Abstract: Disengagement of the C-clip in turbine shroud assemblies is prevented by providing a C-clip retainer. The shroud assembly includes a shroud support having a hook and at least one shroud having a mounting flange. A C-clip overlaps the hook and the mounting flange to clamp the shroud to the shroud support, and the retainer is secured to the shroud support and located so as to engage the C-clip. The retainer engages the C-clip in such a manner so as to limit aft axial movement of the C-clip, thereby eliminating C-clip back-off.

Abstract: A water driven impulse turbine has a barrel rotatably mounted upon an axle, with a plurality of runner blades extending tangentially from said barrel. Side plates secure the runner blades on opposite sides thereof. A breastplate is maintained in concentric juxtaposition with the wheel so defined. A penstock is interposed between a water source and the breastplate to pass water into the runner blades. The turbine may consist of a plurality of axially interconnected wheel sections of similar or dissimilar nature to optimize performance.

Abstract: A stent delivery system which includes a self dividing and retracting stent retaining sleeve having a ribbed configuration. The ribbed configuration providing the sleeve with reduced columnar strength and an improved radial strength characteristics. The present stent delivery system further providing for a perforated portion on the sleeve which will rupture at a predetermined pressure thereby dividing the sleeve into a proximal portion and a distal portion. The ribbed sleeve portions providing a recoil action in opposite longitudinal directions to the individual sleeve portions which assists in actively retracting the sleeve portions off of the stent being expanded.

Abstract: The blades (3) of a turbine of axial design are inserted into an undercut blade groove (2) of the turbine rotor (1) in a positive-locking manner and are secured by a blade lock. The blade lock comprises a mounting space (7), which is in connection with the blade groove (2) and into which a filler piece (8), which is in positive-locking relationship with the blade foot (6) of the blades (3), and a wedge (9) are inserted. The cross section of the mounting space (7) receiving the filler piece (8) is widened conically beginning from the blade groove (2). The cross section of the filler piece (8) is adapted to the cross section of the mounting space (7).

Abstract: Rotor disk stress is reduced in a bolted joint for connecting adjacent rotor disks in a gas turbine engine. The bolted joint includes a bolt hole formed in the first rotor disk and a tube disposed in the bolt hole such that a channel is defined between the tube and the bolt hole. A bolt is disposed in the tube such that a gap is defined between the bolt and the tube. The gap thermally insulates the bolt from hot fluid in the channel. A first passage provides fluid communication between the channel and a forward cavity, and a second passage provides fluid communication between the channel and an aft cavity. Hot fluid passing through the channel reduces thermal gradients in the first rotor disk. The tube thermally shields the bolt from the hot fluid to minimize differential thermal growth.

Abstract: An electric motor turbine-type fuel pump having a pair of substantially separate fuel pumping channels on opposed faces of an impeller which has a plurality of circumferentially spaced vanes disposed about the periphery of the impeller. The tip portion of each vane is generally arcuate or curved such that a radially outermost edge of the tip is forward or leads the corresponding radially innermost edge of its base relative to the direction of rotation of the impeller. Preferably, each vane is defined between a pair of radially, axially, and circumferentially extending pockets formed in the impeller, with one set of vanes opening to each of a pair of opposed side faces of the impeller. An axially centered, circumferentially extending rib extends to the radially outermost portion of the vanes and separates the vanes on one face of the impeller from the vanes on the opposed face of the impeller.

Abstract: An in-line centrifugal fan including a housing having an inlet and an outlet spaced apart and substantially coaxial one to another and a motorized centrifugal-type impeller mounted centrally within the housing substantially coaxially between the inlet and the outlet. A plurality of spaced air flow redirecting vanes are each connected to and radially extend inwardly from the housing toward, but not to, a radially outermost perimeter of the impeller whereby air flow through the housing is increased by the vanes. Various vane configurations, clearances and number of vanes are disclosed.

Abstract: Bolt hole stress in rotor disks having bolted joints is reduced by passing relatively hot secondary flow path air (such as compressor discharge air) through each bolt hole to heat the disk from inside the bolt hole. In doing so, the temperature distribution in the area of the bolt hole is made more uniform and the stress is dramatically reduced. The bolted joint includes a bolt hole formed in a first rotor disk and a bolt disposed in the bolt hole such that a channel is defined between the bolt and the bolt hole. A first nut or abutment is attached to a first end of the bolt, and a second nut or abutment is attached to a second end of the bolt. A first passage associated with the first abutment provides fluid communication with the channel, and a second passage associated with the second abutment provides fluid communication with the channel, thereby allowing the relatively hot fluid to pass through the channel during engine operation.

Abstract: The knife edge air seal ring of a gas turbine is modified to receive a replacement or second seal ring portion having a wire brush seal. The replacement or wire brush air seal ring is mounted with the existing knife edge air seal mounting ring at a location so that the existing mounting ring may be used, while providing adequate strength and structural support for installation of the second, wire brush seal ring. The replacement seal ring may be provided with knife edge seals as well, if desired.

