초록 ▼

An ejector nozzle for a turbomachine comprising fixed inner and outer ducts 16,19 to the downstream ends of which is provided mechanism for varying the geometry and area of the nozzle. A plurality of flaps 20, 20(a) which slide in curved tracks 21 are provided to define the throat of the nozzle. An

An ejector nozzle for a turbomachine comprising fixed inner and outer ducts 16,19 to the downstream ends of which is provided mechanism for varying the geometry and area of the nozzle. A plurality of flaps 20, 20(a) which slide in curved tracks 21 are provided to define the throat of the nozzle. An axially movable shroud 25 is provided downstream of the outer duct 19. A plurality of second flaps 23, 23(a) are pivotally attached to the downstream ends of the flaps 20, 20(a) and to the downstream end of the shroud 25. The second flaps 23, 23(a) having openings therein and doors 30 to close the openings 29. Links 31 which are connected to the shroud 25 are used to open and close the doors 30. By sliding the flaps 20, 20(a) in their tracks 21, and translating the shroud axially the geometry of the nozzle can be altered to cater for “dry”, “ reheat”and “ejector”modes of operation. In the “ejector”mode the shroud is moved rearwards to uncover air inlets and the links 31 push open the doors of the nozzle throat. The flaps 20, 20(a) can be moved to a thrust reverse position whereby the hot gases flowing through the nozzle can be redirected out of the air inlet openings. A two dimensional nozzle is also disclosed in which the plurality of flaps 20 are replaced by a pair of mutually confronting arcuate flaps 20 and the circumferential array of flaps 23 is replaced by a pair of flaps 23.

대표청구항 ▼

A nozzle for a gas turbine aero-engine comprising spaced inner and outer ducts, one or more air inlet openings located at the downstream end of the outer duct, a movable shroud extending downstream of the outer duct, a plurality of first flaps each of which is constrained to move along a curved path

A nozzle for a gas turbine aero-engine comprising spaced inner and outer ducts, one or more air inlet openings located at the downstream end of the outer duct, a movable shroud extending downstream of the outer duct, a plurality of first flaps each of which is constrained to move along a curved path, a plurality of second flaps each of which is pivotally attached to the downstream end of one of the first flaps at least some of the second flaps being provided with an opening therein and a door in each opening, each door being pivotally attached at its upstream end to a region adjacent the upstream end of the second flaps, a plurality of links each of which is pivotally attached at one end to the shroud and pivotally attached at its other end to a door, a first actuation means operable on the first flaps to translate them in unison along the curved path thereby to define a convergent throat of the nozzle and simultaneously move the upstream ends of the second flaps, and a second actuation means operable on the shroud to move the shroud to and from a first position, where the shroud obturates the said inlet opening or openings, to and from a second position, downstream of the first position, where the shroud uncovers the said inlet opening or openings, alters the position of the second flaps and simultaneously causes the said links to push the doors open thereby to form a mixer region downstream of the throat whereby air entering the air inlet opening or openings and the openings in the second flaps intermixes with hot gases flowing through the throat of the nozzle.