Abstract: The present disclosure is directed to a method for reducing loads of a wind turbine. The method includes monitoring, via a turbine controller, a rotor blade of the wind turbine for faults. If a fault is detected, the method includes determining an operational status of the wind turbine. If a predetermined operational status is present at the same time the fault is present, the method also include actively yawing a nacelle of the wind turbine away from an incoming wind direction until either the fault is corrected or cleared and/or the operational status changes.

Abstract: An impeller wheel of a turbocompressor, for rotation about an axis, has an inflow cross-section for inflow of a process fluid into the impeller wheel, an outflow cross-section for outflow of the process fluid from the impeller wheel, a wheel disk that defines a hub-side deflection contour from the axial flow direction into the radial flow direction. Blades are applied to the wheel disk, which define flow channels through the impeller wheel, each blade defining a linear inner track and a linear outer track. A meridional angle is defined for each position of a track as the upstream included angle between a meridional plane through the position and a tangent on the track. So that the flow passes through the impeller wheel with improved efficiency, as far as possible without separation, a local extremum of the meridional angle of the inner track is defined.

Abstract: A gas turbine startup method and device wherein low-pressure, medium-pressure, and high-pressure air bleed flow paths supply compressed air bled from low-pressure, medium-pressure, and high-pressure air bleed chambers, respectively, of a compressor as cooling air to a turbine. Low-pressure, medium-pressure, and high-pressure exhaust flow paths discharge the compressed air in the low-pressure, medium-pressure, and high-pressure air bleed flow paths, respectively to the turbine exhaust system, and the low-pressure, the medium-pressure, and the high-pressure exhaust flow paths are provided respectively with a low-pressure exhaust valve, a medium-pressure exhaust valve, and a high-pressure exhaust valve. When the gas turbine starts up, the high-pressure exhaust valve is opened before the startup state of the gas turbine reaches a region in which rotation stall occurs.

Abstract: A method of preventing surge in a dynamic compressor is disclosed. The method includes providing an anti-surge valve having an adjustable opening for increasing the flow through a dynamic compressor. The next step is sensing process conditions in the dynamic control to determine a compressor load variable. A control system estimates a process disturbance model using the compressor load variable. The control system then adjusts a safety margin using a rate limited response and initiates a closed loop response using process feedback based on the process disturbance model. The control system adjusts the opening of the anti-surge valve according to the safety margin and closed loop response.

Abstract: An apparatus and method regarding an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction, at least one cooling passage extending radially within the interior and defining a primary cooling airflow, and at least one cooling hole having an inlet in communication with the cooling passage and an outlet in communication with the exterior of the outer wall.

Abstract: A blower having high efficiency and low noise by actively controlling airflow in the blower, and an air conditioner having the blower is provided. The air conditioner has a blower. The blower includes a fan having a hub and at least one blade provided on an outer circumferential surface of the hub, a motor to rotatably drive the hub, a shroud configured to surround the periphery of the fan and at least one actuator installed in the shroud and configured to form an airflow along an inner circumferential surface of the shroud.

Abstract: The invention is applicable to industrial gas turbines to reduce the load consumed by the gas turbine compressor and to maximize the turbine mass flow.

Abstract: A turbine engine with a stator having axially spaced first and second structural elements along with a rotor and a face seal between the rotor and the stator including a non-rotating gas bearing face coupled to the first and second structural elements, and a rotating gas bearing face coupled to the rotor and confronting the non-rotating gas bearing surface. Introducing airflow to one or multiple parts of the seal.

Abstract: The diffuser pipe assembly for a compressor of a gas turbine engine includes diffuser pipes circumferentially distributed around a central axis and configured for distributing a flow of compressed air from the compressor to the combustor. Each of the diffuser pipes curving between an inlet end and an outlet end. A first subset of the diffuser pipes has a natural vibration frequency different than a natural vibration frequency of at least a second subset of the diffuser pipes. A method of operating a compressor including the diffuser pipe assembly is also disclosed.

Abstract: A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.

Abstract: A blade outer air seal (BOAS) includes a tube of a ceramic matrix composite (CMC) material. A preform within the shell defines a mount for the BOAS. The preform is of a CMC material. A gas turbine engine and a method of forming a blade outer air seal (BOAS) are also disclosed.

Abstract: A compressor shroud assembly in a turbine engine having a dynamically moveable shroud for encasing a rotor segment. The rotor segment comprises a bladed disc. The compressor shroud assembly maintains a clearance gap between the shroud and the blade tips of the bladed disc. The assembly comprises a static compressor casing, a shroud mounted to the casing, and an actuator mounted to the casing. The shroud comprises a flowpath boundary member spaced radially inward from the casing, the flowpath boundary member being moveable relative to the casing in a radial direction. The actuator is coupled to the shroud for effecting the movement of the flowpath boundary member.

