Abstract: The present invention relates to a turbine engine having a casing (7) which has an inner wall (3i) forming a wall of an air duct (3) and at least one opening (7r) passing through the casing, leading into the duct (3) and forming a passage for an endoscope. The opening (7r) is closed during operation of the turbine engine by a stopper (8) which has an end-surface portion (8s) in the extension of the inner wall (3i). An indicator of wear to the inner wall of the casing is associated with the stopper (8) or with the inner wall (3i) of the casing, in the proximity of the stopper (8).

Abstract: A turbine engine compressor has at least one annular row of variable-pitch stator vanes that are substantially radial and have pivots at their radial ends. The radially outer pivots of the vanes are received in first openings in a stator casing and the radially inner pivots are received in second openings in a floating ring that surrounds a rotor of the compressor. An annular stator part is inserted between the floating ring and the rotor of the compressor, and first sealing means are mounted between the stator part and the rotor of the compressor. Second sealing means are mounted between the floating ring and the stator part.

Abstract: The present invention relates to a turbine engine comprising a casing (7) which has an inner wall (3i) forming a wall of an air duct (3) and at least one opening (7r) passing through the casing, leading into said duct (3) and forming a passage for an endoscope, the opening (7r) being closed during operation of the turbine engine by a stopper (8) which has an end-surface portion (8s) in the extension of the inner wall (3i), characterised in that an indicator of wear to the inner wall of the casing is associated with the stopper (8) or with the inner wall (3i) of the casing, in the proximity of the stopper (8). The means of the invention allows simple inspection, without a measurement apparatus being used.