leading edge of said fixed vane towards the trailing edge of said moving blade so as to lengthen said aerodynamic channel.

Abstract: The present invention concerns a cooled gas turbine blade comprising a foundry part and a longitudinal sleeve obtained by the forming of metal sheet, the foundry part including a longitudinal body provided with a longitudinal cavity with first and second apertures at its ends, the sleeve being mounted in the cavity being held therein by soldering or brazing to the wall of the first aperture, and an end portion of which is free to slide in the second slide-forming aperture. The blade is characterized by the fact that the end portion and the slide are in sliding contact relatively to surfaces formed by machining.

Abstract: An annular platform for the nozzle of a low-pressure turbine in a turbomachine, said nozzle having a longitudinal axis and comprising at least one fixed vane disposed downstream from at least one moving blade of a high-pressure turbine, said platform comprising a downstream portion supporting said fixed vane radially defining an aerodynamic channel which extends longitudinally between a leading edge of said fixed vane and a trailing edge of said moving blade, said platform further comprising an upstream portion extending longitudinally beyond the leading edge of said fixed vane towards the trailing edge of said moving blade so as to lengthen said aerodynamic channel.