180results about "Pump components" patented technology

There is disclosed a gas turbine shroud structure comprising: a shroud support component 12 attached to an inner surface of a gas turbine casing 3; a shroud segment 14 divided in a peripheral direction and supported by the inner surface of the shroud support component; and a heat-resistant restricting spring 18 held between the shroud segment and shroud support component to urge the shroud segment inwards in a radial direction. The shroud segment 14 is formed of a ceramic composite material, and includes a coating layer 15 having heat insulation and impact absorption effect on an inner surface of the segment.

A low profile pump inlet for an implantable blood pump is disclosed. The low profile pump inlet has an inflow diffuser for attachment to a conduit bearing an inflow of a fluid such as blood and an outflow orifice in fluid connection with the diffuser. The outflow orifice is configured to direct the fluid from the diffuser into a pump such as an implantable blood pump. The low profile pump inlet helps to suppress the effects of upstream pipe bends on the blood traveling through the inlet. The inlet thus provides a flow having a substantially uniform velocity profile into the blood pump.

A rolling bearing for a turbomachine supporting a first shaft to rotate relative to a second shaft, and comprising: a plurality of rolling elements engaged between an inner annular ring mounted on the second shaft and an outer annular ring mounted on the first shaft; an oil film formed at an annular contact surface between said outer ring and said first shaft; at least one duct passing through said inner ring and opening out in an inner race for said rolling elements in order to lubricate them; and at least one additional duct passing through said inner ring and opening out outside the inner race in order to feed oil through said outer ring to said oil film under the effect of the centrifugal force generated by said second shaft rotating, said outer ring having an annular shoulder projecting radially towards the inside of said annular space, said shoulder having at least one channel opening out substantially in register with said additional duct and opening out into said oil film.

Noise reduction conduit for non rotary components of aircraft engines, subjected to a characteristic range of temperatures of a gas turbine engine, constituted by an annular structure composed of an aerodynamic wet wall (10a, 10b), perforated and resistant mechanically and thermally; of a dry wall (12a, 12b), not resistant and of light weight; and of some intermediate elements to which both walls are mechanically attached and that define a jump or difference of temperature between the wet and dry walls; between which wet (10a, 10b) and dry walls (12a, 12b) there are partitions that define cavities (16a, 16b) isolated with regard to each other.

A motor. The motor includes a stator, a rotor, a top magnetic structure, and a bottom magnetic structure. The stator is disposed in a frame. The rotor is also disposed in the frame, corresponding to the stator. The rotor comprises a shaft, extended axially from the rotor. The shaft does not contact the stator or the frame. The bottom magnetic structure is at the bottom of the frame. The top magnetic structure is on the top of the frame. The top and bottom magnetic structures are opposite to each other in an axial direction. Magnetic attraction generated between the first magnetic structure and the second magnetic structure attracts and positions the shaft therebetween such that the first magnetic structure, the second magnetic structure, and the shaft are coaxially aligned.

A turbomachine comprising a diffuser-distributor assembly comprising a downstream end-piece connected at its downstream end to means for injecting air for ventilating a turbine and delimiting with the impeller of a centrifugal compressor an annular cavity for the circulation of ventilation air taken from the outlet of the compressor, this turbomachine comprising means for taking air from the injection means and means for guiding this air to the radially internal portion of the downstream face of the impeller.

A motor includes a base, a stator, a bearing, a positioning member and a rotor. The base includes a shaft tube. The stator is mounted around the shaft tube. The bearing is received in the shaft tube. The positioning member is fixed to an end of the shaft tube and has a pressing portion to prevent movement of the bearing in the shaft tube. A plurality of retaining plates is formed on the positioning member. Each retaining plate has a retaining end. The rotor includes a shaft having an annular groove formed in an outer periphery thereof. The retaining ends of the retaining plates are in the annular groove to avoid departure of the rotor from the base. Consequently, by a single-component design of the positioning member, departures of the rotor and the bearing are both avoided.

Several embodiments that enhance and improve the efficiencies of vertical axis wind turbine generators by expanding their normal range of useful operations. Stationary vanes provided external to the rotor blades provide directional control of wind/air flow into the blades for decreased drag and increased differential wind pressure. Control scenarios for adjusting stationary wind vanes and additional ducting of air to increase efficiencies.

The invention relates to gas turbine engine seal systems having a rotating member with an abrasive tip surface disposed in rub relationship to a stationary seal member with an abradable surface. The abrasive tip surface is coated with a metallic alloy matrix having ceramic abrasive particles embedded in and projecting from the matrix. The abradable seal surface is coated with a ceramic coating. The rub relationship affords a tight operating clearance between the rotating member and the stationary seal member, thereby improving engine efficiency, reducing fuel consumption and minimizing overhaul downtime.

The present invention provides novel supersonic compressors comprising novel supersonic compressor rotors. The supersonic compressor rotors are designed to operate at very high rotational speed wherein the velocity of the gas entering the supersonic compressor rotor is greater than the local speed of sound in the gas, hence the descriptor “supersonic”. The new supersonic compressors comprise at least one supersonic compressor rotor defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp. The novel supersonic compressor rotors are expected to enhance the performance of supersonic compressors comprising them, and to provide for greater design versatility in systems comprising such novel supersonic compressors.

An axial-flow wind wheel comprises three blades set on a hub, wherein, the end area of the blades is dishing toward to the costal air-in direction; the three blades use the rotary central axis of the wind wheel as center each other and they allocate equal-spaced or unequal-spaced in the 120degree+-15degree. The external diameter of the axial-flow is defined as D2, the hub diameter is defined as D1, the height of the blade Rm is defined as (D2-D1)/2, the circumference diameter in which there is the beginning dishing place A is defined as D3, (D3-D1)/2=(0.10-0.47)Rm. Since the high-middle part of the trailing edge change the distribution of pressure of the blades before the blade root part, the high pressure draught compartment of the blades flow direction low pressure surface advanced to make local pressure ascending, to reduce boundary layer separating, to make the boundary layer turn into turbulent flow before getting the front of the blade end, to reduce convolution noise and rotor wake, thereby having low noise and big air quantity.