Abstract: An interlocking shroud assembly for a turbine engine includes at least two shroud elements, each having confronting radial ends that define a split interface with axial fore, aft, and circumferential portions.

Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.

Abstract: A shroud assembly may comprise a first ring, a second ring aft of the first ring, and a shroud disposed between the first ring and the second ring. The shroud may comprise a plurality of circumferentially adjacent shroud segments. Each shroud segment of the plurality of circumferentially adjacent shroud segments may extend axially from the first ring to the second ring.

Abstract: A low-pressure compressor for a turbine engine, such as an aircraft turbojet engine includes a rotor with two rows of rotor blades between which two annular ribs are positioned; and one annular row of stator blades between the rotor blades. An internal shroud is connected to the stator blades. The internal shroud includes abradable material collaborating with the annular ribs, and annular teeth made of an abradable material and which extend radially towards the rotor, so as to provide sealing. The system may be used in a method for manufacturing a bypass turbojet engine compressor.

Abstract: A method of operating a multi-engine, rotary wing aircraft in a single engine, in-flight mode, the method includes stopping a first engine while operating a second engine; closing variable inlet guide vanes on the first engine; and turning a gas generator of the first engine at a reference rotational speed.

Abstract: An electric actuator for inlet guide vanes of a gas turbine engine, the electric actuator including a fixed portion secured to a stationary portion of the engine and a movable portion that is mechanically connected to the inlet guide vanes, stationary electromagnets distributed at regular intervals around the periphery of the movable portion and fastened to the fixed portion, and movable electromagnets arranged between the stationary electromagnets, each movable electromagnet being secured on either side to first and second piezoelectric elements, the movable electromagnets and the first and second piezoelectric elements having a degree of freedom of movement relative to the movable portion and having inside faces forming a common line of contact that is tangential to the movable portion.

Abstract: An air moving device includes a housing member, an impeller assembly, and a nozzle assembly. The nozzle assembly can include one or more angled vanes set an angle with respect to a central axis of the air moving device. The air moving device can output a column of moving air having an oblong and/or rectangular cross-section. A dispersion pattern of the column of moving air upon the floor of an enclosure in which the air moving device is installed can have an oblong and/or rectangular shape. The dimensions of the dispersion pattern may be varied by moving the air moving device toward or away from the floor, and/or by changing the angles of the stator vanes within the nozzle assembly.

Abstract: A small aero gas turbine engine with an axial thrust limiter device that uses compressed air acting on a rotating disk extending from a rotor of the engine in which a forward pressure chamber and an aft pressure chamber applies a pressure to both sides of the rotating disk. When rotor is shifted, one side of the rotating disk has an increase in pressure acting on it to shift the rotor in an axial direction. Each pressure chamber includes an upper variable restriction and a lower variable restriction in which the restriction varies due to axial movement of the rotor. A forward and an aft foil bearing can also be used in addition to axial balance the rotor when not enough pressure is available such as at engine startup.

Abstract: A method to dispose at least one air guiding tube between a penstock and a water turbine installed on a dam to form negative pressure at an outlet of the air guiding device by the water kinetic energy produced from high speed of water flow to take in external air for pressurizing, so as to produce a plurality of pressured air bubbles mixed into the water. The water with pressured air bubbles would be decompressed when flowing to an exit of the penstock and has their volumes increased, so as to enhance the water kinetic energy for driving the water turbine more efficiently; meanwhile the method can prevent from production of cavities and further avoid damages of the components of the water turbine from cavitation.

Abstract: Diagnostic systems and methods for a surge valve that selectively bypasses a compressor of a turbocharger of an engine involve receiving, by a controller, a barometric pressure signal indicative of a barometric pressure external to the engine, receiving, by the controller, a throttle inlet pressure (TIP) signal indicative of an air pressure at an inlet of a throttle valve of the engine and downstream from the surge valve and the compressor, and performing, by the controller, a diagnostic technique on the surge valve, the diagnostic technique comprising generating a pressure ratio signal that is a ratio of the TIP signal to the barometric pressure signal, applying a high-pass filter to the pressure ratio signal to obtain a filtered pressure ratio signal, and based on a quantity of detected pulses in the filtered pressure ratio signal that exceed the diagnostic threshold, detecting a malfunction of the surge valve.

