126results about "Non-positive displacement fluid engines" 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 reinforcing sheet for wind power generator blades includes a resin layer and a restricting layer laminated on the resin layer.

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 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.

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 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.

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.

A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane.

A noise suppression apparatus includes a body portion including a plurality of nested channels, each channel of the plurality of nested channels including a first end opening and a second end opening, and a surface portion including each first end opening and each second end opening of each channel.

Mechanisms, devices, apparatus, systems and methods of installing ceiling fan motor housings to ceiling mounted plates without using loose fasteners such as screws, and the like. A plate having a plurality of slots about the perimeter can be pre-mounted to a ceiling. A motor housing having clips on interior perimeter edges of the base can be positioned so that the clips are inserted into the slots. Next, the motor housing can be twisted clockwise until the clips lock to the slots allowing the ceiling fan motor to be hung without any loose fasteners. The twist-lock eliminates unsightly fasteners, such as screws underneath the housing, quickens installation time, and is easier and safer than traditional ceiling fan installation techniques.

The invention discloses an alternating-current permanent magnet synchronous drainage pump with a built-in closed cooling water tank, which comprises a motor assembly and a pump structure assembly, wherein the motor assembly comprises a rotor assembly and a stator iron core; the pump structure assembly comprises an impeller and a pump body; the pump body is provided with an impeller cavity for accommodating the impeller, a rotor cavity for accommodating a permanent magnet rotor and a water-cooling cavity for accommodating cooling liquid; the stator iron core is arranged between the water-cooling cavity and the rotor cavity; the water-cooling cavity is provided with an inner cavity wall covered outside the stator iron core and an outer cavity wall used as a pump body shell; bottoms of the inner cavity wall and the outer cavity wall extend in the opposite directions to form the bottom of the water-cooling cavity; the water-cooling cavity is provided with an opening and is sealed by a pump body gland; and the impeller cavity is formed in front of the pump body gland. In the alternating-current permanent magnet synchronous drainage pump, the cooling liquid in the cooling water tank and fluid pumped by a water pump are independent, so that the water quality of the external complete machine can be prevented from being polluted due to the prevention of the pollution of impurity scales in the pumped fluid on the pump body. The cooling water tank is formed by the pump shell, has a compact structure, and is convenient to assemble and maintain.