초록 ▼

An exhaust nozzle for a gas turbine aero-engine comprising a duct 17(c), a plurality of movable flaps 38,43 for varying the geometry of the nozzle, one or more forwardly and outwardly directed openings 59 located upstream of the flaps 38,43 and a pair of mutually confronting doors 61 each of which i

An exhaust nozzle for a gas turbine aero-engine comprising a duct 17(c), a plurality of movable flaps 38,43 for varying the geometry of the nozzle, one or more forwardly and outwardly directed openings 59 located upstream of the flaps 38,43 and a pair of mutually confronting doors 61 each of which is mounted for rotation about an axis extending transverse to the length of the duct 17(c). The doors 61 are located relative to the duct 17(c) and the openings 59 so that, in a first position, they obturate the openings 59 and mutually confronting surfaces 67 of the doors define therebetween part of the gas flow path through the nozzle, and the doors 61 are movable to a second position, upstream of the first position, where they uncover the openings 59, define, at their upstream ends 68, a reduced area throat for the gas flow path through the nozzle. In the second position the doors 61 also define a divergent part of the gas flow path immediately downstream of the said throat. The reduced pressure downstream of the throat induces ambient air through the openings 59 into the gas flow path through the nozzle. Means 28,35,36 are provided for moving the flaps 38,43 to accommodate the increased gas flow through the nozzle when the said openings 59 are uncovered. In this way the infra red emission of the gas plume exiting from the nozzle is suppressed by the cool air. The doors 61 are movable to a third position where they uncover the openings 59 and co-operate with the flaps 38 to form a thrust reverser.

대표청구항 ▼

An exhaust nozzle for a gas turbine engine comprising a duct and a mechanism for varying the geometry and area of the nozzle, which mechanism includes a plurality of movable flaps which in at least one position define a convergent part of the nozzle, wherein there is provided upstream of the flaps a

An exhaust nozzle for a gas turbine engine comprising a duct and a mechanism for varying the geometry and area of the nozzle, which mechanism includes a plurality of movable flaps which in at least one position define a convergent part of the nozzle, wherein there is provided upstream of the flaps at least two outwardly directed openings in the wall of the duct and a pair of mutually confronting doors which rotate about an axis transverse to the length of the duct, the doors being located relative to the duct, the openings and the flaps, so that, in a first position the doors obturate said at least two openings and provide a substantially unrestricted flow path through the nozzle, in a second position, downstream of the first position, the doors uncover the said openings and co-operate with the flaps when the flaps are in a convergent position, so that the flaps together with the doors provide deflecting surfaces that redirect the flow of gases out through the said openings, and in a third position, upstream of the first position, the doors uncover the openings, define, at their upstream ends a reduced area throat for the gas flow path through the nozzle, and also define a divergent part of the gas flow path immediately downstream of the said throat thereby to reduce the pressure downstream of the throat to induce ambient air through the openings into the gas flow path through the nozzle, and means are provided for moving the flaps to accommodate the increased gas flow through the nozzle when the doors are in said third position.