1243results about "Engine control" patented technology

A wind energy plant with a nacelle, a rotor, which features at least one rotor blade adjustable in its blade pitch angle, a central control device for controlling the wind energy plant and a control unit disposed in the rotor for controlling the blade pitch angle of the at least one rotor blade, wherein the central control device and the control unit in the rotor can exchange data with each other via a data link, which comprises at least one first sending and receiving device at the nacelle side and at least one second sending and receiving device at the rotor side, wherein a wireless network connection with a safety-oriented communication protocol is provided between the at least one first sending and receiving device and the at least one second sending and receiving device, and that one monitoring- and communication device at a time is associated to the first and / or the second sending and receiving device, which can monitor the function of the sending and receiving device and initiate a predetermined action in the case of an error.

A gas turbine engine has a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. A combustor is operable with the first subset of fuel spray nozzles supplied with fuel at a greater fuel flow rate than each the second subset of fuel spray nozzles. A a ratio of the first subset of fuel spray nozzles to the second subset of fuel spray nozzles is 1:2 to 1:5. A first idle-MTO nvPM emissions index ratio is:EIidleEImaxTOwhere: EIidle is the system loss corrected nvPM emissions index in mg / kg operating at around 7% available thrust; and EImaxTO is the system loss corrected nvPM emissions index in mg / kg operating at around 100% available thrust; and the first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 60. A sustainable aviation fuel (SAF) can be provided to the fuel spray nozzles.

A method for providing gearbox lubrication of a wind turbine during an off-grid state includes fluidly coupling an auxiliary lubrication system with a gearbox of the wind turbine. The off-grid state is characterized in that the wind turbine is mechanically and electrically installed at a wind farm but not yet connected to a grid. The method also includes determining a time-based control scheme for the auxiliary lubrication system to provide lubrication to the auxiliary lubrication system during the off-grid state. The time-based control scheme is defined a first time period in which the lubrication is provided to the gearbox via the auxiliary lubrication system during the off-grid state and a second time period in which the lubrication is not provided to the gearbox via the auxiliary lubrication system during the off-grid state. The first time period is less than the second time period. Further, the method includes implementing, via a controller, the control scheme for the auxiliary lubrication system to provide the lubrication to the gearbox of the wind turbine during the off-grid state.

Fuel thermal management systems and related methods are disclosed. An example system includes a flowline to carry a fluid, a waste heat recovery heat exchanger coupled to the flowline, the waste heat recovery heat exchanger to heat the fluid to a first temperature, and a feed tank coupled to the flowline, the feed tank including a first inlet and a second inlet, the first inlet to receive a first portion of the fluid from the waste heat recovery heat exchanger at the first temperature, the second inlet to receive a second portion of the fluid at a second temperature less than the first temperature, wherein the first portion of the fluid and the second portion of the fluid mixes in the feed tank to form a third portion having a third temperature between the first temperature and the second temperature.

An assembly is provided for an aircraft powerplant. This assembly includes a vane structure and a heat exchanger. The vane structure extends longitudinally to a leading edge of the vane structure. The vane structure includes a translating body, a stationary body and an inlet passage. The translating body is configured to translate longitudinally between a first position and a second position. The translating body is configured to form the leading edge of the vane structure and close an inlet into the inlet passage when in the first position. The translating body is configured to open the inlet into the inlet passage when in the second position. The heat exchanger is disposed within the stationary body. The inlet passage projects into the stationary body from the inlet into the inlet passage to the heat exchanger.

The invention provides a controller for a wind turbine having three rotor blades, the controller being for controlling activation of individual pitch control of the rotor blades. The controller is configured to receive a flap load signal, from a flap loading sensor of each of the three rotor blades, indicative of flap loading on each of the respective rotor blades. The controller is configured to determine, based on the received flap load signals, a statistical dispersion parameter of flap loading for each of the rotor blades, the statistical dispersion parameters being indicative of a wind event in a wind field in which the wind turbine operates. The controller is configured to control activation of individual pitch control based on the respective statistical dispersion parameters.

