Abstract: Shrouds and shroud segments for gas turbine engines are provided. In one exemplary aspect, a gas turbine engine includes a first rotor blade stage and a second rotor blade stage. The gas turbine engine also includes a shroud formed from a plurality of shroud segments that each have a body and a vane extending from the body. The vane is disposed within the flow path between the first rotor blade stage and the second rotor blade stage to form at least a portion of a nozzle stage. Further, the body of the shroud segment defines an outer wall of the flow path and spans from the first rotor blade stage to the second rotor blade stage. An impingement baffle segment couples the shroud segment with a casing of the gas turbine engine.

Abstract: A blower arrangement comprising an impeller, which has an axial intake opening formed by a cover plate covering impeller blades at least in sections, by an intake nozzle connected upstream of the impeller, which extends at least in sections into an overlap section in the intake opening of the impeller, wherein a circumferential nozzle gap is formed between the intake nozzle and the cover plate of the impeller, an outer nozzle, which is arranged spaced apart in the radial direction in relation to the impeller and the intake nozzle and enclosing them in the circumferential direction. A first circumferential radial gap is provided between the outer nozzle and the intake nozzle, which forms an inlet nozzle duct extending in the flow direction. A second circumferential radial gap is provided between the outer nozzle and the cover plate of the impeller, which forms a gap duct extending in the flow direction.

Abstract: A method of manufacturing a protective edge for a blade, wherein a protective edge (30) made of an anodizable metal is provided, and that protective edge (30) undergoes a micro-arc oxidation electrolytic treatment. Protective edge (30) manufactured using said method.

Abstract: A gas expander includes: a casing where a swirl chamber for a gas to be expanded is formed; a turbine wheel that is housed in the casing and rotationally driven by the expanded gas; a diffuser that is mounted to the casing in a direction of a rotating shaft of the turbine wheel and includes a flow path for the expanded gas to flow in the direction of the rotating shaft; a swirl stopper that is disposed in the diffuser, faces a downstream front end surface of a boss of the turbine wheel that faces the flow path, and includes a closed swirl stopping surface that is disposed to face the downstream front end surface of the boss with a gap between the closed swirl stopping surface and the downstream front end surface; and a swirl preventing plate that circumferentially partition the flow path in the diffuser.

Abstract: A rotor blade coupling device for coupling to a rotor mast having a rotor head centerpiece. The coupling device has at least three rotor blade mountings mounted on the rotor head centerpiece and accommodating at least three rotor blades lying in a rotor plane, and at least one connecting element between adjacent rotor blade mountings. The rotor blade mountings can carry out pivoting motions about a pivoting axis extending vertical to the rotor plane. The at least one connecting element is a damping device, and the rotor blade coupling device has a plate-shaped transfer element, which respectively crosses a rotor blade mounting and is coupled to at least one damping device. The rotor blade coupling device has a simplified design and ensures improved damping of lead-lag motions.

Abstract: A high pressure BLISK includes at least one circular row of airfoils circumferentially disposed about, integral with, and extending radially outwardly from an annular rim having an annular flat aft facing face with coplanar radially outer and inner face portions radially separated by an annular undercut extending into the rim from the aft facing face. Airfoil roots including root fillets extend around the airfoil between the rim and pressure and suction sides of the airfoils. An axially aftwardly extending annular cylindrical section extends aftwardly from the flat face. The BLISK being a first of axially adjacent first and second rotor sections connected by a rabbet joint. A forward arm of the second rotor section includes an outer forward facing annular face spaced apart from the aft facing face radially outwardly of the annular undercut and a radially inner forward facing annular face contacting the aft facing face.

Abstract: A turbine-blade assembly for use in a gas turbine engine is disclosed. The turbine-blade assembly includes an attachment body, a heat shield, and a retainer. The heat shield surrounds a portion of the attachment body. The retainer is configured to retain the heat shield on the turbine-blade assembly.

Abstract: A system is for sensing a shifting of a drive ring, a compressor, and a gas turbine. The system includes a compressor housing; at least one drive ring installable on the compressor housing and disposed on the compressor housing with a spacing, and the at least one drive ring being provided with at least one installation hole, extending along a radial direction of the at least one drive ring; and at least one sensor, located in the corresponding installation hole and used to sense the spacing between the at least one drive ring and the compressor housing in real time. In an embodiment, the system for sensing a shifting of a drive ring, the compressor, and the gas turbine has advantages of simple structures and relatively low costs.

