Abstract: A turbine system component includes a body having an exterior surface, and a cooling passage defined in the body. The cooling passage has a first cross-sectional area in the body. The component also includes a hollow member defining a first exit opening at the exterior surface of the body and coupled in the cooling passage. The hollow member, at the first exit opening, has a second cross-sectional area that is less than the first cross-sectional area, creating an exit opening with a smaller dimension than the original cooling passage. The hollow member is made of a material having a melt temperature higher than an operating temperature of the turbine system. The hollow member(s) reduces the cooling capabilities of the cooling passage. A cooling profile of the component can be generated to identify those cooling passages having excess cooling so they can have their exit openings reduced in cross-sectional area.

Abstract: A method for preventing damage to a multiphase pump includes measuring a differential pressure of a fluid across the pump and an axial position of a rotor of the pump over a time period, calculating a pressure fluctuation by measuring a difference between a maximum and a minimum value of the measured differential pressure over the time period, calculating a dynamic axial position by measuring a difference between a maximum and a minimum value of the measured axial position of the rotor over the time period, comparing the calculated pressure fluctuation with an expected pressure fluctuation value, comparing the calculated dynamic axial position with an expected dynamic axial position value, and selecting an operating condition of the pump based on the comparison of the calculated pressure fluctuation with the expected pressure fluctuation value and of the calculated dynamic axial position with the expected dynamic axial position value.

Abstract: Centrifugal compressors can incorporate a side stream flow of intermediate pressure vapor between stages of that compressor. The side stream flow can be controlled by a side stream injection port controlled by a throttle ring disposed between stages of the compressor. The throttle ring can allow or obstruct flow through the side stream injection port. The throttle ring can extend and retract in a direction substantially perpendicular to the direction of flow from the first stage impeller to the second stage impeller. A method of operating a centrifugal compressor can include actuating a throttle ring by rotating a drive ring to adjust a flow of interstage fluid into the second stage impeller.

Abstract: An exo-bearing system for a turbomachine is operable to improve aerodynamic efficiency and mechanical limits of rotor blades for fans, compressors, turbines, pumps and the like. The exo-bearing system is positioned between the tips of the blades and a surrounding structural housing. The exo-bearing system eliminates the air gap that is formed in prior art turbomachines and causes the blades to load in compression during operation which increases mechanical operability of the blades.

Abstract: A fan including a frame and an impeller is disclosed. The frame has an air inlet and an air outlet. The impeller is disposed in the frame and includes a hub and multiple blades. Each blade has a negative pressure surface facing the air inlet, a positive pressure surface facing the air outlet, a blade root, and a blade tip opposite to the blade root. In a first region extending from the blade root to the blade tip by a first length, the negative pressure surface and the positive pressure surface are respectively a convex arc surface and a plane. In a second region extending from the blade tip to the blade root by a second length smaller than the first length, the negative pressure surface and the positive pressure surface are respectively a convex arc surface and a concave arc surface or both are convex arc surfaces.

Abstract: A horizontal axis wind turbine comprising a rotor having a plurality of blades, the rotor having a radius R of at least 80 meters, the blades comprising: a root end and a tip end, the blades extending in a spanwise direction from the root end to the tip end; a leading edge and a trailing edge, the blades extending in a chordwise direction along a chord from the leading edge to the trailing edge; a shoulder between the root end and the tip end where a chord length defined between the leading edge and the trailing edge is at a maximum; the blades being twisted between the root end and the tip end and the twist is defined by a twist distribution curve along the spanwise direction of the blades, each blade further comprising: an inboard region between the root end of the blade and the shoulder of the blade; an outboard region between a rotor radius 0.

Abstract: The invention relates to a rotor blade (10) for a turbomachine, in particular of an aircraft, comprising an airfoil (12) comprising a pressure face (15) and a suction face (17) extending from a leading edge (14) to a trailing edge (16), the airfoil (12) comprising an axis of elongation extending substantially along the leading (14) and trailing (16) edges, the airfoil (12) comprising a radially firmer end for connection to a rotor and a free radially outer end. According to the invention, the airfoil (10) further comprises at least one series of fins (24) situated on said free end, each of these fins (24) comprising a pressure face (26) situated on the suction face (17) side of the airfoil (12), and a suction face (28) situated on the pressure face (15) side of the airfoil (12).

Abstract: A system for controlling the pitch of a propeller blade for an aircraft turbine engine, including a cup having an annular wall extending about an axis intended to be a pitch setting axis of the blade, and a bottom wall configured so as to cooperate in a form-fitting manner with a free end of the root so that the cup is prevented from rotating relative to the root about the axis, and a locking ring that is configured so as to be mounted within the cup and to cooperate respectively with the root and the annular wall of the cup in order to ensure axial retention of the root in the cup.

