Abstract: A lightweight gas turbine rotor having a pair of high specific strength support ring members positioned fore and aft a center hub member. The unitary center hub member for carrying a plurality of airfoils that extend radially outward therefrom. The pair of high specific strength support ring members are connected to the blade carrying member at a location to compressively transmit the centrifugal force generated by the rotating rotor to a radially inward location on the support ring members. The support ring members being utilized to resist a majority of the centrifugal force generated by the components of the rotor. The center hub member and the pair of support ring members are made of different materials. More particularly the pair of support ring members are made of a metal matrix composite, and the center hub member when utilized in a compressor is formed of a high temperature titanium alloy, and the center hub member when utilized in a turbine is formed of a nickel alloy.

Abstract: An integrated system for controlling the positioning of a rotating rotor within a compressor to enhance the performance of a gas turbine engine. The rotor being attached to a rotating shaft that is coupled to the compressor housing by a magnetic bearing system. The magnetic bearings support and position the rotor within the high speed tubomachine. During operation of the compressor the magnetic bearings non-axially position the rotor relative to the compressor housing to provide compressor instability control. By non-axially displacing the rotor relative to the compressor housing there is a resulting local disturbance to the fluid flow field, which in turn serves as the disturbance to alter the dynamics of the aerodynamic system and displace the compressor surge line.

Abstract: Foreign object ingestion damage detection and accommodation system for a gas turbine engine system having a gas turbine engine with multiple rotating members, such as a twin spool configuration. System includes speed sensors for sensing the rotational speed of at least two rotating members. Sensors are coupled to a controller which detects damage by comparing the sensed speed of the second rotational member to an expected speed. Expected speed is determined from the sensed speed of the first rotating member using a known characteristic relationship between the the first and second rotating member speeds for the given gas turbine engine design. Thrust loss accommodation is triggered when damage is detected. Accommodation mode provides a synthesized primary thrust control feedback signal in lieu of the sensed signal for a damaged rotational member. Synthesized signal is derived from the sensed speed for the undamaged rotational member.

Abstract: A lightweight high temperature multiproperty rotor disk and method of manufacture for use in a gas turbine engine. The rotor disk of a nickel super alloy and having a plurality of lightweight high temperature single crystal blade attachment lugs bonded thereto. The single crystal high temperature rotor blade attachment lugs being cast in a substantially rectangular shape and bonded to the circumference of the disk. A method of manufacturing the rotor includes positioning the plurality of single crystal attachment lugs on a positioning ring that has locating nests formed thereon. Subsequently, the rotor disk is placed within the bonding ring and a restraining ring is placed around the entire subassembly. Upon subjecting the assembly to high temperature the rotor disk, having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the restraining member, forces the components into a mating relationship.

Abstract: A fluid cooled seal arrangement for a gas turbine engine including a first sealing element coupled to a mechanical housing of the engine, and a second sealing element connected to a shaft rotatable within the housing. The first and second sealing elements are arranged radially adjacent to one another to form a rubbing interface therebetween. A lubrication system for delivering cooling fluid to the second sealing element through a passageway arranged along the rotating shaft. The cooling fluid is discharged through a plurality of openings formed in one end of the passageway. During normal operation of the engine the centrifugal force from the rotation of the shaft flings the oil radially outward to a channel formed on the underside of the second sealing element. The channel receives the cooling fluid therein, and allows for the escape of the cooling fluid onto the underside of the second sealing element to provide a uniform thickness of cooling fluid thereon.

Abstract: A method of casting a turbine wheel of a metal alloy, wherein there is generated a columnar grain structure parallel to the leading and trailing edges of the vanes, by directional solidification of the metal from the central aperture in the wheel outward to the vane tips. A form with cavity to receive therein the molten metal has a thin walled core in the center, with the core wall outer surface in place to provide one wall of the cavity. A heat transfer medium in fluid form is circulated through the core, thereby cooling the poured metal by heat transfer from the inner ends of the vanes outward to the tips.

Abstract: A gas turbine component that includes a very thin wall. The gas turbine component being of a single-piece, single-cast structure. In one form of the gas turbine component it is formed of a superalloy composition and is capable of withstanding gases impinging upon the walls at temperatures greater than 4000.degree. F.