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

Snecma

Patrick R Derouet

Philippe M Paris

Michel S Guimier

Christian J Cattaneo

Roger U Welaratne

Michel S Lemonnier

Jean Tourneboeuf

Michel C Laroche

A self regulating bleed valve for a gas turbine engine is provided which taps or bleeds a portion of a gas, typically air, from a duct of the gas turbine having a wall bounding the gas flow. The bleed valve has a valve member pivotally attached to the wall such that the valve member extends through a main opening formed in the wall. The valve member has an internal cavity in communication with a gas inlet opening and a gas exhaust opening and is pivotally movable between an extended position wherein the gas inlet opening portion of the valve member extends into the gas flow duct such that the inlet opening faces generally in an upstream direction so as to deflect a portion of gas flow into the internal cavity, and a retracted position wherein the inlet opening extends obliquely, generally parallel, to the gas flow so as to minimize the air tapped or bled from the gas flow. The bleed valve also includes a control device fixedly attached to the valve member which is acted on by the flow of gas to cause the valve member to pivot between its extended and retracted positions, depending upon the speed and pressure of the gas flow. Thus, the self-regulating bleed valve taps or bleeds a generally constant amount of air regardless of the speed or pressure of the gas flow with which the valve is associated.

Self regulating bleed valve

The adjustment of the play separating the stators and the rotor is effected automatically and jointly with adjustment of the phase angle of the stators. For each startor, at least one slug is used, the slug being mounted for sliding in an oblique groove of a bush integral with the stator. A bush, groove and slug arrangement can also be provided for an adjustable stop on the starter to adjust the play between a free extremity of the rotor blade and the adjustable stop on the stator. Pivoting of each stator provokes a systematic modification of the play.

Turbomachine equipped with means for adjusting the play between the

An arrangement for discharging to the atmosphere a jet of fluid released by a pressure relief valve in a pressurized hot fluid circuit of an aircraft, wherein the pressure relief valve is placed near a wall of the aircraft, e.g. the wall of an engine pod, so that any jet of fluid released by the valve is directed towards the wall, and the wall is provided with an orifice at the place where the fluid jet would hit the wall, the orifice being closed by a consumable plug designed to melt, at least partly, as a result of the heat of the fluid jet so that the jet is able to discharge through at least a part of the orifice.

Discharge arrangement for a pressure relief valve in a pressurized hot

In a device for breaking up ice formed on a contoured surface before it reaches a dangerous thickness, a flexible and porous membrane is fixed on the contoured surface along airtight lines of contact defining elementary chambers, each of which communicates with a main chamber inside the contoured surface. The main chamber is fed continuously by a source of hot gases. The closing up of the pores of the membrane by ice causes an inflation of the elementary chambers and a deformation of the membrane. Application is to the cowl of the air intake of a turbojet engine and to a detector used for the control of a de-icing device of any type.

Growing community of inventors

Soignolles en Brie, France

Patrick R Derouet