Abstract: The manufacturing cost of the control device is relatively low. This device comprises mainly a first end (46) of a control lever (40) provided with a drive hole (45) that drives the driving part (16) of a blade (10) through a first contact area (41). The close contact between these two parts in this area is obtained using a play compensation plate (50) bearing on a side part (47) of the control lever (40), and fixed to the assembly using a nut (60) screwed onto the external pivot (11) of the blade (10). For application on turbomachines.

Abstract: A machine stator and assembly and disassembly methods. The elements of a casing portion are formed of consecutive shells in line with grooves configured to house roots of guide vane stages that are fixed in place by springs and pins for stopping rotation. The elements are arranged in a complete circle, and the assembly is made by axially separating the elements to insert the guide vane stages between the elements by a radial movement.

Abstract: The pitch control mechanism (controlling the angular position) for stator blades in a turbojet may be adjusted separately for two adjacent stages of blades controlled by a common actuator 10. To achieve this, the synchronization bar 9 located between the mechanisms leading to the two stages is inclined, this inclination being determined by a pin 22 and groove 23 connection with the casing, while another pin 26 and groove 27 connection is arranged between the synchronization bar 9 and one of the mechanisms. Strongly non-linear displacement laws between the two mechanisms may thus be controlled depending on the shapes and directions of the grooves.

Abstract: A device for stopping rotation of a fixed blade bearing sector in a gas turbine casing. Sectors of synchronizing ring blades are maintained against tangential rotational movements by sliding into grooves of a casing by pins passing through perforations in an extension of the two parts. The pins are prevented from accidental removal either by a flexible lock ring or by a locking tab maintained between the two parts when they have been completely assembled.

Abstract: A device for controlling variable-pitch vanes in a turbomachine comprises links connecting the radial pivots of the vanes to radial fingers carried by semicircular elements and bridges of a control ring, the links being mounted in ball-and-socket manner on the radial fingers which are fixed to the control ring. This form of mounting enables all the vanes associated with the control ring to be set to the same angular pitch.

Abstract: A machine stator and assembly and disassembly methods. The elements of a casing portion are formed of consecutive shells in line with grooves configured to house roots of guide vane stages that are fixed in place by springs and pins for stopping rotation. The elements are arranged in a complete circle, and the assembly is made by axially separating the elements to insert the guide vane stages between the elements by a radial movement.

Abstract: The pitch control mechanism (controlling the angular position) for stator blades in a turbojet may be adjusted separately for two adjacent stages of blades controlled by a common actuator means 10. To achieve this, the synchronization bar 9 located between the mechanisms leading to the two stages is inclined, this inclination being determined by a pin 22 and groove 23 connection with the casing, while another pin 26 and groove 27 connection is arranged between the synchronization bar 9 and one of the mechanisms. Strongly non-linear displacement laws between the two mechanisms may thus be controlled depending on the shapes and directions of the grooves.

Abstract: The manufacturing cost of the control device is relatively low.

Abstract: Sectors (16) of synchronizing ring blades are maintained against tangential rotational movements by sliding into the grooves (18) of a casing (15) by pins (23) passing through perforations in the extension of said two parts, and prevented from accidental removal either by a flexible lock ring (24) or by a locking tab (26) maintained between the two parts when they have been completely assembled.

Abstract: A device for controlling variable-pitch vanes in a turbomachine comprises links connecting the radial pivots of the vanes to radial fingers carried by semicircular elements and bridges of a control ring, the links being mounted in ball-and-socket manner on the radial fingers which are fixed to the control ring. This form of mounting enables all the vanes associated with the control ring to be set to the same angular pitch.

Abstract: A spring (15) of angular shape is placed between the lug (17) of a connecting rod (10) controlling the orientation of a stator blade and the pivot (3) of said blade, such that its edge (18) bends against one edge face (19) of the connecting rod (10) and the washer (16) moves the pivot (3) in the play of the bore (21) of the connecting rod and sets and maintains the contact between two plane faces (12 and 13), so as to reduce the differences in angular displacements between the connecting rod and pivot due to the play remaining in the bore (21).

Abstract: A low of compressed air originating from a compressor stream (3) is drawn off through first orifices (13) towards ducts (5, 6) leading outside the casing, creating a flow division through adjacent cavities (11, 12) in the casing (1). These arrangements make it possible to carry a large air flow even if the cavity cross sections (11, 12) are small.

Abstract: A spring (15) of angular shape is placed between the lug (17) of a connecting rod (10) controlling the orientation of a stator blade and the pivot (3) of said blade, such that its edge (18) bends against one edge face (19) of the connecting rod (10) and the washer (16) moves the pivot (3) in the play of the bore (21) of the connecting rod and sets and maintains the contact between two plane faces (12 and 13), so as to reduce the differences in angular displacements between the connecting rod and pivot due to the play remaining in the bore (21).

Abstract: A low of compressed air originating from a compressor stream (3) is drawn off through first orifices (13) towards ducts (5, 6) leading outside the casing, creating a flow division through adjacent cavities (11, 12) in the casing (1). These arrangements make it possible to carry a large air flow even if the cavity cross sections (11, 12) are small.

Abstract: A separate inter-blade platform for a turbomachine rotor comprises a structural rectilinear longitudinal member formed by a foam core, plies of a carbon/epoxy type material in bidirectional layers of crossed fibres oriented at 45.degree. laid around the core and around an insert at each end of the longitudinal member, each insert being made of juxtaposed radial plies of a carbon/epoxy type material in bidirectional layers of fibres crossed at .+-.45 degrees, and further plies of a carbon/epoxy type material in unidirectional layers oriented in the direction of the major axis of the longitudinal member covering the upper and lower faces of the member, the platform further comprising lateral packing cores made of a foam material, plies of a glass/epoxy type material covering the lateral faces of the longitudinal member and connecting it to the lateral foam cores, and peripheral plies of a glass/epoxy type material covering the assembly formed by the longitudinal member and the lateral cores connected thereto.