Abstract: A gas turbine engine incorporating a starter mounted on the gear box is disclosed. The gas turbine engine includes an AGB gear housing mechanically connected with an engine shaft for driving auxiliary machines and an air starter mounted on the housing, the starter and housing enclosures being in communication such that the lubricating oil of the starter should be distributed from the AGB housing. The oil enclosure of the starter is pressurized by a source of air, being independent from the AGB housing. Advantageously, the pressurization air is taken from a pressurization enclosure of an engine bearing.

Abstract: A gas turbine engine incorporating a starter mounted on the gear box The present invention refers to a gas turbine engine, comprising an AGB gear housing (12) mechanically connected with an engine shaft for driving auxiliary machines and an air starter (10, 10?) mounted on the housing, the starter and housing enclosures being in communication such that the lubricating oil of the starter should be distributed from the AGB housing. The engine is characterized in that the oil enclosure of the starter (10, 10?) is pressurized by a source of air, being independent from the AGB housing. Advantageously, the pressurization air is taken from a pressurization enclosure of an engine bearing.

Abstract: Pivoting vane internal extremity bearing (1) whose internal extremities are connected by a linking ring (12). The bearing elements (18) connecting the internal extremity pivots (10) to the ring (12) are composed of a bush (19) prolonged by bearing necks (20) with a spin axis (X') parallel to that of the ring (12). The forces undergone by the vanes, which transversally move the pivots (10), do not cause any wear of the bush (19), but a rotation of the latter around the axis (X'). Application for turbine aero engine stator vanes.

Abstract: The arrangement of a gas turbine engine suitable for high bypass ratio aircraft engines in which gases circulate in a primary air channel (7) and a secondary channel (8) concentric to said primary air channel, is characterized in that structural vanes (22) connecting the channel delimitation casings (2, 10, 14, 5) with each other, alternate with aerodynamic vanes (20) for guiding the gases on a common circumference of the engine bypass air channel (8), and in that the structural channels branch out between the two channels. The resulting advantages are simplicity of construction associated with a reduction in the space required for housing the channels and good resistance without notable increase of the total mass.

Abstract: Screw or nut braking rings and mountings established with the rings include a nut having an upper portion hollowed from a circular throat. Slits divide the upper portion into blocks by cutting the throat. A shape-memory alloy ring is housed in the throat so as to retighten the blocks on the threaded portion of the mounting and thus tighten it. The ring exhibits a change between the tightening state and a mounting state where it is free in the throat and can be easily mounted.

Abstract: Device for controlling pivoting blades or variable pitch blades (3) in a turbine in which the control ring (10) rotates under the effect of an angled cam (15) controlled by a system with a connecting rod (22) and crank (21). This system imposes a non-linear rotation law between the blades (3) and the crank (21).

Abstract: A device for assembling a circular stage of pivoting vanes and composed of a ring for retaining bushes in which the pivots of the vanes rotate. The ring is composed of sectors extending between the pivots and connected together by a circular rail. A further ring separate from the rail or integrated with the latter is engaged in throats of the pivots so as to retain them against an axial movement.

Abstract: A fixing arrangement for axially fixing a blade in position on a rotor disk of a turbomachine rotor includes a relatively flexible locking wedge inserted between the root of the blade and the bottom of the axial groove in the periphery of the rotor disk in which the root is received in a radially interlocking manner, the locking wedge having a retaining hook which is received in a groove in the blade root to hold the locking wedge in position. In one embodiment the locking wedge holds a plate in position in the recesses defined by undercut projections on the upstream face of the blade root and the rotor disk to prevent axial movement the blade relative to the disk.

Abstract: A turbine engine includes a ferrule formed of a plurality of ferrule elements in the shape of circular sectors, each bearing on one internal face thereof fixed vanes and a circular housing surrounding the ferrule. The turbine has a support ring including a plurality of circular ring sectors each secured to the housing and having a U-shaped section whose opening is directed towards the ferrule, each ferrule element includes a hooking mechanism (9a) to be introduced into the opening of at least one ring sector so as to integrally connect the ring sector and the ferrule element.

Abstract: A turbine engine stator has a metal casing surrounding an envelope carrying bearings for the pivots of pivoting blades. A control mechanism for setting the position of the blades includes a radial spindle to which are transmitted the thrust forces of the gases, the envelope being advantageously formed from angular sectors of axially juxtaposed flanges or rings and which are not loaded. Therefore, the bearings are not subject to wear giving rise to gas leaks and efficiency losses. Advantageously, the envelope is made from a composite material.