Abstract: The present invention provides a turbocharger including: a rotating shaft; a turbine wheel; a compressor wheel; a rolling bearing including an inner race fixed to an outer circumferential surface of the rotating shaft, an outer race surrounding the inner race from the outside in a radial direction, and rolling bodies arranged between the inner and outer races and that supports the rotating shaft to be rotatable about an axis; a housing that covers the rolling bearing from an outer circumferential side via a gap between the housing and an outer circumferential surface of the rolling bearing; and a lubricant supply line configured to supply a lubricant into the housing. The turbocharger includes an operating state detection unit that detects an operating state of the turbocharger and a lubricant regulating unit configured to regulate the flow rate of the lubricant flowing through the lubricant supply line depending on the operating state.

Abstract: Embodiments of the present invention provide methods and apparatus for increasing turbulent mixing in the wake of at least one wind turbine. Doing so, increases efficiency of a wind turbine located in the wake by transferring energy to the wake that was lost when the wind passed through the upwind turbine. Turbulent mixing may be increased by changing the induction factor for a rotor by, for example, altering the pitch of the blades, the RPMs of the rotor, or the yaw of the nacelle. These techniques may be static or dynamically changing. Further, the different induction factors for a plurality of wind turbines may be synchronized according to a predetermined pattern to further increase turbulent mixing.

Abstract: A method of calibrating load sensors of a wind turbine, and a wind turbine for such load sensor calibration, are disclosed. The wind turbine comprises a rotor, a plurality of rotor blades, and a plurality of load sensors associated with the rotor blades. While the rotor is rotating, at least one of the rotor blades is moved from a first calibration position to a second calibration position, and load values from the load sensors are measured. The number of rotor blades being moved is at least one fewer than the number of the plurality of rotor blades. The rotation of the rotor may be during idling of the wind turbine. The movement of the blade(s) may be to change the pitch angle of the blade(s). At least one of the rotor blades not being moved to a calibration position may also be moved, for example to control the rotational speed of the rotor.

Abstract: There is provided a seal structure to suppress a leak flow of a working fluid from a gap between a rotating structure and a stationary structure, the rotating structure being configured to rotate in a prescribed direction about an axial center line, the stationary structure facing an outer periphery of the rotating structure in a radial direction with the gap inbetween, wherein the stationary structure has a cavity in which the rotating structure is accommodated, an inner peripheral surface of the cavity is provided with a seal fin that extends toward the axial center line and a plurality of stationary-side recesses arranged along a flow direction of the leak flow, and as compared with a first stationary-side recess disposed on a most upstream side, a second stationary-side recess disposed on an immediately downstream side of the first stationary-side recess is set to have a smaller depth dimension.

Abstract: Various fluid turbine systems and methods are described. The turbine can be a vertical axis wind turbine configured to generate power from wind energy. The turbine system can have a blade assembly. The blade assembly can have a plurality of blades rotatable about an axis. The turbine system can have a concentrator positionable upwind and in front of a return side of the blade assembly. The concentrator can define a convex surface facing the wind. The turbine system can also have a variable concentrator positionable upwind of a push side of the blade assembly. The variable concentrator can be adjustable between a first position and a second position, the variable concentrator being capable of deflecting more wind toward the turbine in the first position than in the second position.

Abstract: Provided is a control device of a gas turbine including a compressor, a combustor, and a turbine. The control device executes load control of allowing an operation control point for operation control of a gas turbine to vary in response to a load of the gas turbine. The operation of the gas turbine is controlled on the basis of a rated temperature adjustment line for temperature adjustment control of a flue gas temperature at a predetermined load to a rated flue gas temperature at which performance of the gas turbine becomes rated performance, a preceding setting line for setting of the flue gas temperature at the predetermined load to a preceding flue gas temperature that becomes lower in precedence to the rated flue gas temperature, and a limit temperature adjustment line for temperature adjustment control.

Abstract: The invention provides a system for creating a prescribed vibration profile on a mechanical device comprising a sensor for measuring an operating condition of the mechanical device, a circular force generator for creating a controllable rotating force vector comprising a controllable force magnitude, a controllable force phase and a controllable force frequency, a controller in electronic communication with said sensor and said circular force generator, the controller operably controlling the controllable rotating force vector, wherein the difference between the measured operating condition and a desired operating condition is minimized.

Abstract: A wind farm that includes a plurality of wind power generation units. The wind farm further includes a sensing part and a controlling part. The sensing part is configured to sense an external environment risk element. The controlling part is configured to receive a risk signal from the sensing part and to control the wind power generation units in the wind farm.

