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

Jean-Paul Lagrange

Gerard E Jourdain

Jean-Louis Charbonnel

Georges Mazeaud

Marcel R Soligny

Gerard M Mandet

Jean-Max M Silhouette

Jacques H Mouchel

Christian J Cattaneo

Jean-Philippe E Richard

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

A device for maintaining clearance between rotor blades and a surrounding housing is disclosed in which the device radially expands or contracts to match the expansion or contraction of the rotor blade tips. The expansion or contraction of the device is achieved by thermal transfer between the device and the gasses passing over the rotor blades. The device has several alternating segments having different thermal characteristics such that the expansion/contraction characteristics of the rotor blade can be accurately matched by the device.

Device for monitoring clearance between rotor blades and a housing

A bearing for turbojet engines, placed between a high pressure journal and a low pressure journal is in the form of a roller bearing with rollers, and an inner bushing and an outer bushing, all contained in a box mounted on the low pressure journal. A nut maintains the bushing on the high pressure journal and has an annular recess arranged to receive oil through an inlet dividing it by means of vanes, through axial holes on the bushing, toward the roller bearing for its lubrication and cooling, and through radial holes, by means of the centrifugal effect, to an annular collector formed in the box. The collector has a plurality of stabilizing vanes and its radial height determines the feed pressure, by means of calibrated holes in the box, of a film of oil in an axial space constituted between the bushing and the box, in order to assure therein the damping of vibrations.

Inter-shaft bearing for multibody turbojet engines with damping by a

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Le Chatelet en Brie, France

Jean-Paul Lagrange