A discharge grille of an intermediate casing of a turbomachine includes a peripheral edge and a seal mounted on the peripheral edge via an attachment system, the seal ensuring the sealing between a first turbomachine member and a second member of the turbomachine, and surrounding the discharge grille of the intermediate casing, the seal having a U-shaped cross section and includes a base plate configured to bear against the first member, a sealing lip configured to bear against the second member through deformation of the sealing lip to ensure air tightness and fire proofing through contact.

A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.

A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.

A heat management system for turbomachinery is provided. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a turbomachinery. The thermal delivery system includes a first heat transfer conduit and a second heat transfer conduit. The second heat transfer conduit is disposed on the turbomachinery adjacent to the first heat transfer conduit. The heat management system additionally includes a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the turbomachinery via the thermal delivery system.

A heat management system for turbomachinery is provided. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a turbomachinery. The thermal delivery system includes a first heat transfer conduit and a second heat transfer conduit. The second heat transfer conduit is disposed on the turbomachinery adjacent to the first heat transfer conduit. The heat management system additionally includes a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the turbomachinery via the thermal delivery system.

A gas turbine engine has: a high-pressure turbine; a low-pressure turbine (LPT) having a LPT outer case and a LPT plenum extending around a central axis; a mid-turbine frame (MTF) assembly connecting the low-pressure turbine and the high-pressure turbine, the MTF assembly having: a MTF outer case defining an inlet for connection to a source of the cooling air, an intermediary plenum fluidly connected to the source of cooling air via the inlet, the intermediary plenum having a first air outlet and a second air outlet, and a MTF plenum disposed radially inwardly of the MTF outer case and fluidly connected to the source of the cooling air via the first air outlet of the intermediary plenum; and a cooling air conduit fluidly connecting the second air outlet of the intermediary plenum to the LPT plenum while bypassing the MTF plenum.

A gas turbine engine has: a high-pressure turbine; a low-pressure turbine (LPT) having a LPT outer case and a LPT plenum extending around a central axis; a mid-turbine frame (MTF) assembly connecting the low-pressure turbine and the high-pressure turbine, the MTF assembly having: a MTF outer case defining an inlet for connection to a source of the cooling air, an intermediary plenum fluidly connected to the source of cooling air via the inlet, the intermediary plenum having a first air outlet and a second air outlet, and a MTF plenum disposed radially inwardly of the MTF outer case and fluidly connected to the source of the cooling air via the first air outlet of the intermediary plenum; and a cooling air conduit fluidly connecting the second air outlet of the intermediary plenum to the LPT plenum while bypassing the MTF plenum.

A device for cooling a turbine shroud comprising at least one annular flange configured to be attached to an annular radial collar of a shroud support structure being arranged upstream, with respect to a circulation direction of an air flow, of the turbine shroud, and comprising at least one cooling air circulation channel, a diffuser configured to be attached to said annular radial collar downstream of the annular flange and comprising at least one intake channel in fluid communication with the circulation channel of the annular flange, and comprising an injection cavity comprising a plurality of injection holes and being configured to inject on a radially external face of the shroud, via the injection holes, the cooling air originating in the intake channel, and a particle filter arranged on an inlet section of the circulation channel of the annular flange, the particle filter comprising a plurality of openings.

A device for cooling a turbine shroud comprising at least one annular flange configured to be attached to an annular radial collar of a shroud support structure being arranged upstream, with respect to a circulation direction of an air flow, of the turbine shroud, and comprising at least one cooling air circulation channel, a diffuser configured to be attached to said annular radial collar downstream of the annular flange and comprising at least one intake channel in fluid communication with the circulation channel of the annular flange, and comprising an injection cavity comprising a plurality of injection holes and being configured to inject on a radially external face of the shroud, via the injection holes, the cooling air originating in the intake channel, and a particle filter arranged on an inlet section of the circulation channel of the annular flange, the particle filter comprising a plurality of openings.

An assembly having an outer tubular portion delimiting an inner space, an inner tubular portion in the outer tubular portion, a fluid jacket in the inner tubular portion, a plurality of groups of at least four thermal flow sensors. For each group, the sensors of the group are disposed in the inner space and overall in one and the same plane perpendicular to a central line. In each group, the sensors of the group are distributed angularly about the central line. A control unit which, for each group, receives the data from each sensor of the group and which, on the basis of these data, determines a warning level. With such an arrangement, the monitoring of the values of the different thermal flow sensors makes it possible to monitor a potential problem at the fluid jacket.