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

Patrick Kapala

Jean-Pierre L Mareix

Michel S Guimier

Philippe M Paris

Alain J Guibert

Michel M Ribault

Roland M Grateau

Alain J Henu

Florence J Monchois

A turbine casing includes circumferential walls delimiting an annular stream for the flow of gases. The radial arms traversing the stream are completed by a channeling part on the downstream side which is bolted to the arms. The walls are formed of butt-joined tiles assembled together and joined to collars situated on the arms and the channeling parts by riveted ridge tiles. The invention results in a reduction of resistance to the flow of gases, as well as absorption without the production of excessive stresses of the original thermic dilations in the walls.

Turbine casing delimiting an annular gas flow stream divided by radial

The present invention provides a fastener system for attaching a jet engine to a mounting bar requiring access to only one side of the mounting flanges. The fastener remains in place should either the bolt or the hollow pin fracture during operation of the engine. The fastener system has jet engine casing flanges extending on either side of a mounting bar with aligned openings extending through these elements. Hollow sleeves extend through the openings in each of the engine casing flanges with the rear, or downstream sleeve extending through the downstream flange having an internally threaded portion. A hollow pin passes through the interiors of the sleeves and the aperture in the mounting bar and engages the downstream sleeve such that rotation between this sleeve and the hollow pin is prevented. A bolt, having a headed portion, is inserted through the hollow pin at, and is threadingly engaged with, the threaded portion of the rear or downstream sleeve. The headed portion of the bolt bears against a headed portion on the hollow pin to hold the fastener assembly together. An anti-rotation device is applied between the headed portion of the hollow pin and the jet engine casing to prevent inadvertent rotation.

Fastener system for a jet engine mounting

A unitary exhaust gas housing for a turbo-engine comprises an outer ring, two intermediate rings defining the flow path for the hot gases, and an inner ring forming a hub with a hollow annular chamber. A temperature control device is provided including a bleed tube having one end fixed and communicating with the gas flow path for drawing off hot gases therefrom, the other end of the tube passing into the hollow chamber of the hub where it regulates the flow of gases by variation of the clearance j between the end of the tube and the opposing wall of the hub in response to relative radial movements of the tube and the hub according to the thermal states of the assembly.

Turbo-engine exhaust gas housing with temperature control device

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Claye-Souilly, France

Patrick Kapala