Abstract: The present disclosure generally relates to a guide vane for a gas turbine, and provides for example an innovative guide vane with improved flexibility leading to a reduction of stresses at the interface between the vane platform and the vane carrier. Exemplary embodiments provide only circumferential line contact or point contact between the guide vane and the guide vane carrier.

Abstract: The present disclosure relates to devices, systems, and methods for controlling and/or augmenting acoustic sounds emitted from flight vehicles, such as unmanned aerial vehicles (UAVs). For example, while in flight, a UAV may emit a characteristic sound or tone (or a plurality of such tones), which may be a result of propeller and/or motor noise. To mitigate such noise from UAVs, disclosed embodiments may include acoustic resonators that may provide additional tones to complement the sounds or tones emitted from the UAV. Namely, the acoustic resonators may be shaped, adjusted, or otherwise controlled to emit additional tones that form pleasing intervals in combination with the characteristic tone(s) from the UAV.

Abstract: The invention relates to part of a turbine engine comprising two arms passing through a stream of the turbine engine, wherein each arm comprises an outer surface and an aerodynamic linking device. The aerodynamic linking device comprises fairings extending between the two arms, compressible interface means interposed between the fairings and means for retaining the fairings in place by pressure in relation to the arms, which compress the interface means.

Abstract: A ram air turbine has a turbine having blades to be extended into an airflow adjacent to an aircraft. The turbine is operable to drive a power generation rotor. A module receives sensed information from a plurality of sensors. The plurality of sensors are associated with locations on the ram air turbine, sense conditions at the locations, and send information with regard to the sensed conditions to the module. The module is operable to compare sensed conditions to limits and identify a potential condition of concern based upon the comparison. A method of testing a ram air turbine is also disclosed.

Abstract: A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil body. The metal leading edge further includes a second edge extending axially aftward from the nose along a suction side of the fan blade airfoil body. The first edge and the second edge forming a notch at the conjunction of the first edge, the second edge, and the nose. The metal leading edge also includes a nose length extending from a nose tip to the notch. The nose length at a first radial location is different from the nose length at a second radial location.

Abstract: A method for producing turbine rotor blades or the base bodies thereof includes a) providing the base body, which has, following one another along a longitudinal axis, a blade root, a blade platform and a blade airfoil, b) sensing a value of at least one parameter of the base body, at least one of the parameters representing a vibrational property of the base body, c) comparing the sensed value with a predetermined target interval, d) if the sensed value lies outside the target interval, reducing the mass of the base body, wherein the reduction of the mass takes place at the blade root and/or on the blade platform by introducing at least one recess and/or by reducing a dimension below the corresponding target value.

Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes first and second airfoil pieces. The first airfoil piece defines a portion of the airfoil profile and has a first slot. The second airfoil piece defines a different portion of the airfoil profile and has a second slot. The first slot and the second slot together form a seal slot, and a seal is disposed in the seal slot.

Abstract: An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.

Abstract: A cooling device includes a fan; an intake-side intrusion-preventing member that is provided on an intake side of the fan and prevents an object from entering the fan; an exhaust-side intrusion-preventing member that is provided on an exhaust side of the fan and prevents an object from entering the fan. The intake-side intrusion-preventing member and the exhaust-side intrusion-preventing member have different shapes.

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. The resupply hole has a single inlet that is fluidly connected to multiple discrete outlet apertures.

Abstract: The present invention relates to a floating wind energy harvesting apparatus for offshore installation, the wind energy harvesting apparatus comprising: an elongated wind turbine body extending along a longitudinal wind turbine body axis, the wind turbine body comprising a lower body portion to be below a water surface when the wind energy harvesting apparatus is in operation and an upper body portion to be above the water surface when the wind energy harvesting apparatus is in operation; wind turbine blades attached to the upper body portion for converting wind energy to rotation of the wind turbine body around the longitudinal wind turbine body axis; an energy converter attached to the wind turbine body for converting the rotation of the wind turbine body in relation to a non-rotatable part to electrical energy; and anchorage means connecting the non-rotatable part to at least one anchor point via at least one float body.

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A slot extends longitudinally in the skin passage. A resupply hole fluidly interconnects the core passage and the slot.