The invention relates to a turbomachine comprising a device for ventilating and pressurising a turbine rotor of a turbomachine of axis (A), the device comprising at least one collection pipe suitable for collecting a fraction of the air circulating in a high-pressure compressor of the turbomachine and conveying it to a first inner chamber (39) inside the turbomachine that communicates with a second inner chamber (40) delimited by the turbine (24) rotor (23), the first and second chambers (39, 40) being at least partially separated by a stationary shroud (56) of axis (A), characterised in that it comprises at least one injector (58) passing through the stationary shroud (56) and having a cross-section that varies in response to a pressure difference between said first and second chambers (39, 40).

The invention relates to a turbomachine comprising a device for ventilating and pressurising a turbine rotor of a turbomachine of axis (A), the device comprising at least one collection pipe suitable for collecting a fraction of the air circulating in a high-pressure compressor of the turbomachine and conveying it to a first inner chamber (39) inside the turbomachine that communicates with a second inner chamber (40) delimited by the turbine (24) rotor (23), the first and second chambers (39, 40) being at least partially separated by a stationary shroud (56) of axis (A), characterised in that it comprises at least one injector (58) passing through the stationary shroud (56) and having a cross-section that varies in response to a pressure difference between said first and second chambers (39, 40).

A turbine rotor for aircraft turbine engine includes a mobile disc supporting mobile blades, the mobile disc including a plurality of slots into which are inserted the roots of the mobile blades a passage being formed between the bottom of the slots and the roots of the mobile blades inserted into the slots. The rotor also includes a circulation channel configured to allow circulation of fluid, the circulation channel including the passage, and a calibration device configured to allow the flow of a first fluid flow rate in the circulation channel when the temperature within the channel is less than a predetermined temperature threshold value, and to change state so as to allow the flow of a second fluid flow rate, greater than the first flow rate, in the channel, when the temperature within the channel is greater than or equal to said predetermined threshold value.

A turbine rotor for aircraft turbine engine includes a mobile disc supporting mobile blades, the mobile disc including a plurality of slots into which are inserted the roots of the mobile blades a passage being formed between the bottom of the slots and the roots of the mobile blades inserted into the slots. The rotor also includes a circulation channel configured to allow circulation of fluid, the circulation channel including the passage, and a calibration device configured to allow the flow of a first fluid flow rate in the circulation channel when the temperature within the channel is less than a predetermined temperature threshold value, and to change state so as to allow the flow of a second fluid flow rate, greater than the first flow rate, in the channel, when the temperature within the channel is greater than or equal to said predetermined threshold value.

An assembly for a turbomachine extending along an axis includes a combustion chamber having, at its downstream end, a downstream flange having a radially extending part. The assembly further includes a distributor disposed downstream of the combustion chamber and having a platform from which at least one vane extends radially. The platform includes an upstream flange extending radially and delimiting, with the radial part of the downstream flange disposed opposite it. An annular space for the circulation of cooling air opens into the combustion chamber at its radially internal end and has, at its radially external end, means of sealing attached to the distributor.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a turbine engine component that includes a sidewall and a cooling aperture. The cooling aperture includes an inlet, an outlet, a meter section, a diffuser section and a transition section between and fluidly coupled with the meter section and the diffuser section. The cooling aperture extends through the sidewall from the inlet to the outlet. The meter section is at the inlet. The diffuser section is at the outlet. The transition section is configured to accommodate lateral misalignment between the meter section and the diffuser section.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a turbine engine component that includes a sidewall and a cooling aperture. The cooling aperture includes an inlet, an outlet, a meter section, a diffuser section and a transition section between and fluidly coupled with the meter section and the diffuser section. The cooling aperture extends through the sidewall from the inlet to the outlet. The meter section is at the inlet. The diffuser section is at the outlet. The transition section is configured to accommodate lateral misalignment between the meter section and the diffuser section.

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

The present disclosure relates to an impeller and a method of manufacturing the same. The impeller includes: a hub in which a plurality of spiral first slots are formed; a shroud which is positioned opposite the hub, and has a plurality of spiral second slots formed therein; and a plurality of blades which is coupled to the hub and the shroud, and have an upper protrusion formed on one side and a lower protrusion formed on the other side; and wherein the upper protrusion is inserted into and coupled to a second hole formed in the second slot, and the lower protrusion is inserted into and coupled to a first hole formed in the first slot.