Abstract: A device for positioning and maintaining electric harnesses on the casing of a turbo-jet engine includes harness supports standardized for directions substantially perpendicular to the axis of the turbojet engine and harness supports standardized for directions substantially parallel to the axis of the turbo-jet engine.

Abstract: A rigid link of adjustable length includes a yoke with a transversal stud. The stud is mounted on the yoke with two bearings, each inside a through-orifice in the yoke. The axis of the stud is offset from the axis of the bearings whereby the link includes a stopping device in order to lock the stud in at least two different positions, relative to the yoke.

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: The blade of gas turbine engine compressor of the invention includes a hammer type root to be inserted into a circumferential groove of the rotor of the compressor, a platform (12) integral with the root (11) and supporting an airfoil portion (13), the platform including two edges perpendicular to the axis of the rotor (20, 21) and two curved flanks (22, 23), the curve of the flanks being made out of at least one curve defined by an equation, the curvature centre of the point in the curve whereof the curvature radius is the smallest, being situated within a band (B) central to the platform and accounting for 60% of the width (D) of the platform (12) measured between its parallel rectilinear edges (20, 21), the equation defining the curve being, in the sense of mathematic functions, continuous and with continuous first derivative.

Abstract: The device for positioning and maintaining electric harnesses on the casing of a turbo-jet engine comprises harness supports standardised for directions substantially perpendicular to the axis of the turbojet engine and harness supports standardised for directions substantially parallel to the axis of the turbo-jet engine.

Abstract: The invention concerns a rigid link (10) between a first member and a second member, including a means for adjusting the distance between both members, said link including a yoke (20) with a transversal stud (40), co-operating with a fastening tab on the first member. It is characterised in that the stud (40) is mounted on the yoke (20) by bearing-forming means (42, 44), each inside a recess (23, 25) laid out on the yoke, whereas the axis (40A) of the stud and the axis (42A, respectively 44A) of the bearing-forming means are not confused, whereby the link (10) includes stopping means (22B, 24B) in order to lock the stud in at least two different positions, relative to the yoke.

Abstract: A method for making a blade ring includes producing an outer shell of a blade ring by setting a blank using a plasma-forming process on a frame that is then removed. The tips of the blades are well embedded in the ferrule independently of their profile, such that the aerodynamic performances do not deteriorate.

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 flexible rod (20) is articulated at a first end to a control ring (30) and is fixed at a second end to a pivot of a blade (10) that is to be controlled. At this second end, it is held so that it can rotate without play on the blade pivot by a holding device (44; 52; 54). The articulation device comprise a pivot (24) passing through a first orifice (22) pierced in this first end and engaged in a radial housing (28) of the control ring, the pivot being held in position by a locking ring (34) which has openings (36) for the passage of this pivot and which slides on this control ring. The fixing device comprise a fixing screw (40) passing through a second orifice (38) pierced in the second end of the rod and introduced into a hole (42) of the pivot of the blade that is to be controlled.

Abstract: These objects are achieved by a method of acoustically inspecting a one-piece bladed wheel in which the wheel is driven in rotation; each blade of the wheel is subjected to mechanical excitation; its acoustic response is picked up and a corresponding electrical signal is generated; its frequency response is determined by computing a FFT; the electrical signal and the associated frequency response are stored; the characteristic frequencies of each blade of the wheel are identified; and a wheel is rejected or accepted depending on whether or not the frequency distribution obtained in this way matches a predetermined set of forbidden frequency distributions. Advantageously, an additional step is provided in which the defects of a blade are determined by comparing its frequency response with predetermined frequency responses that are characteristic of various types of defect.

Abstract: The invention relates to hammer-fastener blade-locking device affixing the blades in the channel (2) of a turbojet-engine rotor disk (1) and comprising a case (15) of which the cross-section matches that of the channel (2), further a locking element (16) mounted in radially displaceable manner in a traverse orifice in the case (15) and receivable in part in a lock housing (9a, 9b), and a drive bolt (17) acting on the locking element (16). The locking element (16) comprises stops (32a) sliding in windows (22a) of the case (15). The bolthead (4) is large and is radially affixed between the bottom of the channel (2) and the base (20) of the case (15).

Abstract: These objects are achieved by a method of acoustically inspecting a one-piece bladed wheel in which the wheel is driven in rotation; each blade of the wheel is subjected to mechanical excitation; its acoustic response is picked up and a corresponding electrical signal is generated; its frequency response is determined by computing a FFT; the electrical signal and the associated frequency response are stored; the characteristic frequencies of each blade of the wheel are identified; and a wheel is rejected or accepted depending on whether or not the frequency distribution obtained in this way matches a predetermined set of forbidden frequency distributions. Advantageously, an additional step is provided in which the defects of a blade are determined by comparing its frequency response with predetermined frequency responses that are characteristic of various types of defect.

Abstract: A flexible rod (20) is articulated at a first end to a control ring (30) and is fixed at a second end to a pivot of a blade (10) that is to be controlled. At this second end, it is held so that it can rotate without play on the blade pivot by holding means (44; 52; 54). The articulation means comprise a pivot (24) passing through a first orifice (22) pierced in this first end and engaged in a radial housing (28) of the control ring, the pivot being held in position by a locking ring (34) which has openings (36) for the passage of this pivot and which slides on this control ring. The fixing means comprise a fixing screw (40) passing through a second orifice (38) pierced in the second end of the rod and introduced into a hole (42) of the pivot of the blade that is to be controlled.

Abstract: The invention relates to hammer-fastener blade-locking device affixing the blades in the channel (2) of a turbojet-engine rotor disk (1) and comprising a case (15) of which the cross-section matches that of the channel (2), further a locking element (16) mounted in radially displaceable manner in a traverse orifice in the case (15) and receivable in part in a lock housing (9a, 9b), and a drive bolt (17) acting on the locking element (16). The locking element (16) comprises stops (32a) sliding in windows (22a) of the case (15). The bolthead (4) is large and is radially affixed between the bottom of the channel (2) and the base (20) of the case (15).

Abstract: A system for inspecting internal zones of a machine, such as an engine, comprises an observation device having an optical fiber endoscope, and distribution and guide means including a network of flexible guide sheaths placed in the machine to define a number of different inspection routes along which the endoscope can be guided from an aperture in the machine wall to various predetermined critical internal zones. Preferably the system includes first electrical means implanted in each guide sheath and co-operable with second electrical means secured to the endoscope in order to detect the position thereof in the network and to transmit the position to a monitoring device outside the machine for monitoring and assisting the guidance of the endoscope in the network.

Abstract: The blades (10) of a turbine or a compressor are here fixed to the disk (1) by three roots (7, 8 and 9) inserted in the same number of circular grooves (4, 5 and 6). This assembly makes it possible to provide a good distribution of stresses during functioning.

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 stator for a turbo-engine and a method for mounting the stator serve to improve fixing of the vanes of the stator and resistance of these vanes to impact in the event foreign bodies enter the turbo-engine. The stator includes several vanes radially maintained by their external and internal pivots between an internal ferrule and an external casing. The internal ferrule includes at least one bore intended to receive one of the internal pivots and the external casing includes a mechanism for the radial positioning and locking of the vane so as to make it possible to keep the internal pivot of the vane in the bore.

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.