Abstract: A rotor and blade assembly for a gas turbine engine in which blades are retained in position on the rotor by a plurality of circumferentially extending segment plates and a snap ring, the segment plates extending radially between a circumferential groove in the rotor and the underside surface of a blade platform and extends circumferentially to seal at least two blade roots, and the snap ring is installed in a groove on the underside of the blade platform and external of the platform surface contacted by a segment plate, the snap ring covering the outer peripheral portion of the segment plates.

Abstract: A metallic clamp for an electrical component which rigidly supports the component and its connecting leads in a control panel so that they vibrate in unison in response to oscillations of the panel structure thereby preventing embrittlement and failure of the component leads. The metallic construction of the clamp serves as a heat sink and aids in the transfer of heat within the panel.

Abstract: Rotating machinery construction employing one or more split balance rings within a rotating element the circumferential position of a ring being adjustable through associated casing structure without disassembly of the machinery to permit rebalancing or trim balancing of the rotor element.

Abstract: An axial-flow compressor in which rotor blade clearance, in an area where the stator case surrounding a rotor blade stage is unsupported, is controlled by the cross-sectional area of a ring surrounding the stator case and by a gap between the inner surface of the ring and the outer surface of the stator case established at the time of compressor build.

Abstract: A trainer for the fuel system of an aircraft such as a helicopter which has full-scale aircraft and fuel system components for training in the operation and maintenance of the fuel system and which uses a fuel substitute which has a higher flashpoint and does not have the odor of aircraft fuel, but does have the specific gravity, dielectric constant and viscosity of aircraft fuel.

Abstract: A viscous damper for a helicopter rotor blade having a stator member and a rotor member each having a plurality of flanges of different diameter defining cylindrical internal and external shear surfaces, respectfully, and a shear gap therebetween, one stator member internal shear surface having two diameters, the shear gap distances between proportional to radius, and a coaxial rotor member comprising two discs having outer cylindrical shaped shear suraces forming a shear gap with adjacent stator member shear surfaces and one rotor disc being axially movable so that a variable portion of its shear surface is opposite both of the diameters of the stator member two-diameter internal shear surface.

Abstract: A swashplate configuration for helicopter which eliminates the need for scissors linkages through the use of a centering member capable of tilt and axial translation while driving torque to the rotating swashplate member through the use of elastomeric bearing assemblies each consisting of a first stack of flat laminates and a second stack of spherical laminates.

Abstract: A compressor stator vane for a gas turbine engine comprised of a leading edge section and a trailing edge section and constructed so that either or both sections may be rotated about a common axis of rotation to vary vane camber with torque for rotating the sections being applied around the engine perimeter.

Abstract: A spherical exhaust nozzle for a gas turbine engine having gimbal mounted convergent-divergent flaps in which cooling air for the flaps is ducted through the convergent flap pivots and the convergent flaps are actuated by actuators connected to the gimbal structure.

Abstract: Mechanism for determining the fatigue properties of helicopter rotor blade flexbeam sections using one motor driven eccentric for imparting combined bending, twisting and deflection loads to a flexbeam.

Abstract: A tail rotor flapping hinge elastomeric bearing in which the inner and outer races are split and the races have ramped surfaces with the higher slope of the inner races being toward the outer edge of the bearing. The races have a plurality of slope angles and each inner race having a groove therein to facilitate a method of preloading.

Abstract: A circulation control aircraft rotor blade of advanced composite material having a spanwise Coanda surface 16 and a plurality of spanwise extending flexible panels 18 cooperating with the Coanda surface to define slots for the discharge of compressed air from a duct 14 within the blade with each panel having flexure means 34 associated with attaching means 24 and limiting means 38 for establishing a slot opening preload and a slot maximum opening and with limiting means 38 providing structural equilibrium and reduced bending moments in the inboard corners of the air duct.

Abstract: A crashworthy helicopter cockpit having a pyrotechnic system actuated by a stroking pilot seat for repositioning the upper portion of the cyclic control stick upon a severe or crash landing that is independent of aircraft electric and hydraulic systems.

Abstract: A circulation control aircraft rotor blade having a spanwise Coanda surface 16 and a plurality of spanwise extending flexible composite material panels 18 cooperating with the surface to define slots for the discharge of compressed air from within the blade with each panel having first flexure means 60 associated with screw adjustments 36 for establishing a slot opening preload and second flexure means 62 associated with screw adjustments 38 for establishing a slot maximum opening.

Abstract: A plenum for a circulation control rotor aircraft which surrounds the rotor drive shaft (18) and is so constructed that the top (32), outer (38) and bottom (36) walls through compressed air is admitted are fixed to aircraft structure and the inner wall (34) through which air passes to rotor blades (14) rotates with the drive shaft and rotor blades.

Abstract: A fan jet engine construction in which the drive connection between the rotor drive shaft (10) and the gearbox (18) includes a slideable tower shaft member (26) movable to a first position permitting removal of a drive module (16) and to a second position permitting removal of the fan casing (20) without removal of the gearbox.

Abstract: Helicopter tail rotor control system having a quadrant (18) with two flexible cables (20,22) wrapped around the quadrant surface in opposing directions and each attached to the quadrant at a point (42,60) opposite to initial contact of the cable with the quadrant, and spring extension (44, 62) from each cable passing around a pulley (46) and attached to the quadrant at a point on a radial line with the cable attachment.

Abstract: A flight control system for a helicopter tail rotor having a semicircular quadrant 18 with bell cranks 36, 40 mounted on either end of the quadrant and flexible control cables 20, 22 connected to each bell crank. The bell cranks are spring loaded in opposition to cable tension, and a fixed abutment 72 provides a reaction against the bell crank springs in the event of a cable severance. The quadrant works against the spring loading of one bell crank in the event of breakage of the opposite control cable and is centered by the spring loading of both bell cranks if both cables are broken.

Abstract: A circulation control rotor system in which butterfly valves (44, 46) control the flow of compressed air from a plenum chamber (40) to the rotor blades (14). Each has an actuator (48, 52) positioning the valve in accordance with a control input and in which a spring loaded averaging linkage (120) between adjacent valves around a plenum chamber circumference acts to position the valve at an average position of the two adjacent valves if a fault in the actuator or within its control or power system should develop. Should such a fault develop, as determined by a comparison of actual valve position with command position, the faulty valve's actuator is shut down.

Abstract: Mechanical collective pitch control system for a circulation control rotor system aircraft utilizing an axially moveable pneumatic system plenum 32 in the collective pitch control system.