Abstract: The invention relates to a low pressure turbine (1) of a turbomachine comprising a nozzle (62) belonging to an upstream stage (20B) and a nozzle (162) belonging to a downstream stage (20C), the nozzle (62) forming segments (62a) having an external structure (66) comprising: a tab (76) bearing radially on a hook (79) fixed to the case, a tab (85) bearing radially on a reaming (87) in the case, the tabs (76, 85) delimiting an annular upstream cooling air circulation cavity (91), a contact surface (84) extending in the downstream direction from the tab (85) and lined with an abradable element (86) on the inside, the contact surface comprising a downstream end (92) bearing axially on the nozzle (162) and bearing radially on a stop (93) of the case, the contact surfaces (84) delimiting an annular downstream cooling air circulation cavity (94) communicating with cavity (91).

Abstract: A turbine engine, including a final centrifugal compressor stage associated with a diffuser for supplying air to a combustion chamber, and a ventilation element for ventilating a high-pressure turbine wheel, is disclosed. The ventilation element includes an injection element for injecting air onto the wheel and a take-up element for taking up a flow for cooling the impeller of the compressor, where the take-up element has a labyrinth seal mounted at the outlet of the injection element, and the air outlet orifices are installed between the injection element and the labyrinth seal and leading upstream of the turbine wheel.

Abstract: The invention relates to a low pressure turbine (1) of a turbomachine comprising a nozzle (62) belonging to an upstream stage (20B) and a nozzle (162) belonging to a downstream stage (20C), the nozzle (62) forming segments (62a) having an external structure (66) comprising: a tab (76) bearing radially on a hook (79) fixed to the case, a tab (85) bearing radially on a reaming (87) in the case, the tabs (76, 85) delimiting an annular upstream cooling air circulation cavity (91), a contact surface (84) extending in the downstream direction from the tab (85) and lined with an abradable element (86) on the inside, the contact surface comprising a downstream end (92) bearing axially on the nozzle (162) and bearing radially on a stop (93) of the case, the contact surfaces (84) delimiting an annular downstream cooling air circulation cavity (94) communicating with cavity (91).

Abstract: Turbine engine, including a final centrifugal compressor stage associated with a diffuser for supplying air to a combustion chamber, and ventilation means for ventilating a high-pressure turbine wheel, including injection means for injecting air onto the wheel and take-up means for taking up a flow for cooling the impeller of the compressor, wherein these take-up means comprise a labyrinth seal mounted at the outlet of the injection means and the air outlet orifices installed between the injection means and said labyrinth seal and leading upstream of the turbine wheel.

Abstract: The invention provides a turbomachine including a device for supplying pressurized gas, the gas being bled from the compressor of the turbomachine via a bleed orifice and cooled in a cooling cavity disposed within the compressor rotor upstream of the bleed orifice. This arrangement has the effect of cooling the bled gas by heat transfer through the outer wall of the compressor rotor to the gas stream which is being compressed by the compressor upstream of the bleed orifice, and has the result of reducing the drop in the performance of the compressor as a result of the gas being bled off.

Abstract: A turbine vane-system cooling system uses three internal cooling cavities 1, 12, 13) separated by two radial walls (9, 10). The upstream cavity (11) uses a helical ramp (30) and is fed through an intake (22) at the vane root (3). The middle cavity (12) also is fed at the vane root (3) and includes a compartmented, multi-perforated lining (40). The air is exhausted from each compartment through impact orifices and enters the succeeding compartment through slots (42) and then is finally exhausted through a vane-head orifice (21). The vane side walls opposite the downstream cavity (13) have double skins with bridging elements. The air passes through these double skins but circulates centrifugally in the upstream portion (15) of the downstream cavity (13) and enters this cavity's downstream portion (16) to be exhausted through slots (19) in the trailing edge (6). A third wall (14) divides the downstream cavity (13) into two parts (15, 16).

Abstract: A gas mixer (8) which placed in a flow of gases upstream of a ring (3) that is to be heated or cooled, the gas mixer (8) including a succession of mbers (12, 14, 15) having communication or outlet orifices (16, 17, 18) in large numbers in order to render uniform a rate and temperature of the gas flow. The gas mixer (8) is applicable to gas turbine engines.

Abstract: A cooled turbine guide vane comprises a hollow aerodynamic portion between inner and outer platforms. The interior of the aerodynamic portion is partitioned into a leading edge duct and a main cavity in which a perforated tubular member is disposed, being spaced from the intrados and extrados side walls of the vane by longitudinal ribs. The tubular member is divided by a partition into two cavities on the intrados and extrados sides of the partition. A first cooling circuit is constituted by the leading edge duct and the intrados cavity of the tubular member, and a second cooling circuit is constituted by the extrados cavity and a cooling system for the inner platform, both circuits being supplied with air by the same source from the outer platform. Cooling air from each circuit passes through the perforations of the tubular member to impinge on the inside face of the respective side wall of the vane and is then guided towards the trailing edge where it escapes through slits in the trailing edge.

Abstract: A nozzle of a turbine stator of a turbine engine, wherein at least two of the vanes are fixed to each inner platform and to opposite each outer platform, and a maintaining unit is configured to maintain each sector with respect to a case of the turbine stator and to connect sectors together and has a rotational maintaining element, a radial maintaining element and an axial maintaining element. The radial maintaining element is flexible so as to permit a radial expansion of each sector and is constituted by an elastic joint fixed to the case so as to surround the sectors.

Abstract: While remaining in one piece and unsectored, a nozzle permits a slight radial expansion of an assembly. The nozzle is formed by an inner platform mounted in a sliding manner with respect to a stator and an outer platform mounted in a free manner with respect to the case of the stator. Rods are fitted in a pivoting manner so as to radially guide and axially block upper parts of vanes, which are mounted in a sliding manner in the inner platform. The assembly is advantageously completed by gaskets. The nozzle can be used in high pressure turbines of turbojets.