Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a damping strip seal. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The damping strip seal extends circumferentially into the first shroud segment and the second shroud segment to block gases from passing between the first shroud segment and the second shroud segment.

Abstract: A stator vane for a turbomachine, including an airfoil having a leading edge and a trailing edge, which are interconnected by a suction side and a pressure side, the airfoil extending substantially in a radial direction between an inner platform and an outer platform, wherein, when viewed in an axial direction of the turbomachine toward the trailing edge, the trailing edge extends so as to be inclined at a first angle to the pressure side radially on an outside in relation to the radial direction at a circumferential position at which the trailing edge meets the outer platform, and wherein the first angle between the trailing edge and a tangent to the outer platform at a transition from the outer platform to the trailing edge is between 72° and 84°.

Abstract: The present invention relates to a blade (7) comprising: —a composite material structure (17), —a blade root fastening portion (9) further comprising a shoulder (10) extending into the recess from the wall —a base (18) arranged in the recess and comprising a support member configured to abut against the shoulder (10) of the blade root fastening portion (9) and a passage (39) formed in the support member, the sections (23) of the blade root portion (22) of the composite material structure extending through the passage (39), and —a blocking part (19) arranged in the recess between the two sections (23) of the blade root portion (22) such that each section of the blade root portion (23) is pressed against the support member by the blocking part (19).

Abstract: A method (800,900) of assembling or disassembling a rotor blade of a wind turbine, the wind turbine comprising a tower, a nacelle mounted on the tower and a rotor coupled to the nacelle, the rotor having a rotor hub and a rotor blade, the rotor blade comprising a first blade segment connected with the rotor hub, a second blade segment, wherein the second blade segment is configured for joining to the first blade segment such that the second blade segment extends from the first blade segment towards a blade tip of the rotor blade, and a releasable locking device configured for joining the second blade segment to the first blade segment, the releasable locking device comprising a structural member of the second blade segment, the structural member being configured for engaging a further structural member of the first blade segment for releasable locking with the further structural member, wherein a fastening device of the second blade segment is arranged on the structural member; the method comprising raising (

Abstract: A rotor blade assembly includes a rotor blade having inboard and outboard regions, a blade body, and an internal spar, the blade body defining leading and trailing edges. A trailing edge assembly extends from and is connected to the trailing edge, and has a trailing edge flap and an actuator configured to deploy the trailing edge flap between first and second positions. In one of the first and second positions, an upper surface of the trailing edge flap conforms in profile to an upper surface of the rotor blade, and in the other, the trailing edge flap is inclined relative to the blade. During hovering flight, at least one trailing edge flap segment is deflected to enhance hover performance. During forward flight, at least one trailing edge flap segment is either not deflected for reduced effect on forward flight or is deflected for additional thrust.

Abstract: A method and device for determining a suction height of a variable speed unit is provided. The method includes: acquiring a reference cavitation coefficient and a reference specific rotation speed parameter corresponding to a target water head section in a preset number of power stations; conducting calculations on the reference cavitation coefficient and the reference specific rotation speed parameter by utilizing a target scheme to obtain a target formula; acquiring a maximum lift, a minimum lift, a speed variation range and a synchronous rotation speed value of a current target variable speed unit and input force values of the target variable speed unit at a plurality of key working condition points; and determining a target suction height of the target variable speed unit.

Abstract: A flow path component assembly includes a flow path component that has a plurality of segments that extend circumferentially about an axis. At least one of the segments have a first radial side and a second radial side and extend from a first circumferential side to a second circumferential side. A mateface seal is arranged on the first radial side near the first circumferential side. The mateface seal has a v-shaped groove.

Abstract: An improved stator assembly for use in a gas-turbine engine is disclosed. The stator assembly may comprise a vane, an inner diameter (ID) ring, an outer diameter (OD) ring, a vane disposed between the ID ring and the OD ring, a potting component coupling the vane to at least one of the OD ring or the ID ring, and a potting embedded component disposed within the potting component. The potting embedded component may prevent disbond of the potting component during operation of the gas-turbine engine.

Abstract: A runner for a hydraulic machine comprising a band, a crown, a plurality of blades extending between the crown and the band, wherein the runner comprises a plurality of runner segments which together define the runner, each runner segment comprising a band portion, a crown portion and a blade, which portions are integrally formed with one another, each runner segment being attachable to another segment at a band joining edge and a crown joining edge, wherein the band joining edge and the crown joining edge are each spaced apart from the blade of the segment.

Abstract: The invention relates to a portion of a turbofan (1) extending about a longitudinal axis (A), comprising: —an outer wall (Pe) and an inner wall (Pi), defining a secondary duct portion (Vs), —a cascade of guide vanes (OGV), each guide vane extending within the secondary duct portion (Vs) between the outer wall (Pe) and the inner wall (Pi), wherein, in the region of the cascade of guide vanes (OGV), and in a plane orthogonal to the longitudinal axis (A), the distance from the outer wall (Pe) to the longitudinal axis (A) along a first axis (Xi) orthogonal to the longitudinal axis (A) is greater than the distance from the outer wall (Pi) to the longitudinal axis (A) along a second axis (X2) orthogonal to the longitudinal axis (A) and to the first axis (X1).