Provided is a control method for de-icing blades of a wind power generator, including: Step S101: performing real-time monitoring of temperature of a surface of a blade of the wind power generator, and constructing a first positional temperature sequence at a time interval of v; and Step S102: calculating actual temperature at each position on the surface of the blade of the wind power generator according to the positional temperature sequence, and generating a second positional temperature sequence. In the present disclosure, it can be avoided that a discrepancy between the temperature acquired and the actual temperature of the surface of the wind power generator; and weight differences that may exist among three blades are taken into account, and synchronous de-icing operations are performed after eliminating the weight differences, so that ice treatment can be achieved without shutdown, and the stable operation of the wind power generator can be ensured.

A gas turbine engine has a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. A combustor is operable with the first subset of fuel spray nozzles supplied with fuel at a greater flow rate than each of the second subset of fuel spray nozzles. A ratio of the first subset of fuel spray nozzles to the second subset of fuel spray nozzles is 1:2 to 1:5. A first idle-MTO nvPM emissions index ratio is:EIidleEImax⁢TO,where: EIidle is the nvPM emissions index in mg / kg operating at around 7% available thrust; EImaxTO is the nvPM emissions index in mg / kg of the gas turbine engine operating at around 100% available thrust; and the first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 60. A sustainable aviation fuel (SAF) can be provided to the fuel spray nozzles.

The invention discloses a charging pile anti-condensation control system and method based on an internal and external humidity difference value, and belongs to the technical field of new energy automobile charging equipment. The system comprises an external humidity sensor arranged outside the charging pile and an internal humidity sensor arranged inside the charging pile. The external humidity sensor and the internal humidity sensor are both connected with a central processing unit, and the central processing unit is in communication connection with a cloud platform server; the central processing unit is further connected with a fan and a heating element which are arranged in the charging pile. The control method comprises the following steps: calculating a humidity difference value and a humidity difference value change rate according to acquired internal and external humidity data, performing fuzzification processing to obtain Ftarget and Ptarget, outputting a control signal to a fan and a heating module, recording and feeding back state data, judging whether delta H returns to normal or not, and after the delta H returns to normal, enabling a system to enter a low-power-consumption mode; and if not, continuously processing. According to the method, the potential condensation risk is identified more accurately by utilizing internal and external humidity comparison.

The invention relates to the technical field of fatigue load reduction, in particular to a wind power plant torque and variable pitch cooperative control method with fatigue load reduction as the target. The method comprises the following steps: acquiring real-time and historical operation data of each fan in a wind power plant, and preprocessing the operation data; based on the preprocessed operation data, load characteristic indexes reflecting structural fatigue are extracted, and a load state vector reflecting the current fatigue accumulation trend of the draught fan is constructed; and based on the load state vector, establishing a coupling model of the influence of the generator torque and the variable pitch angle on the rotating speed response and the fatigue load, wherein the coupling model is used for reflecting the influence mechanism of torque adjustment on the low-frequency load and the inhibition effect of variable pitch adjustment on the high-frequency load. According to the method, the load state vector fusing the low-frequency mechanical load and the high-frequency pneumatic excitation is constructed, and the rain flow counting and equivalent damage theory is combined, so that the load component which has the greatest influence on the fatigue life of key parts such as a main shaft, a transmission chain, a tower and a blade root is accurately identified.

Dynamic wake control (or dynamic induction control) is used to promote wake breakdown and recovery behind a wind turbine that improve wind farm performance / efficiency. Constructive interference is created by simultaneously performing harmonic rotor speed control and harmonic collective pitch control so that the phase of the rotor speed perturbations leads the phase of the collective pitch perturbations by 90-135 degrees.

A fuel system for a hydrogen-fueled gas turbine engine includes a main fuel conduit configured to conduct hydrogen fuel from a hydrogen storage unit to a core combustor of the gas turbine engine, a pre-heater including an auxiliary combustor configured to combust hydrogen fuel diverted from the main fuel conduit to heat hydrogen fuel in the main fuel conduit. A first exhaust passage is configured to conduct combustion products from the auxiliary combustor to the core combustor of the gas turbine engine.

