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

Snecma

Francois E Crozet

Jean-Luc Soupizon

Alain M Lardellier

Georges Mazeaud

Marcel R Soligny

Jean G Bouiller

Robert Kervistin

A stator ring assembly for a turbine comprising a plurality of sections, each section has a first sheet metal portion being connected to a second sheet metal portion, and a support ring of generally S-section defining a radially outer edge portion of the second sheet metal portion co-operating with the support ring.

Turbine stator ring assembly

A clearance control device in an inter-shaft turbojet engine bearing journal placed between a high pressure trunnion and a low pressure trunnion and including inserted between an inner ring and an outer ring, the high pressure trunnion including a series of longitudinal grooves and a series of longitudinal holes which are supplied with oil from an intake and an annular collector in the low pressure trunnion, from which the oil moves by centrifugation through radial holes into an annular recess in the downstream tightening nut of the outer ring, which in turn communicates with the grooves through holes formed in the nut. Clearance in the bearing journal is controlled by cooling the high pressure trunnion at the maximum operating speeds of the turbine via circulating oil. By virtue of an appropriate circuit, the oil supplied by the collector lubricates the bearing and cools the roller bearing journal.

Means for controlling clearance in an intershaft bearing journal of a

A system for cooling a gas turbine by bleeding air from the compressor and channeling the air at the center of the engine towards the turbine in order to cool it. The air is bled from the plane of the disc bearing the blades of the compressor, said disc having radial ducts for the flow of the air. The invention is utilized in gas turbine engines to cool the turbine.

System for cooling a gas turbine by bleeding air from the compressor

Growing community of inventors

Yerres, France

Francois E Crozet