Abstract: The invention relates to a system for controlling variable-setting blades (14) for a turbine engine, which includes at least one control ring (36) mounted rotatably mobile about an annular casing (16) with axis of revolution A, at least one annular row of variable-setting blades (14) extending substantially radially relative to said axis A and connected to said at least one control ring so that a rotation of the ring about the casing rotates the blades about substantially radial axes B, and means (40) for actuating said at least one ring in order to rotate same about the casing, characterised in that said actuation means are connected to said at least one ring by linking means comprising a shaft (52) extending along an axis C which is substantially radial relative to said axis A and mounted rotatably mobile about said axis C on the housing.

Abstract: A vane assembly for a gas turbine includes a first shroud segment, a second shroud segment, a first inner air seal, and a seal assembly. The first shroud segment has a first end face. The second shroud segment is disposed adjacent to the first shroud segment and has a second end face that faces towards and is spaced apart from the first end face by a gap. The first inner air seal extends into the first shroud segment and defines a first trench. The seal assembly at least partially received within the first trench.

Abstract: An arrangement for a gas turbine engine that includes a turbine blade configured to rotate about an axis, a casing radially outside of the turbine blade, and a carrier segment mounted to the casing so as to define a first impingement space therebetween. The carrier segment is positioned radially outside the turbine blade and includes a first impingement carrier wall, a main carrier wall, and a cooling chamber. The first impingement carrier wall is adjacent to and radially inside of the first impingement space, and the first impingement carrier wall includes a first aperture. The main carrier wall is radially inside of the first impingement carrier wall. The cooling chamber is radially inside of the main carrier wall. Additionally, an intermediate chamber is disposed radially between the cooling chamber and the first impingement space. A second aperture is configured to allow ingress of air into the intermediate chamber.

Abstract: A gear system for a turbofan engine assembly includes a sun gear rotatable about an engine centerline, a non-rotatable ring gear, a rotating carrier that drives a fan, and a plurality of planet gears intermeshed between the sun gear and the ring gear. Each of the plurality of planet gears supported on rolling element bearings fit into the carrier. Each of the plurality of planet gears includes an inner cavity and a lubricant passage directed at the rolling element bearings. The carrier includes an outer scoop that receives lubricant from an outer fixed lubricant jet and feeds lubricant into the inner cavity and through the lubricant passage to spray lubricant on to the rolling element bearings. A geared turbofan engine assembly is also disclosed.

Abstract: A gas compressor system is provided to operate at a well site and to inject a compressible fluid into a wellbore in support of a gas-lift operation. Methods and systems are provided that allow for the automated individual control of discharge temperatures from coolers for gas injection, in real time, wherein the temperature control points of the first and/or second stage cooler discharges are automatically controlled by a process controller in order to push heat produced by adiabatic compression to a third or final compression stage. In this way, discharge temperatures at the final stage are elevated to maintain injection gaseous mixtures in vapor phase.

Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span. A method of manufacturing a gas turbine engine component and a method of controlling flow in a gas turbine engine component are also disclosed.

Abstract: An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with a leading edge angle of less than 40° at 100% span.

Abstract: A turbine ring assembly comprises a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure including first and second annular flanges. In section, each ring sector presents a K-shape having an annular base-forming portion with an inside face defining the inside face of the turbine ring and an outside face with first and second S-shaped tabs projecting therefrom. The inside faces of the first and second tabs of each ring sector rest on holder elements secured to the first and second annular flanges, while the outside faces of the first and second tabs are in contact with clamping elements secured to the ring support structure.

Abstract: A gas turbine engine includes a bypass flow passage and a core flow passage. The bypass flow passage defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is located upstream of the bypass flow passage. The bypass flow passage includes an inlet and an outlet that define a design fan pressure ratio of approximately 1.3 to 1.55. A first, inner shaft and a second, outer shaft are concentric. A first turbine is coupled with the first shaft, and the first shaft is coupled with the fan. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number of the fan blades, the number (N) being 18, a solidity value (R) at tips of the fan blades that is from 1.0 to 1.1, and a ratio of N/R that is from 16.4 to 18.0.

Abstract: This method allows determining the operating point of a hydraulic machine in a considered operating range, such as turbine mode, and comprises steps that consist in a) determining two coordinates (N?11, T?11) of a first series of potential operating points of the hydraulic machine for the orientation affected to guide vanes of the machine, b) measuring the rotation speed of the machine, and c) determining the torque exerted by water flow on the machine. The method further includes steps consisting in d) calculating two coordinates (N11, T11) of a second series of potential operating points of the machine in function of the rotation speed (N) measured at step b) and the torque determined at step c), and e) deducing the two coordinates (N11_real, T11_real) of operating point that belongs both to the first and the second series in the said considered operating range of the machine.

