Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Jacques H Mouchel

Jean-Claude Christian Taillant

Gerard M Mandet

Gerard E Jourdain

Marcel R Soligny

Jean-Paul Lagrange

Jean-Philippe E Richard

Patrick Didier Michel Lestoille

Frederic Chambon

A labyrinth disk includes a main stiffener placed in the middle of the rim immediately below labyrinth elements. Attachment elements are preferably in the form of a bayonet attachment system using teeth fixed on the labyrinth disk crown and teeth fixed on the rotor. Attachment by bolting may optionally be used. The disk may be utilized with turbojets, on the cooling circuit, on the upstream side of the high pressure turbine.

Labyrinth disk with built-in stiffener for turbomachine rotor

The disclosed invention relates to a sealing device for the rotor blades of a gas turbine engine which permits real time adjustment to be made of the clearances between the rotor blade tips and the sealing structure. The sealing shroud around the turbine wheel is formed of sectors, each sector being attached to a monolithic short response time ring and a monolithic long response time ring. Ventilating air from upstream of the turbine wheel is directed onto the rings such that the sectors are caused to radially expand or contract in compliance with the expansion or contraction of the tips of the rotor blades during stabilized and transient engine operational modes. A small positive clearance between the sealing sectors and the blade tips is maintained throughout the range of the engine's operation.

Gas turbine engine rotor blading sealing device

An annular member is attached coaxially to a disk of a turboshaft engine by ounting element comprising two separate sets of interengageable lugs, each set consisting of one ring of equi-angularly spaced lugs on the disk and another ring of equi-angularly spaced lugs on the annular member which is interengageable with the first ring by interleaving and overlapping the lugs of the two rings in bayonet fashion, the two sets of lugs being offset radially from each other and arranged so that they are interengageable simultaneously with each other. In addition the disk and the annular member are provided with substantially cylindrical coaxial surfaces which engage each other to ensure that the annular member is centered on the disk when the two sets of lugs are interengaged to attach the member to the disk.

Fixing arrangement for mounting an annular member on a disk of a

The present invention discloses a device for varying the fluid passage area between adjacent turbine stator vanes. Upstream and downstream baffles are pivotally attached to the turbine casing, such that their distal ends may be extended into and retracted from the fluid passage area, so as to vary the cross section of the throat between adjacent vanes. A control system interconnects all of the baffles so as to synchronize and positively control their movements. The invention finds particular use in an aircraft turbojet engine.

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Paris, France

Jacques H Mouchel