Abstract: Apparatus is disclosed for providing cooling channels in the interior of a gas turbine rotor blade. The cooling channels are formed by metallic inserts which extend from adjacent the root of the blade toward the tip. The inserts are substantially flat and are secured in the interior of the airfoil section by means of rails which engage the longitudinal edges of the inserts and serve as a guide during insertion. The rails are preferable formed integrally with the blade casting.

Abstract: A rotor for a gas turbine comprises a multiplicity of rotor blades of which each comprises a blade airfoil, a blade root and a platform arranged between blade airfoil and blade root and each of which, together with the blade root, is pushed into an axial location slot, which is arranged on the outer periphery of a rotor disk, and is releasably retained there in such a way that hollow spaces are formed between the platform and the peripheral surface of the rotor disk, and each of which is supplied, for cooling purposes, with cooling air through at least one cooling air supply passage extending in the rotor disk and emerging into the location slot, which cooling air is fed through the blade root to within the blade airfoil.

Abstract: A turbine blade includes a platform and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough to cool the airfoil. At least one supply passage is provided to direct some of the coolant that has passed at least partially through the internal cooling circuit onto the platform for cooling the platform.

Abstract: A gas turbine engine rotor assembly such as a fan or compressor includes fan blades spaced axially from stator vanes inside an annular duct. A controlled air blowing system is secured to the annular duct and adapted to blow a hot air flow in a direction opposite to the rotation of the fan blades into the annular duct between the fan blades and the stator vanes, to impart an opposite rotational momentum with respect to the air compressed by the rotor blades, in a asymmetrical pattern to interfere with or destroy a symmetrical pattern of the blade rotation-wake of the compressed air, thereby reducing the strength or preventing the generation of the spinning mode so that the fan-stator interaction tones are significantly reduced.

Abstract: A cooled airfoil has an internal cooling passage in which a plurality of trip strips are arranged to effect variable coolant flow and heat transfer coefficient distribution so as to advantageously minimize the amount of coolant flow required to adequately cool the airfoil structure. In one embodiment, this is accomplished by varying the dimensions of the trip strips along a transversal axis relative to the cooling passage.

Abstract: A bi-directional hydroturbine assembly for tidal deployment. A hydroturbine is carried by a cylindrical shroud. Rotation of the hydroturbine blades by tidal currents drives rotation of the shaft, thereby converting kinetic energy into electrical energy. Stabilizer fins extend radially outwardly from the shroud along substantially the entire length of the shroud. Each comer of each stabilizer fin carries a pivot point for connection of pivoting deflectors between adjacent pivot points of adjacent stabilizer fins at the same end of the shroud. Pivoting deflectors are positioned between pivot points about the periphery of each end of the shroud and are biased such that tidal current flow in a first direction urges pivoting deflectors at the first end of the shroud into a non-deflective position, while urging pivoting deflectors at the second end of the shroud into a deflective position, and vice versa for tidal current flow in the opposite direction.

Abstract: A fan frame for encircling an impeller of a fan that includes a base and a plurality of teeth. A hole is formed on the base to form an inner periphery. The plurality of teeth is substantially perpendicular to, and mounted around the inner periphery for encircling the impeller of the fan. A plurality of clearances is formed between each one of the plurality of teeth and its adjacent tooth.

Abstract: A turbine blade includes a platform having an internal cavity formed therein and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough, and at least one supply passage extends between the internal cooling circuit and the internal platform cavity for diverting coolant to the internal platform cavity. The coolant is expelled from holes located in the forward and aft edges of the platform for purging the forward and aft disk wheel spaces and impingement cooling adjacent nozzle bands.

Abstract: A fluid pump (10) has a body housing (14) a fluid pumping chamber having a rotatable pumping member (16), a drive shaft (12) which passes through an aperture in the body into the pumping chamber to effect rotation of the pumping member in use, a seal (18) between the pump body and drive shaft to inhibit fluid moving along the shaft out of the pumping chamber, and a dividing shroud (32) operably located between the seal and the rotatable pumping member to divide the fluid pumping chamber (30) between the seal and the rotatable pumping member.

Abstract: A floatable impeller for multistage metal working pump includes an impeller hub which has an impeller metal working member supporting a rear wall of the impeller and an impeller plastic member integrally formed with the impeller working member. The impeller plastic member is engaged with and driven by the pump shaft. The impeller has a front wall attached with an impeller thrust ring which has a thrust metal working member integrally formed with a thrust plastic member located in front of the impeller front wall. The thrust plastic member serves as a bearing when rotating against a metallic pump shell of an adjacent pump unit for reducing friction loss. The impeller hub has axial grooves formed in the inside wall. The thrust plastic member has radial slots formed in the sidewall. The grooves and slots may collect and discharge grits and sands carried by fluid and generated by friction for reducing friction, improving pumping efficiency and enhancing pump durability.

Abstract: A method and replacement detail for use in processing a stator vane for a rotary machine are disclosed. Various steps and construction details are developed which promote the ease of carrying out the process and improve the fatigue life of the processed stator vane. In one particular embodiment, a portion of the airfoil and the platform are removed in a region adjacent the leading edge of the airfoil and replaced with a replacement detail having new material at a location where cracks are known to form.