Abstract: A variable area, convergent-divergent (10) nozzle for directing the flow of exhaust gas from an aircraft turbine engine to achieve thrust vectoring about yaw, pitch and roll axes includes a convergent section (16) and a divergent section (18) each comprised of hingedly connected planar members (201-214, 301-322) selectively positioned by actuators (101-114) for defining deformable gas directing flow ducts.

Abstract: A seal assembly (28) is provided for sealing between a static sidewall (12), a rotating first member having a flat and annular surface (22) disposed therein, and a concentric rim (34) disposed between the sidewall (12) and first member (22). The rim (34) is supportably secured to an arcuate hood (18) which extends axially from the rim (34).

Abstract: Control means and method for steering an aircraft is disclosed. The aircraft includes engines positioned on opposite sides of its longitudinal axis. The method comprises: selecting an aircraft heading; sensing a deviation from said heading; and varying the thrust of at least one engine in response to the sense deviation.

Abstract: A convergent/divergent gas turbine engine exhaust nozzle having reverse thrust capability includes a concentric flap (22) and arc valve (36) pivotable about a common axis (34). A method and linkage (48) schedule the opening of the valve (36) in response to rotation of the flap (22) into a blocking position with respect to the normally aftward flow of the exhaust gas (12). The arc valve (36) is accelerated by the linkage (48) to full opening speed prior to unsealing an alternate, thrust reversing flow passage (38).

Abstract: An internal combustion propulsion engine comprises a spherical engine body having radially projecting exhaust nozzle extending from its surface. The spherical engine body is adjustably supported in a complementarily mating socket for unrestricted positioning of the body, for selectively directing the flow of combustion gases emanating from the exhaust nozzle and thus channeling the direction of thrust generated thereby as required. A convergently conical valve member is mounted on the rod of a piston cylinder coaxially with the corresponding divergently conical opening of the exhaust nozzle, the valve member being positioned adjustably projecting into the outlet end of the complementarily mating exhaust opening in direct confrontation with the combustion gases flowing therefrom. Means for positioning the valve member to regulate the distance between valve member and exhaust opening walls are provided to adjust selectively the rate of exhaust flow and thus the magnitude of thrust force developed.

Abstract: A transverse pivotable flap is cantilevered between movable sidewall members (10) which include a stub flap (14). A removable central flap portion (18) is secured between the stub flats (10) by a pair of joints (26) having alternating lug sets 28, 30, secured by respective elongated pins (32, 34). Flow area (40) is provided to conduct internal cooling air (16) into the central flap portion (18).

Abstract: An impulse propulsion unit or pulse-generating impeller mechanism for the lateral acceleration of a projectile, including a hollow cylindrical member, having an outer shell surface which is passed through by nozzles which are peripherally offset relative to each other, and each of which connects into a propellant chamber in the interior of the hollow-cylindrical shell or casing. The propellant chamber is in the shape of an axially elongated section of the hollow wall of a cylinder in which the annular space between the cylindrical inner and outer walls is subdivided through the intermediary of radial separating walls into peripherally neighboring chamber.

Abstract: An exhaust nozzle for a gas turbine engine comprising a duct 17(c) extending along an axis and having at a dowstream end thereof a mechanism for varying the geometry and area of the nozzle. The mechanism 28 comprises an axially translatable member 28 which has a face 29 extending in a direction transverse to the axis of the duct 17(c) against which pressurized gases flowing through the duct acts to balance out the loads on the flaps. A plurality of flaps 38,43 are spaced circumferentially around the axis of the duct. The flaps 38 are pivotally attached to the axially translatable member 28 and are provided with a cam follower 40 that co-operates with a cam 37. The cams 37 are fixed relative to the duct 17(c) and thereby defines the attitude of each flap 38 relative to the member 28. Seal plates 41 and 45 cover the gaps between adjacent flaps 38 and 43 to the seal plates 45. A plurality of struts interconnect the member 28 and the second flaps of the pivotal attachment of the flaps 43 to the flap 38.