Abstract: With regard to a load running system that comprises a plurality of compressors that compress a fuel gas and supply the compressed fuel gas to a load apparatus, this compressor control device comprises: a feedforward control signal generation unit that, on the basis of a value that is found by dividing the total load of the load apparatus by the number of running compressors, generates a first control signal that is for controlling the amount of fuel gas supplied by the compressors; and a control unit that, on the basis of the first control signal, controls the amount of fuel gas supplied by the compressors.

Abstract: A method for controlling a wind turbine is provided. The wind turbine is a turbine of the type that is operated to perform a control function that controls the amount of power produced based upon measures of fatigue life consumption of one or more turbine components. The method comprises initialising the control function by: over-riding or bypassing (405) the control function for a predetermined period of time, such that power produced by the wind turbine is not altered based upon the determined measures of fatigue life consumption; during the predetermined period of time, operating (407) one or more fatigue lifetime usage estimation algorithms, to determine a measure of the fatigue life consumed by each of the one or more turbine components; and after the predetermined period of time has elapsed, activating (409) the control function and using, in the control function, at least one of the measures of fatigue life consumption determined during the predetermined period of time.

Abstract: This disclosure provides assemblies for providing a bumper between an exhaust frame and a bearing housing in a gas turbine. The bumper or bumpers have an attachment surface for attaching to the exhaust frame and a bearing contact surface that engages the bearing housing during a blade out event.

Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle from 80% span to 100% span.

Abstract: Provided is a compressor capable of calculating the correct time remaining before maintenance. The compressor is provided with: a compressor body that compresses fluid; a motor that drives the compressor body; a temperature sensor that detects the temperature of the compressor; a pressure sensor that detects the pressure of the compressed fluid outputted from the compressor body; and a calculation unit that calculates the time remaining before maintenance for the compressor body, using the temperature of the compressor and the pressure of the compressed fluid assigned with respective predetermined weights. The calculation unit changes the weighting of the temperature according to the pressure of the compressed fluid or the operation rate of the compressor body.

Abstract: A turbine impeller includes: a hub portion coupled to an end of a rotational shaft; a plurality of main blades disposed at intervals on a peripheral surface of the hub portion; and a short blade disposed between two adjacent main blades among the plurality of main blades. An inter-blade flow channel is formed between the two adjacent main blades so that a fluid flows through the inter-blade flow channel from an outer side toward an inner side of the turbine impeller in a radial direction. In a meridional plane, a hub-side end of a leading edge of the short blade is disposed on an inner side, in the radial direction, of a hub-side end of a leading edge of the main blade.

Abstract: An active clearance control system of a gas turbine engine includes a radially adjustable blade outer air seal system movable between a radially contracted Blade Outer Air Seal (BOAS) position that defines a first air volume and a radially expanded Blade Outer Air Seal (BOAS) position that defines a second air volume, the second air volume different than the first air volume. An accumulator system accommodate a difference in air volume between the first air volume and the second air volume.

Abstract: A control device is configured to control a gas turbine that is configured to compress a suctioned air with a compressor to obtain compressed air, mix a fuel supplied from a combustor with the compressed air to burn the fuel and the compressed air to generate a combustion gas, operate a turbine with the combustion gas to rotate a rotor, and discharge the combustion gas that has operated the turbine as a flue gas. The compressor includes an inlet guide vane which is capable of adjusting a degree of opening and is on an air-suction side, and the control device is configured to execute temperature adjustment control to control the degree of opening of the inlet guide vane along a temperature adjustment line indicating an upper limit temperature of a flue gas temperature defined according to a load of the gas turbine.

Abstract: A method for controlling an active air flap (AAF) based on an aerodynamic force gain may include an AAF optimization cooling-related mode in which the AAF is configured to be controlled to operate in an AAF open state or an AAF close state to match a detected ambient temperature and a detected vehicle speed when an operation of a heating device is detected by a controller during vehicle traveling.

Abstract: A runner for a hydraulic turbine or pump has a plurality of blades. Each of the blades is defined by a pressure surface, an oppositely facing suction surface, a leading edge and a spaced-apart trailing edge. At least one of the blades has a device for supplying a flow of oxygen containing gas to the trailing edge of the same blade. The device includes at least two separate gas inlet apertures and at least two separate gas passages, each extending from one of the separate gas inlet apertures to a separate group of orifices in the trailing edge of the same blade. Each of the separate group of orifices has at least one orifice to admit gas out of the corresponding separate gas passage to the passing fluid during the operation of the runner.