Societe De Construction Des Avions Hurel-dubois

Verbena Corporation N.v.

Pascal J Meyer

Jean Ren&eacute; Bickart

Robert R Standish

Joel Frank

The invention concerns a spray nozzle comprising a central swirl chamber ( ) in which the fluid to be sprayed penetrates by tangential channels ( ) producing a swirl axis perpendicular to the longitudinal axis (I&mdash;I). The fluid comes out of the swirl chamber ( ) through a coaxial outlet passage ( ). The nozzle comprises a rear coaxial recess ( ) dimensioned and shaped so as to inhibit any residual outflow of fluid through the coaxial outlet passage ( ) when the fluid supply is interrupted at the spray nozzle inlet ( ).

Spray nozzle with static means for inhibiting outflow

A spray nozzle includes a central swirl chamber (,), receiving the fluid tangentially through lateral fluid inlet channels (,) from a peripheral front cavity (,), and projecting the fluid in outlet through a coaxial outlet passage (,). The coaxial outlet passage (,), the central swirl chamber (,) and the fluid inlet channels (,) are made up of ribs and recesses in a front plate (,) engaged between a nozzle (,) hollow body and a rear core (,) which is itself formed by a core rear body (,) and a rear plate (,) with rear axial recess (,). Thus one can economically produce fluid inlet channels (,) and a central swirl chamber (,) with coaxial outlet passage (,) and rear axial recess (,) with very accurate dimensions, thereby ensuring satisfactory reproducibility of the features of the fluid spray jet at the outlet.

Spray nozzle with directly mounted plate

The reverser includes a partition (28) exhibiting openings (19) and separating the cavity (16) which exists, when the doors (2) are in the closed position, between the front part (7) of the internal panel (11) of the door and the stream of gaseous flow (15) flowing in direct jet mode through the jet pipe CA, thus overcoming the aerodynamic losses which result from the presence of this cavity.

Specially configured deflection edge thrust reverser for jet engine

An improvement made to jet-engine thrust reversers and, more particularly, to reversers called tilting-door reversers. The doors are equipped, on their upstream portion, with a flow-deflecting overlay 90 which, in the open-door position, is in a position close to a line PM parallel to the axis of the engine 1, the overlay making with the inner door skin an angle B greater than 90.degree., preferably between 105.degree. and 110.degree.. The invention is more particularly applicable to dual-flow engines.

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Clamart, France

Pascal J Meyer