The present invention relates to a transformer (100) for the transfer of electrical power from a nacelle (250) of a horizontal-axis wind turbine to a turbine tower (350) of said wind turbine whereby the nacelle (250) is in revolute attachment to the tower (350), comprising: a primary winding (200) adapted for attachment to the nacelle (250), and a secondary winding (300) adapted for attachment to the turbine tower (350), which windings (200, 300) are in revolute alignment with each other, and configured for transfer of electrical power by induction from the primary winding (200) to the secondary winding (300). It also relates to a method for assembly or disassembly of a wind turbine.

A radial compressor rotor is provided for stabilizing the flow behavior of a delivery gas, consisting of a wheel disc and blades arranged uniformly in the circumferential direction, wherein the generatrix of the surface of the blades is designed as a curved line at least in a curved section, such that the surface is curved in two directions in this section.

The disclosure relates to a cylinder head having at least one cylinder. The cylinder head comprises a radial turbine including a rotor arranged in a turbine casing and rotatably mounted on a shaft, an overall exhaust line which opens into an inlet zone of the radial turbine, said zone merging into a flow duct which carries exhaust gas, and at least one coolant duct integrated into the turbine casing to form a cooling system, the at least one coolant duct extending in a spiral around the shaft in the casing, wherein the at least one coolant duct extends circumferentially around and at a distance from the flow duct over an angle α, where α≦45°.

A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one catch to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that a portion of the at least one spline seal is received within a recess defined within the turbine nozzle slot to facilitate retaining the at least one spline seal within the turbine nozzle slot.

A method of forming a fan blade includes the step of applying an adhesive layer around a leading edge of a fan blade body. The adhesive layer includes an adhesive film supported by a scrim cloth, and the adhesive layer contacts a portion of an inner surface of the fan blade body and a portion of an outer surface of the fan blade body. A leading edge sheath is positioned relative to the fan blade body such that a first flank and a second flank of the leading edge sheath is positioned over the portion of the inner surface and the portion of an outer surface, respectively, of the fan blade body. Pressure is applied to the first flank and the second flank of the leading edge sheath to secure the leading edge sheath to the blade body and curing the adhesive film.

The invention discloses a flushing device for a mechanical seal of a centrifugal pump, and belongs to the technical field of centrifugal pumps. The flushing device comprises a flushing pipe connected to the centrifugal pump; the liquid feeding end of the flushing pipe is connected with the outlet end of the centrifugal pump; the liquid discharging end of the flushing pipe is connected with the mechanical seal of the centrifugal pump; the flushing device is characterized in that the flushing pipe is connected with a tubular filter, a pressure gauge and a throttling orifice plate; the tubular filter is close to the outlet end of the centrifugal pump; the throttling orifice plate is close to the mechanical seal of the centrifugal pump; a first stop valve and a second stop valve are arranged on the flushing pipe; the first stop valve is positioned between the outlet end of the centrifugal pump and the tubular filter; and the second stop valve is positioned between the pressure gauge and the throttling orifice plate. The flushing device can both achieve a good cooling effect on the mechanical seal and prevent particle impurities from being deposited on the sealing surfaces of movable and fixed rings, thus effectively protecting the sealing surfaces of the movable and fixed rings, relieving wear and enhancing the sealing effect; and therefore, normal and stable operation of the centrifugal pump is guaranteed.

A flow discouraging system includes a stator assembly, a rotor assembly, and a plurality of fingers. The stator assembly includes one or more stationary components forming a side wall, the side wall including an annular groove defined by an outer axially-extending surface, an inner axially-extending surface, and a radial surface extending between the outer and inner axially-extending surfaces. The rotor assembly is disposed adjacent to and spaced apart from the stator assembly to form a portion of a cavity and includes an annular rim extending at least partially into the annular groove. The plurality of fingers is disposed in the annular groove and extends from the one or more stationary components the annular rim.

A turbocharger system having a compressor wheel including blades that define an inducer and an exducer, a compressor housing configured to receive the compressor wheel, and an impeller passage within which air is to be compressed by the blades, wherein the compressor housing forms an intake port configured to provide intake air to the inducer, and a bypass port opening into the impeller passage between the inducer and exducer. The bypass port places the impeller passage in fluid communication with the atmosphere without having a fluid interaction with the intake air. A bypass-air filter is adapted to filter air passing between the bypass port and the atmosphere, and is a portion of the intake-air filter.

A gas turbine engine system includes a gas turbine engine using vaporized liquefied gas as fuel. The gas turbine engine is configured to ingest intake air from an intake port and direct exhaust gases to an exhaust port. The gas turbine engine system also includes a heat exchanger with a heat transfer fluid therein. The heat exchanger is configured to create at least a part of the fuel by heating the liquefied gas. The gas turbine engine system also includes an intake air temperature control circuit. The intake air temperature control circuit includes conduits configured to direct the heat transfer fluid to the intake port and the exhaust port. The gas turbine engine system also includes a control system configured to selectively direct the heat transfer fluid to one of the intake port and the exhaust port.

A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or welding. The first vane assembly member includes the outer band, the airfoil, an inner flange, and a first segment of the inner band with a first edge, spaced from the flange and extending between and through inner band circumferential edge portions. The second vane assembly member includes a second segment of the inner band including a second edge of shape and size matched with the first edge and extending through the inner band circumferential edge portions.