Abstract: A blade for a rotor of a gas turbine engine is constructed with a spar and shell configuration. The spar is constructed in an integral unit or multi-portions and includes a first wall adjacent to the pressure side and a second wall adjacent to the suction side, a tip portion extending in the spanwise direction and extending beyond the first wall and the second wall and a root portion extending longitudinally, an attachment portion having a central opening for receiving the foot portion and a platform portion. The root portion fits into the central opening and is secured therein by a pin extending transversely through the attachment and the foot portion. The shell fits over the spar and is supported thereto by a plurality of complementary hooks extending from the spar and, shell. The ends of the shell fit into grooves formed on the tip .portion and the platform, The shell is made from a high temperature resistant material, such as Molybdenum or Niobium, and is formed from a wife EDM process.

Abstract: The clearance between the tips of the rotor blades and the segmented shroud of a gas turbine engine is controlled by a passive clearance control that includes a support ring made from a low thermal expansion material supporting a retainer for the blade outer air seal that is slidable relative thereto so that the segments expand circumferentially and move radially to match the rate of change slope of the rotor during expansion and contraction for all engine operations. A leaf spring between the support ring and outer air seal biases the outer air seal in the radial direction and maintains the desired radial position during steady state operation of the gas turbine engine.

Abstract: A blade for a rotor of a gas turbine engine is constructed with a spar and shell configuration. The spar is constructed in an integral unit or multi-portions and includes a first wall adjacent to the pressure side and a second wall adjacent to the suction side, a tip portion extending in the spanwise direction and extending beyond the first wall and the second wall and a root portion extending longitudinally, an attachment portion having a central opening for receiving the root portion and a platform portion. The root portion fits into the central opening and is secured therein by a pin extending transversely through the attachment and the root portion. The shell fits over the spar and is supported thereto by a plurality of complementary hooks extending from the spar and shell. The ends of the shell fit into grooves formed on the tip portion and the platform.

Abstract: The clearance between the tips of the rotor blades and the segmented shroud of a gas turbine engine is controlled by a passive clearance control that includes a support ring made from a low thermal expansion material supporting a retainer for the blade outer air seal that is slidable relative thereto so that the segments expand circumferentially and move radially to match the rate of change slope of the rotor during expansion and contraction for all engine operations. A leaf spring between the support ring and outer air seal biases the outer air seal in the radial direction and maintains the desired radial position during steady state operation of the gas turbine engine.

Abstract: The clearance between the tips of the rotor blades and the segmented shroud of a gas turbine engine is controlled by a passive clearance control that includes a support ring made from a low thermal expansion material supporting a retainer for the blade outer air seal that is slidable relative thereto so that the segments expand circumferentially and move radially to match the rate of change slope of the rotor during expansion and contraction for all engine operations. A leaf spring between the support ring and outer air seal biases the outer air seal in the radial direction and maintains the desired radial position during steady state operation of the gas turbine engine.

Abstract: The nacelle of the aircraft is purged and the sidewall of the vector nozzles of the gas turbine engine in the nacelle is cooled by utilizing the engine fan air to drive ejector pumps mounted in series flow relationship, a rectangular mixing zone and a diffuser with a rectangular cross section and a step in the exhaust nozzle gaspath. This results in minimizing the amount of fan air for driving the system and enhancing engine thrust and enhanced sidewall cooling because the temperature of the mixed air is lower than heretofore known systems.

Abstract: The backbone which is a load carrying support member of the aft end of the compressor of a gas turbine engine is fabricated from an annular disk-like element that is generally straight in cross section. The points of attachment permit circumferential thermal growth with radial restraint and snugness at judicious locations for minimizing scrubbing of the case-tied segmented inner stator case.

Abstract: Tip shroud segments (26) are supported in support ring (24). The ring has at its downstream end conical surface (32) mating and in interference fit with conical surface (16). When flange (20) is torqued, face (22) aligns and forces support ring (24) into the interference fit. Concentricity and rigidity of the shroud support is obtained in a structure easily assembled and disassembled.

Abstract: A high speed curved position sensitive porportional counter detector for use in x-ray diffraction, the detection of 5-20 keV photons and the like. The detector employs a planar anode assembly of a plurality of parallel metallic wires. This anode assembly is supported between two cathode planes, with at least one of these cathode planes having a serpentine resistive path in the form of a meander having legs generally perpendicular to the anode wires. This meander is produced by special microelectronic fabrication techniques whereby the meander "wire" fans outwardly at the cathode ends to produce the curved aspect of the detector, and the legs of the meander are small in cross-section and very closely spaced whereby a spatial resolution of about 50 .mu.m can be achieved. All of the other performance characteristics are about as good or better than conventional position sensitive proportional counter type detectors. Count rates of up to 40,000 counts per second with 0.5 .mu.s shaping time constants are achieved.

Abstract: A cylindrically shaped spacer between a shaft and hub of a turbine rotor of a gas turbine engine as fabricated from a flexible resilient material and interference fitted at discrete points on either side of the transverse axis of the spacer between the shaft and spacer and between the hub and spacer to impart a twist of the spacer about this axis to remain in contact with the hub and shaft throughout its entire rotating envelope.

Abstract: A seal between co-rotating, opposed annular surfaces of interconnected elements comprises a multi-filament wire rope disposed within an annular groove formed at the interface between the two surfaces, the groove being wedge-shaped in cross-section, one side of the wedge being formed by each element. The wire rope is forced into sealing relationship with the groove surfaces along its entire length by centrifugal forces. The multi-filament wire rope has improved sealing capability over solid, single filament wire seals of the prior art. The seal is particularly well suited for use in the hot turbine section of a gas turbine engine and is resistent to damage and failures due to multiple engine cycles.