1760results about "Component unification devices" patented technology

A method of assembling a rotor blade for a turbine is provided that includes forming a rotor blade trailing edge by coupling a suction side terminus to a pressure side terminus and positioning a trailing edge assembly between the suction side terminus and the pressure side terminus, the trailing edge assembly having a varying cross-section.

A power generation system includes a first compressor, a second compressor, a combustor configured to receive compressed air from the second compressor to produce an exhaust stream, a first turbine, and a power turbine. The first turbine is configured to receive the exhaust stream, generate a rotational power from the exhaust stream, output the rotational power to a second compressor, and output the exhaust stream. The system includes a coupling device configured to couple and decouple the first compressor to / from a second turbine, an electrical generator coupled to an output of the power turbine and configured to output electrical power, and a controller configured to cause the coupling device to mechanically decouple the second turbine from the first compressor, and cause the coupling device to direct compressed air from an air storage cavern to an inlet of the second compressor.

A metal vane core or strut (64) is formed integrally with an outer backing plate (40). An inner backing plate (38) is formed separately. A spring (74) with holes (75) is installed in a peripheral spring chamber (76) on the strut. Inner and outer CMC shroud covers (46, 48) are formed, cured, then attached to facing surfaces of the inner and outer backing plates (38, 40). A CMC vane airfoil (22) is formed, cured, and slid over the strut (64). The spring (74) urges continuous contact between the strut (64) and airfoil (66), eliminating vibrations while allowing differential expansion. The inner end (88) of the strut is fastened to the inner backing plate (38). A cooling channel (68) in the strut is connected by holes (69) along the leading edge of the strut to peripheral cooling paths (70, 71) around the strut. Coolant flows through and around the strut, including through the spring holes.

A single piece pulsed flow wing assembly method providing for horizontal wing manufacture is accomplished using synchronized automated vehicles guided in a predetermined manner to move and, locate wing structure in a plurality of assembly positions. Multi-axis assembly positioning systems (MAPS) are used at each assembly position to support and index components in the wing structure and determinant assembly techniques are used for indexing of the components. Modular automated manufacturing processes employing magnetic assembly clamping, drilling, fastener insertion, and sealant application are employed.

A process for joining a base for an airfoil to a disk for an integrally bladed rotor stage in a gas turbine engine includes providing a disk having a radially outer rim with a slot defined therein by a recessed surface, and further includes providing a base having a longitudinally extending root portion facing opposite a longitudinally extending support portion for supporting the airfoil. The root portion has a root surface and the support portion has an outer surface. The process further includes bringing the root surface of the root portion into contact with the recessed surface bounding the slot, applying pressure and relative movement between the base and the rim to achieve during welding, substantial contiguity between the root surface and the recessed surface over the area of the recessed surface, resulting in a substantially continuous linear friction weld between the base and the rim.

Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially therefrom. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.

A bushing (30, 31) in a hole (26) through a ceramic matrix composite structure (20) with a flange (34, 38) on each end of the bushing (30, 31) extending beyond and around the hole and pressing against opposed surfaces (22,24) of the CMC structure (20) with a preload that resists buckling of the composite structure fibers and resists internal CMC fiber separation. A connecting element (40), such as a bolt or pin, passes through the bushing (30, 31) for engagement with a supporting element (50). The bushing (31) may be formed in place as a single piece of ceramic, and cured along with the CMC structure (20), or it may be formed as two ceramic or metal parts (32, 36) that are joined together and preloaded by threads (33). The connecting element (40) may be a pin, or it may be a bolt with a shaft threaded into one part (32) of the bushing and a head (42) that pushes the second flange (38) toward the first flange (34).

A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor that includes a first plurality of rows of turbine blades configured to rotate in a first rotational direction, providing a low-pressure turbine outer rotor that includes a second plurality of rows of turbine blades configured to rotate in a rotational direction that is opposite the first rotational direction, and coupling a support structure between the outer rotor and a turbine mid-frame such that the support structure supports a forward end of the outer rotor, and wherein the support structure includes a first portion that has a first coefficient of thermal expansion and a second portion that has a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion.

A system and method for harvesting the kinetic energy of a fluid flow for power generation with a vertically oriented, aerodynamic wing structure comprising one or more airfoil elements pivotably attached to a mast. When activated by the moving fluid stream, the wing structure oscillates back and forth, generating lift first in one direction then in the opposite direction. This oscillating movement is converted to unidirectional rotational movement in order to provide motive power to an electricity generator. Unlike other oscillating devices, this device is designed to harvest the maximum aerodynamic lift forces available for a given oscillation cycle. Because the system is not subjected to the same intense forces and stresses as turbine systems, it can be constructed less expensively, reducing the cost of electricity generation. The system can be grouped in more compact clusters, be less evident in the landscape, and present reduced risk to avian species.

A ceramic shroud assembly suitable for use in a gas turbine engine comprises a metal clamp ring shrink fitted around a ceramic shroud ring and an insulating and compliant interlayer. The interlayer is positioned between the metal clamp ring and the ceramic shroud ring.