Abstract: A turbomachinery rotor comprising a rotatable hub and a composite blade attached to the periphery thereof. The blade comprises a plurality of bonded filament laminates extending between, and wrapped around, a pair of hollow, semicylindrical inserts at the blade root. The laminates are bonded to the inserts so as to form a cylindrical blade root profile for insertion into a complementary cylindrical groove in the periphery of the hub. A slotted pin is positioned within the inserts to prevent the root from collapsing under loadings and to retain the blade in the hub.

Abstract: A blade for use in a fluid flow machine such as a compressor or fan is fabricated by laying up and bonding together a plurality of filament laminates. The filaments of at least a portion of the laminates are skewed, in a chordwise direction, forward and aft of a non-radial blade axis, thus forming a biased layup with the blade center of twist biased forward or aft of the blade radial axis. This significantly increases the torsional frequency of the blade. In one embodiment, the filaments are skewed forward such that no filaments run from the blade leading edge to the blade tip but, rather, from the blade leading edge to the blade root. This orientation permits more strain produced by foreign object impact to be transmitted to the blade root where it can be more easily absorbed and dissipated by the blade supporting disc.

Abstract: A gas turbine engine fuel delivery and control system is provided with means to recirculate all fuel in excess of fuel control requirements back to the aircraft fuel tank, thereby increasing the fuel pump heat sink and decreasing the pump temperature rise without the addition of valving other than that normally employed. A fuel/oil heat exchanger and associated circuitry is provided to maintain the hot engine oil in heat exchange relationship with the cool engine fuel. Where anti-icing of the fuel filter is required, means are provided to maintain the fuel temperature entering the filter at or above a minimum level to prevent freezing thereof. In one embodiment, a divider valve is provided to take all excess fuel from either upstream or downstream of the fuel filter and route it back to the tanks, the ratio of upstream to downstream extraction being a function of fuel pump discharge pressure.

Abstract: A turbomachinery blade platform comprising a pair of complementary platform halves, each having an outer flow path defining shroud adapted to extend generally laterally of the blade. An inner flange on each platform half, also extending generally laterally of the blade, is retained in a cooperating slot formed within the support structure retaining the blade. A structural member extending between the shroud and the flange is contoured to conform to an overlapping wedging surface disposed about the blade airfoil surface. The platform is thus provided with redundant retention by both the blade and by the blade support structure.

Abstract: A laminated filament composite structure, such as an airfoil for use in an environment in which it is subjected to both foreign object impact and bending is provided with improved leading edge protection. At least one fine wire mesh layer is partially bonded within the composite structure along its neutral bending axis. A portion of the wire mesh layer extends beyond the neutral bending axis and partially around the leading edge where it is bonded to the outer periphery of the primary composite structure. The wire mesh is clad with a metal such as nickel to provide an improved leading edge protective device which is firmly anchored within the composite structure. The neutral bending axis anchoring tends to retain the leading edge protective device intact even after the delamination of the composite structure.

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 blade fabricated of a plurality of bonded filament laminates, at least one of the laminates characterized by a plurality of continuous, collimated filaments embedded in a different matrix at the blade tip than at the blade root. The matrices are characterized by different relative impact strengths.

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.

Abstract: A variable area exhaust device is provided for a gas turbine engine, with the actuation thereof being achieved by means other than conventional actuators. Area variation is accomplished by means of a rotatable duct section forming the downstream extremity of the exhaust device. A portion of the duct comprises a nozzle flap and another portion comprises a piston disposed in a pressure plenum and adapted to at least partially balance the exhaust gas loads on the flap portion to facilitate actuation thereof.

Abstract: A thrust vectoring gas turbine engine exhaust nozzle is provided with a variable area flow path wherein cooling of the stationary flow path side walls is partially obtained by the film cooling technique. Regulating means, such as a valve, is provided to control the pressure drop of the cooling fluid across the walls as a function of nozzle flow path area, thus optimizing the coolant flow rate as a function of flow path area. Where a rotating bonnet-type deflector is employed to divert the exhaust stream downward to obtain a vertical take-off and landing capability, a system is provided to cool the deflector walls by both the impingement and convection cooling techniques. A favorable pressure gradient for the cooling fluid is obtained by exhausting the cooling fluid to ambient pressure whenever the deflector is deployed. Another valve is provided to regulate the flow of coolant to an expansion flap when the deflector is in its stowed position external to the flow path.

Abstract: A flight maneuverable gas turbine exhaust nozzle is provided with cooperating variable internal converging-diverging flaps to provide area control. A flap downstream of the converging-diverging flap provides flight maneuver vectoring as well as external exhaust expansion control. A vertical take-off and landing capability is provided by deployment of a rotating bonnet-type deflector which diverts the exhaust stream downward around one side of the exhaust nozzle. The nozzle throat rotates with the deflector to produce efficient turning of the exhaust stream.

Abstract: An aircraft propulsion system is provided which incorporates a flight maneuverable exhaust nozzle. In one embodiment, gas turbine engines are mounted on both sides of an aircraft fuselage, each engine having an exhaust duct partially defining an exhaust stream flow path. The duct transists from a substantially cylindrical diffuser section aft of the engine to a relatively high aspect ratio section proximate the trailing edge of the wing. Exhaust gases are expelled through a thrust vectorable nozzle which is contoured within the wing and which is adapted to increase wing lift through the concept of supercirculation. Maximum aerodynamic advantage is achieved by distributing the exhaust flow over a significant portion of the wing span at the trailing edge. Thrust augmentation is provided through use of a long, flat duct burner disposed within the high aspect ratio section proximate the exhaust nozzle thereby minimizing turning losses and cooling air requirements.

Abstract: A bore vane assembly is adapted to be received within the annular passage formed between two axially displaced turbine disc halves so as to provide axial columnar support therebetween during high centrifugal loading. The bore vane assembly includes a plurality of axially extending vanes which provide the required support and which also serve to pump cooling fluid from a plenum into the turbine disc.

Abstract: A thrust vectoring gas turbine exhaust nozzle is provided with cooperating variable internal coverging-diverging flaps to provide nozzle flow path area control. A vertical take-off and landing capability is obtained by deployment of a rotating bonnet-type deflector which diverts the exhaust stream downward around one side of the exhaust nozzle. Actuating means are provided to rotate the nozzle throat simultaneously with deflector rotation to produce efficient turning of the exhaust stream in the lift mode. The actuation means also simultaneously controls the nozzle flow path area and external exhaust expansion in the cruise mode.

Abstract: A wheel comprising a plurality of wheel plies, each wheel ply including concentric inner and outer hoops and a plurality of circumferentially spaced spoke loops therebetween, wherein each of the spoke loops is entrapped within the hoops. In one embodiment the wheel comprises a laminate of alternating wheel plies and intermediate plies bonded together. A spoked frame comprising one or more of the wheels is provided, the frame including fairing means to substantially envelope the spokes and retain the individual wheels in their proper spacial relationship.

Abstract: Positionable deflector means are provided in a gas turbine engine inlet duct. The deflector means are actuated to change the axial and circumferential location of a forward protruding extension of the inlet duct in order to selectively reduce noise propagation. A method is disclosed for directional noise shielding as a gas turbine engine experiences altitude and operational changes.

Abstract: Positionable deflector means are provided in a gas turbine engine inlet duct. The deflector means are actuated to change the axial and circumferential location of a forward protruding extension of the inlet duct in order to selectively reduce noise propagation. A method is disclosed for directional noise shielding as a gas turbine engine experiences altitude and operational changes.