Abstract: In a V/STOL aircraft having a vectorable exhaust device in the form of a cascade of variable pitch nozzle vanes, an operating mechanism for effecting coordinated pivotal movement of the vanes is provided to vector engine thrust. The operating mechanism includes a plurality of elongate pushrods arranged in end to end abutment with a corresponding plurality of vane operating levers interspaced between the pushrods. The vanes are rotated about spanwise axes by translation of the pushrods in a direction normal to the vane axes. For a given actuating input the vanes rotate by progressively different amounts so that the combined nozzle throat area remains substantially unchanged throughout the nozzle vectoring range.

Abstract: In a VTOL or STOL aircraft in which a lift device is housed internally within the aircraft fuselage or wing an outlet nozzle is stowable within the lift device exit aperture. A pair of doors, which when closed conceal the aperture from the sides of the nozzle, and a third folding member form the forward side of the nozzle and support a frame carrying variable vanes which vector the lift thrust.

Abstract: A fluid flow duct such as the jet pipe of an aircraft gas turbine powerplant has alternatively selectable outlets so that thrust may be directed through either an axial discharge nozzle or through vectorable lift nozzles. Side outlets in the jet pipe leads to lift nozzle on port and starboard sides of the aircraft. Nozzle selection is made by means of a composite diverter valve comprising a sleeve valve to cover the side outlets and a segmented blocker valve to close the jet pipe and deflect engine exhaust through the side outlets. The blocker valve segments are carried on the sleeve valve for simultaneous deployment. The segments are adapted to delay the opening of the side outlets as the sleeve valve translates axially. Specially extended segments co-operate with a shaped duct wall adjacent the outlets to delay their uncovering.

Abstract: A diverter valve arrangement for a fluid flow duct having selectively alternative outlets. In order to avoid an over-area condition during transition an additional valve is provided to delay the effect of operating the main changeover valve. The diverter valve comprises a sleeve valve which covers/uncovers side outlet ports in the duct wall and a blocker valve made up of a plurality of segments pivoted to the inside of the sleeve valve. As the sleeve translates to uncover the side ports the blocker valve leaves deploy to obstruct axial flow. The additional sleeve valve acts as a shuttle and temporarily follows the main sleeve to delay uncovering the side ports.

Abstract: A variable geometry nozzle for a gas turbine engine in which a circumferential array of flaps are pivotally connected to the engine by their upstream ends, the flaps comprising interdigitated flexible and rigid flaps. The geometry of the nozzle is varied by drawing together the side edges of adjacent flexible flaps which causes pivoting of both the rigid and flexible flaps and a change in the curvature of the flexible flaps. The rigid flaps seal the spaces between the side edges of adjacent flexible flaps. A modification is shown using auxiliary radially outwardly flared flaps to provide convergent divergent geometry.

Abstract: A mounting arrangement for a composite material flameholder in teh reheat system of a gas turbine engine provides for a flameholder to be suspended from a flameholder bracket in the jet pipe by a means of pivotal mounting and to be restrained from movement by a leaf spring mounted trunnion attached between the bracket and the flameholder at a second mounting spaced a short distance away from the first. The resilience of the leaf spring allows movement in directions parallel to a line through the axes of the two mountings in order to accommodate differential thermal growth of the composite flameholders and their metallic supporting structure.

Abstract: A reheat system for a gas turbine engine includes a plurality of radial flameholders constructed of non-metallic material, such as a ceramic composite or carbon/carbon reinforced material, mounted on a metallic support structure in the engine jet pipe. The metallic support structure may be cooled by air from the engine bypass duct, and the non-metallic flameholders are capable of withstanding higher exhaust gas temperatures in the jet exhaust beyond the capability of currently used metal alloy materials. However, the mounting assembly must be capable of absorbing the considerable differential thermal expansion which will take place.

Abstract: A connector for conveying hydraulic pressure from a relatively fixed source to a relatively moveable hydraulically actuable arrangement is described. The connector comprises a telescoping assembly of hollow members opposite ends of which have means for joining the connector to hydraulic lines. A first of the telescoping members is formed with an integral annular chamber which is swept by annular piston means carried by a second of the telescoping members interengaged with the first. Dimensions are chosen so that a change in the internal volume of the telescoping members is compensated by the volume displaced by movement of the piston in the chamber whereby the total internal volume of the system remains constant.

Abstract: A vectorable propulsion nozzle has first and second ducts 10, 16 attached to each other by gimbal attachment means 18 to allow universal swivelling of vectoring in any lateral direction. The second duct 16 comprises a supporting ring 28 which has a plurality of guide means 36 in which arcuate ribs 41 are slidably mounted. Each rib 41 is formed integrally with a master flap 38 which together with slave flaps 44 define the geometry and outlet area of the nozzle. To facilitate varying the throat area of the nozzle the flaps 38, 44 are moved bodily along the guide means by actuators. The area of the nozzle can thus be altered independently of the swivelling of the second duct 16. The supporting ring 28 also has formed therein a plurality of openings 30 for thrust reversing which are uncovered when reverser doors 32 are deployed.

Abstract: A variable flow area nozzle suitable for a gas turbine engine equipped with afterburning means comprises first and second ducts, the second duct pivotably mounted to the first and extending downstream from the first duct thereby defining a fluid flow therethrough. The first duct includes a lip which extends downstream through the second duct, the lip being of width corresponding to the internal width of the second duct thereby defining an exit orifice the flow area of which is controlled by the position of the second duct with respect to the lip. The nozzle further comprises a pressurizable chamber located on a side of the lip remote from the fluid flow path, the chamber being defined at least in part by the lip and a portion of the second duct. A vent hole in the lip is provided for admitting fluid into the chamber from fluid flow path.