Abstract: A system for retaining and sealing vanes and composed of an flange provided with a throat on tabs which are interlaced in other tabs, also provided with throats of the vane feet. An elastic joint is engaged in the throats and a disk throat and keeps the elements of the flange and the vanes in an axial position.

Abstract: A removable inspection hole plug for sealing a plurality of inspection holes formed in a double-walled enclosure is disclosed in which individual sealing units are disposed in each of the inspection holes, with the individual sealing units linked together by a link rod pivotally attached to each of the sealing units. A seal is provided on each of the sealing units which slideably engages a wall defining the inspection hole and the link rod may be attached to the sealing units by a ball and socket swivel joint. One of the sealing units is attached to a housing which is, in turn, removably attached to the enclosure such that the sealing unit may undergo limited axial movement relative to the housing. This accommodates differential thermal expansion between the walls of the enclosures and also facilitates removal of the inspection hole plug by merely unfastening the housing from the enclosure and removing the housing along with the sealing units.

Abstract: Variable phase vane provided with a composite pivot having a joining piece for receiving the control pieces. The joining piece is made of a material less dense than the actual pivot. These two elements are force-fitted without using any weld or mechanical linking device.

Abstract: An annular gasket includes, at least partially conically shaped portion and is supported on a rotor via three bearing surfaces. The conical shape makes it possible to reject the center of gravity of the sections of the rotor which provokes substantial rotational movement when centrifugal forces exist and allows for an improved imperviousness via the internal and external bearings. This invention is applicable for the rotors of aircraft engines provided with axial broachings in which blade feet are able to slide.

Abstract: A device for ensuring the sealing in a rotary machine between a rotor and fixed blade stages.Blade edges are joined by rings carrying circular seals in slots. Springs force the seals in the longitudinal direction towards transverse faces of reinforcements of the rotor.A turbulence-free gas flow is obtained as a result of the total seal obtained by the seals (19). Moreover, the rotor can be constructed with a substantially rectilinear ferrule which only induces limited stress concentrations.

Abstract: A sealing structure for a gas turbine blade which pivots about a pivot shaft. A split ring is located in a groove on the shaft, in which the ring can be embedded and held by a bush. When the blade is fitted, the bush abuts against a wall of the stator, slides on the pivot shaft and frees the ring, which expands and forms the seal. The invention relates to gas turbines where the stator blades have a variable setting.

Abstract: A sealing and retention device for the blades of a rotor which engage with axial pin settings of the rotor wherein the device includes, in a first embodiment, a flange in the shape of a circular collar which engages the rotor and a locking ring which engages the blades and the flange wherein the locking ring has a conical portion which engages a first protuberance portion of the blades such that upon centrifugal sliding of the locking ring in a radially outward direction, the locking ring is axially displaced toward the flange. The device may also include a conical crest located on the rotor and the flange may have a conical surface for engaging the conical crest of the rotor.

Abstract: A turboshaft engine in which the stator comprises an outer casing surrounding a ring formed by a number of ring elements each having an apertured rib which spaces the element from the casing, the ribs dividing the space between the casing and the ring into separate compartments, and each rib having a sealing element disposed alongside it to cover the apertures and seal one compartment from the next. The casing and the ring are fixed together by virtue of bolts which have their axes inclined to the radial direction so that tightening the bolts causes the casing to press radially on the sealing elements at the same time as pressing them axially against the respective ribs.

Abstract: A stemmed blade for flow-straightener blading of a gas turbine engine includes at least one shank at the head of the blade forming a stem for use in fixing the blade. The shank has a notched portion situated adjacent the head of the blade and an end portion separated from the notched portion by a zone of lower tensile strength. Fixing of the blade to the engine casing is carried out by fitting the blade in position with the shank projecting radially outwards through a hole in the casing and then crimping a bush on to the notched portion of the shank using a suitable crimping tool which exerts a compressive force on the bush while exerting a traction force on the end of the shank until the zone of lower tensile strength breaks.

Abstract: A gas turbine compressor casing has two inner and outer envelopes forming at least one closed cavity and a locking or clamping ring having a thermal inertia higher than that of the envelopes and mounted in the closed cavity in such a way as to limit its contraction during a lowering of the temperature. The thermal inertia difference can be obtained by using for the locking ring a material having a thermal expansion coefficient lower than the coefficient of the envelopes. It can also be controlled by a ventilation means device for ensuring hot air flow in the cavity.