GB2155552A

GB2155552A - Adjustable jet propulsion nozzle

Info

Publication number: GB2155552A
Application number: GB08105843A
Authority: GB
Inventors: Clifford Stanley Woodward
Original assignee: Rolls Royce PLC
Current assignee: Rolls Royce PLC
Priority date: 1981-02-24
Filing date: 1981-02-24
Publication date: 1985-09-25
Also published as: US4641782A; GB2155552B

Description

1 GB 2 155 552A 1

SPECIFICATION

Jet propulsion nozzle This invention relates to a jet propulsion nozzle.

It is an object of this invention to provide improved means for converting the nozzle between a convergent and convergent divergent configuration.

According to this invention there is pro vided jet propulsion nozzle comprising a pair of mutually confronting first panels extending transversely between the walls, both of the first panels being supported on the walls for pivotal movement about a common first axis lying between the first panels and extending transversely between the walls, a pair of mu tually confronting second panels extending transversely between the walls, each second panel being situated adjacent a respective said first panel and being supported thereon for pivotal motion about a second axis parallel to the first axis, said walls and panels defining between them a flow duct, first means for pivoting each first panel about the associated first axis and second means for pivoting each second panel about the associated ' second axis independently of the pivotal position of the first panels, thereby to enable the panels to be moved into positions wherein said duct is respectively convergent and convergent divergent.

An example of a nozzle according to this invention will now be described with reference 100 to the accompanying drawings wherein:

Figure 1 is a perspective of the nozzle.

Figure 2 is a section on the line 11-11 in Fig.

1.

Figures 3, 4 and 5 are views similar to Fig. 105 2 but showing different operational positions.

Referring to Fig. 1, the nozzle, generally denoted 10, comprises two side walls 11 which extend rearwardly from a nacelle 12 secured to the underside of an aircraft wing 13 and housing a gas turbine engine (not shown).

Referring now also to Fig. 2, the nozzle 10 comprises a pair of mutually confronting first panels 14 extending transversely between the 115 walls 11 and spaced apart to opposite sides of the nozzle main axis denoted 15. Each panel 14 is secured to a pair of plates 16 lying adjacent the respective walls 11 and having pivot elements 17 whereby the panel is sup ported on the walls 11 for pivotal motion about an axis 18 extending transversely be tween the walls 11 and through the axis 15.

The elements 17 extend through the walls 11 and are connected at the outside thereof to levers and hydraulic actuators 19 for effecting the pivotal motion of the panels 14.

The nozzle 10 further comprises a pair of second panels 20 extending transversely be tween the walls 11 and spaced apart to 130 opposite sides of the axis 15. Each panel 20 is situated adjacent one of the panels 14 downstream thereof and the panels 14, 20 are connected at their adjacent edges by pivots 21 whose axes are parallel to the axis 18. Each panel 20 is provided with a pin 22 extending through an opening 23 in the adjacent wall 11 and connected by an actuator 24 to one end 25 of a belicrank lever 26 supported on the adjacent wall for pivotal motion about an axis 27. The other end 28 of the lever 26 is connected to an actuator 29 mounted on the adjacent wall 11 at 30. The actuators 24 define links whereby the panels 20 are supported to follow the pivotal motion of the panels 14. The actuators 24 are also a means whereby the panels 20 can be turned about the pivots 21 independently of one another and of the panels 14. The actuator 29, acting through the lever 26, is a means for pivoting the panels 20 about the pivots 21 simultaneously and in the same angular sense.

The panels 14, 20 and the walls 11 define a flow duct 31 for the combustion products from the engine, the walls being the lateral, and the panels 14,20 being the upper and lower confines of that duct. The upstream end of the nozzle 10 is defined at members 32 fixedly connecting the upper and lower portions of the walls 11. Downstream of each member 32 is provided a member 33 also fixedly connecting the walls 11. Between each pair of members 32, 33 is provided an opening 34 which is closed at the interior of the nozzle by the adjacent panel 14 and at the exterior of the nozzle by a panel 35 hinged to the member 33. The opening 34 can be opened by pivoting the panels 14, 35, the latter panel being pivoted by an actuator 36.

Fig. 2 shows the nozzle 10 in the convergent mode, that is, surfaces 1 4A of the panels 14 facing the interior of the duct 31 are parallel while surfaces 20A of the panels facing the interior of the duct 31 are convergent. Alternatively, the convergent mode is attainable by operating the actuators 19 for the surfaces 14A to be convergent while the actuators 24 are operated to move the panels 20 for the surfaces 20A to be parallel, this being shown at 14AX, 20AX.

If the nozzle 10 is to be deployed in a convergent-divergent mode, Fig. 3, the actuators 19 are extended to move the panels 14 so that the surfaces 1 4A are convergent, and the actuators 24 are extended to move the panels 20 for the surfaces 20A to become divergent.

If the nozzle 10 is to be deployed in a downwardly vectored mode, Fig. 4, the actuator 29 is contracted so that the lever 26 acts on both actuators 24 to move both panels 20 downwards for the surfaces 20A to attain a downward and rearward attitude relative to the axis 15. Either one of the panels 24 can 2 GB 2 155 552A 2 be moved by its associated actuator 24 to achieve a required degree of convergence of the surfaces 20A in this mode.

If the nozzle 10 is to be deployed in a thrust reversing mode, Fig. 5, the actuators 19 are extended to move the panels 14 rearwards sufficiently far to clear the openings 34, and the actuators 36 are extended to move the panels 35 into the open position. In this mode, the actuators 24 are preferably contracted to the maximum extent to avoid any unduly small angle between the adjacent panels 14, 20.

Claims

1. jet propulsion nozzle comprising a pair of mutually confronting walls, a pair of mutually confronting first panels extending transversely between the walls, both of the first panels being supported on the walls for pivotal movement about a common first axis lying between the first panels and extending transversely between the walls, a pair of mutually confronting second panels extending transversely between the walls, each second panel being situated adjacent a respective said first panel and being supported thereon for pivotal motion about a second axis parallel to the first axis, said walls and panels defining between them a flow duct, first means for pivoting each first panel about the associated first axis and second means for pivoting each second panel about the associated second axis independently of the pivotal position of the first panels, thereby to enable the panels to be moved into positions wherein said duct is respectively convergent and convergentdivergent.

2. Nozzle according to Claim 1 wherein the first panels are pivotable between a first position in which the panels are substantially in line with the mean direction of flow through the duct and a second position in which the panels are transverse to said direc- tion thereby to oppose flow, and the nozzle comprising structure defining openings positioned to be closed by the first panels when in said first position and to be opened by movement of the panels into the second position.

3. Nozzle according to Claim 1 or Claim 2 comprising means for pivoting the second panels jointly thereby to vary the direction of efflux from the nozzle.

4. Jet propulsion nozzle substantially as described herein with reference to the accompanying drawings.

Printed in the United Kingdom for Her Majesty's Stationery Office, Dd 8818935, 1985, 4235. Published at The Patent Office. 25 Southampton Buildings, London. WC2A lAY, from which copies may be obtained.