Abstract: An airfoil element has first and second ribs each connecting the pressure side and the suction side. Each of the first and second ribs define: a tube portion circumscribing a rib passage; and first and second connector arms joining the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel having a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. At least one of the pressure side portion and the suction side portion includes a skin passageway between at least one of the respective tube portions of the first rib and second rib and an adjacent portion of an interior surface of the airfoil wall. The skin passageway has an outer surface formed by the adjacent portion and an inner surface formed by said at least one of the respective tube portions.

Abstract: A method of controlling a plurality of wind turbines of a wind park includes: determining an axial induction zone of at least a wind turbine of the wind park; and modifying the axial induction zone for controlling wind farm blockage by adjusting at least one of the following operational variables: a yaw angle of a blade rotor of the wind turbine, a pitch offset angle of at least one blade of the blade rotor, a rotor speed of the blade rotor.

Abstract: A fan is disclosed. The fan includes a base mountable to a ceiling; a base motor contained in the base; a multi-section shaft operably connected to the base motor and moveable between a collapsed position and an extended position; and a fan assembly connected to the multi-section shaft and including a fan motor and at least one fan blade operably connected to the fan motor, wherein in response to a signal, the base motor raises or lowers the fan assembly by moving the multi-section shaft between the collapsed position and the extended position.

Abstract: A turbocharger includes: an oil drainage path formed in a radial bearing support, one end of the oil drainage path being opened on at least one of a surface facing a thrust bearing and a surface facing a supported portion in the radial bearing support, the other end of the oil drainage path being opened on a bottom surface of the radial bearing support, an entire projected surface of the oil drainage path projected along a central axis thereof to an oil outlet being included within the oil outlet; and an oil drainage space provided between the thrust bearing and an impeller and connected to an oil chamber.

Abstract: Proposed is a through type drain pump for a fluid draining apparatus of a fluid pipe. The drain pump includes: a housing formed in a hollow cylindrical shape, the housing being configured such that a fluid inlet port and a fluid outlet port are in communication with each other via a fluid movement path; a rotary shaft having a driving motor, the rotary shaft being rotatably coupled to an output shaft of the driving motor via a coupler; an impeller formed at a lower end of the rotary shaft and configured to be rotated so that the fluid is moved to the fluid outlet port through the fluid movement path; and a mounter mounted at a lower outer side surface of the housing and configured to mount the drain pump on any pipe such that the drain pump is capable of being lifted and inserted into the pipe.

Abstract: A propeller control system of an air mobility is configured to insert a movable part forming a propeller into a fixed part in a situation where the air mobility is stored and crashes, thereby reducing an entire length of the propeller. As a result, an entire size of the air mobility is reduced when the air mobility is stored, which may prevent secondary accidents caused by fragments generated by contact of the rotated propeller with the ground in the situation where the air mobility crashes.

Abstract: A turbine shroud assembly for a gas turbine engine includes a shroud wall extending circumferentially partway around a central reference axis to define a gas path of the gas turbine engine. An attachment feature extends radially from the shroud wall. A foam is located at least on the shroud wall.

Abstract: A seal assembly in a gas turbine engine is presented. The seal assembly is arranged at a forward side of an inner compressor exit diffusor. The seal assembly is arranged between an outlet guide vane assembly and the forward side of the inner compressor exit diffusor to reduce cooling air leakage therebetween or is arranged between adjacent outlet guide vane assemblies to reduce cooling air leakage therebetween. The seal assembly includes a plurality of seal segments. The seal assembly includes at least one seal, such as a brush seal.

Abstract: A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.

Abstract: Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments may involve a flow loop that at least in part flows through the interior of the tie bolt or by way of a venting arrangement that at least in part extends through one of the rotor shafts of the rotor structure. Disclosed embodiments may further benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of the process fluid being processed by the compressor. In operation, the flow loop may be appropriately pressurized to keep any residual seal leakage that may develop in one or more of the seal elements from travelling onto the hirth couplings.

Abstract: A rotary machine is disclosed, which includes a rotary shaft having a rotation axis, a first shaft end, and a second shaft end; a first bearing arrangement at the first shaft end; a second bearing arrangement at the second shaft end; a coupling flange mechanically connected to the first shaft end. The coupling flange is mechanically connected to the first shaft end by means of a first axial-contact coupling.

Abstract: The present application provides an inducer seal configured to provide a flow of air to a rotor shaft within a turbine of a gas turbine engine. The inducer seal includes a ring plate having an outer surface with a circumferential channel and an inner surface having an abradable seal. A number of inducer slots are positioned in the ring plate that extend from the outer surface to the inner surface such that the flow of air may pass therethrough in a tangential direction relative to rotation of the rotor shaft to cool the rotor shaft.