Abstract: One major problem associated with the design of high-speed vertical take-off or landing aircraft is the requirement to have the front vectorable nozzles of the aircraft deployed in the airstream which passes over the fuselage of the aircraft when they are in use. The nozzles tend to act as air brakes and thus seriously effect the forward speed and flight characteristics of the aircraft. This invention attempts to solve this problem by providing a vectorable nozzle which is rotatable about one axis between a first position in which it is stowed inside a cavity within the aircraft fuselage when not required, and a second position in which it is deployed into the airstream when required.

Abstract: A valve for selectively changing the direction of flow of working fluid through a variable cycle engine which comprises a first and second compressor 14,16 spaced along a flow duct 26. The duct 26 having air intakes 42 leading to the second compressor 16 and outlets leading to nozzles 44. The valve comprising a sleeve 30 axially movable along the duct. The sleeve 30 having openings 31 in it in which are located doors 32. Links 36 are connected to each of the doors 32 so that as the sleeve 30 is moved axially the doors 32 are pulled open to open the air inlets 42 and the outlets and simultaneously obturate the flow duct 26. In a second position of the sleeve 30 the doors 32 and the sleeve 30 close off the air inlets and outlets and open the duct to allow the first compressor to supercharge the second compressor.

Abstract: Jet propulsion powerplant comprising a gas producer 11 having a first flow duct 12 for receiving the output of the gas producer 11. The flow duct 12 includes a nozzle 13 having a center body 16 which has an upstream part 17 and a downstream part 20. Motors 22 are provided for expanding and contracting the downstream part 20 relative to the upstream part 17. A second flow duct 33 having an inlet 30 openable to airflow and connected to the interior of said upstream part 17 is provided. An outlet 24 from the interior of the upstream part 17, is provided at the downstream end of the upstream part 17. The outlet 24 opens into the interior of the first flow duct 12 by contracting the downstream part 20 relative to the upstream part 17. By such an arrangement, infrared radiation may be suppressed when necessary by opening the inlet for air flow and controlling the upstream and downstream parts so that there can be a mixing of air with exhaust gases which reduces the mean temperature of the exhaust gases.

Abstract: 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.

Abstract: An ejector nozzle for a turbomachine comprising fixed inner and outer ducts 16,19 to the downstream ends of which is provided a mechanism for varying the geometry and area of the nozzle. A plurality of pivotal flaps 20,20a are mounted on the inner duct 16 for rotation about their pivots. An axially movable shroud 25 is provided downstream of the outer duct 19. A plurality of second flaps 23,23a are pivotally attached to the first flaps 20,20a and slide relative to the shroud 25. The second flaps 23 have openings therein and doors 30 to close the openings. Links 31 which are connected to the shroud 25 are used to open and close the doors. Rotation of the flaps 20,20a and axial movement of the shroud 25 alters the geometry of the nozzle and can be used to open air inlet openings on the downstream side of the flaps 20,20a and also open the doors 30 in the second flaps 23,23 a to provide a mixer to reduce infra-red radiation emitted by the hot gas plume from the engine.

Abstract: 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.

Abstract: 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.

Abstract: A nozzle for a gas turbine aero engine comprises two spaced inner and outer ducts 16,19 with a mechanism for varying the geometry of the nozzle exit. Air inlet openings 21 are provided downstream of the ducts. The mechanism comprises two pairs of mutually confronting doors 22,23 downstream of the ducts 16,19 and two pairs of pivotal flaps 26,27 mounted downstream of the doors 22,23. The inner doors 23 are provided with a convoluted mixer chute assembly 24 and serve to define the throat of the nozzle whereas the outer doors 22 serve to close off the air inlets 21 or open them, and also form a thrust reverser. The pressures acting on flaps 26,27 cause them to readjust their attitude to form a parallel or divergent part of the nozzle.

Abstract: A variable geometry ejector nozzle for a gas turbine aero engine, in which a primary nozzle and convergent throat is defined by a pair of mutually confronting flaps 30 which are of corrugated form and have slots in them, and a pair of corrugated fairing flaps 33. The fairing flaps 33 are mounted on pivotal links 31 which also carry a pair of flaps 32 that define part of the downstream boundary of the nozzle flow path. A pair of outer flaps 35 interconnect the upstream ends to the flaps 33 to the downstream ends of the flaps 32. To define an ejector nozzle, the flaps 30 are rotated to define in appropriate area throat and the flaps 32,33 and 35 are swung bodily outward to form an air intake scoop 38. The flaps 30 and 33 can be rotated to a position where they form a thrust reverser to deflect gases flowing through the nozzle out through outlets 29.

Abstract: A gas turbine powerplant has an inner casing (4A) containing a gas turbine engine, an outer casing (5) surrounding the inner casing, a fan driven by the engine and driving air through an annular duct defined between the casings. The powerplant is connected to an aircraft fuselage (1) by a front mounting (9,9A,9B,9C) and by a rear mounting (8,10,17,18). The front and rear mountings react lateral forces on the powerplant. The powerplant includes a thrust reverser (11) situated rearwards of the rear mounting and supported by a ring (18) lying in the annulus of the outer casing and forming part of the rear mounting. At each side of the powerplant there is provided a tie (14,15) which connects the inner casing at a joint (6,16A) adjacent the front mounting to the ring of the rear mounting. The ties therefore lie oblique to the main engine axis. The ties react the forward and reverse thrusts of the powerplant.