Abstract: A thrust reversing system for controlling the fan gases from a thrust producing aircraft engine. The system comprises a first group of blocker doors surrounding the upper longitudinal portion of the engine fan duct; a second group of blocker doors positioned rearward of the first group surrounding the entire engine fan duct; mechanism is provided for translating an upper movable fairing and a lower sleeve section which during translating provides an upwardly directed opening from the fan duct through gas-directing cascades and deploys the blocker doors from a stowed duct wall lining position to a deployed fan gas blocking deployed position.

Abstract: A vectorable nozzle 17 comprising a fixed first duct 21 a rotatable second duct 22 scarfed at its rear end and a rotatable third duct 23 scarfed at its front end. The second and third ducts 22,23 are mounted in bearings 24,26 respectively and the bearing 26 is constrained to swing bodily about trunnions 29, the axis of which lies transverse to the ducts 22,23, and a screw jack 32 is provided to rotate the bearing 26 about the trunnions 29. The second and third ducts 22,23 are provided with means to rotate them in opposite directions in syncronism with the rotation of the bearing 26 in the trunnion 29.

Abstract: Ducted fan propulsion unit for aircraft has a main duct 3 containing a reversible pitch fan 1 rearward of which is provided a flow splitter 13 dividing the main duct into radially outer and inner branch ducts 3A, 3B. A radial passage 15 in the splitter connects the branch ducts and divides the splitter into front and rear parts 13A, 13B. The part of the inner branch duct forward of the radial passage contains an array of stator vanes 12B and has outer and inner wall surfaces 3B1,3B2 both of progressively reducing diameter to urge the flow through that branch duct toward the inlet of a compressor 8 of yet smaller diameter. Stator vanes 12A in the outer branch duct are arranged forward of the radial passage. The arrangement favors a relatively low axial length of the powerplant.

Abstract: A variable geometry gas turbine engine exhaust nozzle is disclosed wherein the inner surface of the nozzle housing and the surface of the tail plug are defined by two sets of hinged together axially extending elements and the nozzle housing outer surface is defined by a single set of axially extending elements. Viewed in the transverse direction, the elements are of an annular geometry with adjacent elements circumferentially overlapping one another to define an annular exhaust duct. A set of hydraulically operated drive units, connected for radial displacement of the juncture between the two sets of elements that define the nozzle housing inner surface, provides rapid control over the nozzle throat diameter. A set of gear driven drive units controls axial displacement of the forward end of the elements defining the nozzle housing outer surface and drives hinged together annular extending support beams into abutment with the overlapping regions of the nozzle housing inner wall.

Abstract: A jet flow alternator for reversing the flow of a confined fluid stream which includes selectively controlled tubes to cause said stream to flow in either one of two directions under pressure.

Abstract: A gas turbofan engine including a variable pitch fan is provided with flow straightening means which are adapted to reduce fan exit swirl in the forward thrust mode. The flow straightening means are so arranged to produce low losses in the fluid entering a core engine during reverse thrust operation while allowing large supercharging of the core engine during forward thrust operation.

Abstract: A gas turbine engine flight maneuverable nozzle for installation within an aircraft wing or the like is provided with pivotably connected convergent and divergent flaps partially defining an exhaust stream flow path. A third flap, pivotably connected to the divergent flap, partially defines the wing control surface contour. In the cruise and flight maneuver modes, an actuation system provides synchronous movement of the convergent and divergent flaps to control, in a predetermined relationship, the areas of the exhaust stream flow path throat and exit. A vectoring actuator, carried by the main actuator, overrides the main actuator in the flight maneuvering mode and causes the divergent flap to pivot downward, thus deflecting the exhaust stream. Simultaneously, the control surface contour defining flap is repositioned to increase the control surface camber thereby increasing lift. Flow separation from the wing control surface is prevented by the effect of super-circulation due to the exhaust stream.