Abstract: A turbomachine comprising a cone positioned at an upstream end and secured in rotation to the low-pressure shaft, a system for deicing said cone, comprising resistive heating elements positioned in the cone, an energy transfer system, an electrical power source coupled to the high-pressure shaft and connected to the energy transfer system by a set of switches, and a computer configured so as to define a power set point for deicing the cone depending on ambient temperature and pressure data, and on an operating speed of the low-pressure shaft, and, depending on the electrical power supplied by the electrical power source, define a duty cycle of the set of switches to deliver electrical power to the resistive heating elements.

Abstract: Disclosed is side liner for a centrifugal pump. The side liner comprises an aperture for access to a central chamber of the centrifugal pump through the side liner. The side liner also comprises a plurality of grooves on a surface contacting material pumped by the centrifugal pump, the plurality of grooves extending radially from an inner edge of the surface, located near the aperture, to an outer edge.

Abstract: An instrumented vane body is provided that includes a suction side and pressure side outer walls, an interior cavity, at least one supply conduit, a plurality of sensors, and a plurality of sensor ports. The suction and pressure side outer walls extend chordwise between leading and trailing edges and between inner and outer radial ends. The supply conduit is in fluid communication with the interior cavity, and is in communication with the interior cavity through at least one of the inner or outer radial ends. The sensor ports are disposed in the leading edge and each is configured to receive a sensor, and are spaced apart from one another. Each sensor port is in fluid communication with at least one vent aperture, and each is configured to permit core gas to enter that sensor part and exit the vane body through the at least one vent aperture.

Abstract: Tangential onboard injector assemblies include a TOBI and a TOBI blocker assembly arranged upstream of an inlet of the TOBI. The TOBI blocker assembly includes a first blocker plate upstream from the inlet and defining a blocker cavity between the first blocker plate and the TOBI. The first blocker plate includes a blocking portion and a filter portion to permit airflow therethrough. A second blocker plate is arranged within the blocker cavity to obstruct a flow of air containing particulate matter and a gap is present between the second blocker plate and the first blocker plate to permit flow of air around the second blocker plate. A third blocker plate is arranged downstream from the second blocker plate within the blocker cavity and includes a feed hole. Air within a region between the second blocker plate and the third blocker plate flows through the feed hole into the TOBI.

Abstract: An open impeller for a submergible pump for pumping abrasive fluids. The impeller has a cover plate, a hub and at least two spirally swept blades, each blade having a leading edge, a trailing edge, and a lower edge extending from the leading edge to the trailing edge and separating the suction and pressure sides of the blade. At least one blade includes a winglet at the lower edge projecting from the suction side, located radially outside an inner radius of the impeller, and extending circumferentially to the trailing edge at the suction side at a maximum radius of the impeller. The lower edge and winglet lower wear surface are configured to be located opposite of and facing a pump wear plate. The inner radius is equal to the largest of the maximum radius of the impeller multiplied by 0.6, and an inlet radius of the impeller multiplied by 1.2.

Abstract: A turboprop engine includes a main nacelle body, a rotatable hub provided on the main nacelle body, a plurality of propellers connected to the rotatable hub, and a nacelle extension coupled to the main nacelle body, the nacelle extension including at least one wall defining an air intake inlet. The air intake inlet is movable in an airflow axis with respect to a trailing edge of a propeller in the plurality of propellers to vary a distance between the air intake inlet and the trailing edge of the propeller during various phases of operation of the turboprop engine.

Abstract: A propeller fan includes a hub rotatable about an axis, and a plurality of blades extending radially outward from an outer peripheral surface of the hub. A ring surrounds the plurality of blades and is connected to each blade tip. A maximum camber location is on a camber line where a distance from a chord line to the camber line in an arc-shaped cross section of each blade about the axis is maximum. An axial height is from a trailing edge to the camber line in a direction along the axis. Each blade has a first portion provided inside in the radial direction of rotation and whose axial height at the maximum camber location is substantially constant, and a second portion provided outside in the radial direction of rotation and whose axial height at the maximum camber location increases toward the blade tip.

Abstract: A kite control system for controlling a kite which includes a plurality of rotators, a plurality of guiding elements locatable between each of the plurality of rotators and the kite, a plurality of adjustable deflectors, a plurality of deflector guides configured to adjust the operational length of the kite connecting line upon adjustment of the deflector, at least one invert correlator for, when in use, inversely correlate the adjustment of the operative length of the respective kite connecting lines, wherein the plurality of kite connecting lines includes the connection of at least one of the kite connecting lines at the kite biased towards the leading end region of the kite, and the connection of at least another kite connecting line biased towards the trailing end region of the kite.

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.

Abstract: An aircraft turbine engine includes a turbine shaft having a first axis of rotation, a propulsion propeller having a second axis of rotation parallel to and spaced from the first axis, and a mechanical reduction gear coupled to the turbine shaft and rotating the propeller. The reduction gear has a sun gear connected to the turbine shaft, a ring gear, and at least two planet gears, each including a first external toothing that is meshed with an external toothing of the sun gear. A second external toothing is located within the ring gear and is meshed with an internal toothing of the ring gear.