Abstract: A stator ring of a flow path, preferably secondary, of a turbomachine, the ring including an inner platform and an outer platform, a plurality of stators extending radially between the two platforms, in which at least one of the two platforms includes a plurality of integrated platforms, each one of the integrated platforms being integral with one of the stators, and the integrated platforms are all of the same shape as one another, and a plurality of attached platforms, each one of the attached platforms being in the form of a part that is assembled and arranged between two integrated platforms, and the attached platforms are also all of the same shape as one another.

Abstract: A turbomachine or high pressure compressor including a stator casing housing a plurality of compression stages that are spaced apart in an axial direction along the central axis of the turbomachine, each compression stage including a row of rotor blades followed by a row of stator vanes. The compressor further includes an air injection system including at least one air injection passage through the casing and including an outlet segment that opens out in an inclined manner upstream from and directed towards a row of rotor blades into a set-back zone of the inside face of the casing.

Abstract: A turbomachine or high pressure compressor including a stator casing housing a plurality of compression stages that are spaced apart in an axial direction along the central axis of the turbomachine, each compression stage including a row of rotor blades followed by a row of stator vanes. The compressor further includes an air injection system including at least one air injection passage through the casing and including an outlet segment that opens out in an inclined manner upstream from and directed towards a row of rotor blades into a set-back zone of the inside face of the casing.

Abstract: The present invention relates to an improvement in the clearances 12 between a casing and the moving blades 11 of a rotor 1 of a turbomachine, in particular a casing provided for this purpose, and also to a turbomachine fitted with such a casing. The invention applies in particular to aircraft turbojet engines. It relates more particularly to a turbomachine inner casing 21 comprising a plurality of annular shrouds 23 that are provided with flanges 24 for joining two adjacent shrouds 23 together. According to the invention, this inner casing 21 further includes: at least one circumferential heat shield 5 covering the flanges 24 in contact with two adjacent shrouds 23; and a cavity 6 filled with a first thermal insulation 8, said cavity being located between a concave internal surface 51a, 52a of the heat shield 5 and the flanges 24. The heat shield 5 is formed by a plurality of sectors 50 joined end to end.

Abstract: The present invention relates to an improvement in the clearances 12 between a casing and the moving blades 11 of a rotor 1 of a turbomachine, in particular a casing provided for this purpose, and also to a turbomachine fitted with such a casing. The invention applies in particular to aircraft turbojet engines. It relates more particularly to a turbomachine inner casing 21 comprising a plurality of annular shrouds 23 that are provided with flanges 24 for joining two adjacent shrouds 23 together. According to the invention, this inner casing 21 further includes: at least one circumferential heat shield 5 covering the flanges 24 in contact with two adjacent shrouds 23; and a cavity 6 filled with a first thermal insulation 8, said cavity being located between a concave internal surface 51a, 52a of the heat shield 5 and the flanges 24. The heat shield 5 is formed by a plurality of sectors 50 joined end to end.