A Surface-affixed, Storm-Resistant Containment Unit involves a shelter structure, with internally-mounted photovoltaic solar panels, and movable doors which may be ‘closed’ to protect the photovoltaic solar panels from storm-related damage, e.g. hail, extreme wind and airborne debris. When weather conditions improve, the movable doors may be ‘opened’, allowing sunlight to strike the undamaged photovoltaic solar panels, and renewable energy production to resume. These Storm-Resistant Containment Units may be installed, and electrically connected in multiples to comprise a storm-resistant, commercially-sized, renewable power generating station (or ‘Micro-Grid’) for use in geographic areas prone to severe storms and hurricanes. Such storm-resistant, commercially-sized, power generation station may be advantageously applied at existing ‘Brown-Field’ industrial sites that have existing, unused electrical-grid infrastructure.

An aircraft hybrid electrical propulsion (HEP) system includes an electrical system configured to deliver power to a plurality of electrical loads, a propulsion system configured to generate thrust in response to an input power, and an HEP controller in signal communication with the electrical system and the propulsion system. The HEP controller is configured to monitor a load demand of at least one electrical load among the plurality of electrical loads and to actively control the input power to actively control the thrust in response to changes in the load demand.

A method for controlling operation of a generator (5) for a wind turbine is disclosed. A measure for a rotational speed of the generator (5), and a measure for vibrations originating from gear tooth meshing of a gearbox (3) of the wind turbine, at the rotational speed of the generator (5), and at least one amplitude of a harmonic in the gearbox vibrations is determined. An initial phase angle and an initial amplitude are selected, based on the rotational speed of the generator (5), on initial characteristics of the wind turbine, and on the at least one amplitude of the harmonic in the gearbox vibrations. An optimization process is performed, including adjusting the initial phase angle and the initial amplitude in order to obtain a minimum in amplitude of a resultant vibration of vibrations originating from the gearbox (3) and vibrations originating from the generator (5), corresponding to the harmonic in the gearbox vibrations, thereby obtaining an adjusted phase angle and an adjusted amplitude. A torque modulating signal for the generator (5), specifying the adjusted phase angle and the adjusted amplitude, is generated and injected into the generator (5). Information regarding residual vibrations at the minimised resultant vibration is derived.

An automated system for mitigating risk from a wind turbine includes a plurality of optical imaging sensors. A controller receives and analyzes images from the optical imaging sensors to automatically send a signal to curtail operation of the wind turbine to a predetermined risk mitigating level when the controller determines from images received from the optical imaging sensors that an airborne animal is at risk from the wind turbine

A method for controlling a renewable energy farm (1) comprising a plurality of wind turbines (2) and at least one central control unit (5) is disclosed. The wind turbines (2) of the renewable energy farm (1) are connected to a power grid (3). The central control unit (5) receives a request for change in operation of at least one of the wind turbines (2), where execution of the change in operation causes a change in power output of the wind turbine (2). The central control unit (5) checks whether or not the change in power output is in conflict with at least one obligation of the renewable energy farm (1) towards the power grid (3). In the case that the change in power output is in conflict with at least one obligation of the renewable energy farm (1) towards the power grid (3), execution of the change in operation is deferred.

Gas turbine engines include an engine core having compressor, combustor, and turbine sections arranged within an engine casing. A transfer tube (404) is arranged on an exterior of the casing and configured to define a fluid conduit for fluid (410) to be transferred about the engine. A fitting (402) is connected to the transfer tube (404) and a seal assembly (406) is arranged between the fitting (402) and the transfer tube (404). The seal assembly (406) provides a fluid seal between the fluid conduit and an ambient environment (412) at a connection between the fitting (402) and the transfer tube (404). The seal assembly (406) includes a primary seal (414) arranged in a gap (413) between the fitting (402) and the transfer tube (404) and a secondary seal (416) arranged in the gap (413) between the primary seal (414) and an ambient environment (412). The secondary seal (416) is configured to expand into engagement with the fitting (402) and the transfer tube (404) when exposed to temperatures of at least 800 °F.

A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.

Device (1) for characterizing wear on a gas turbine engine comprising: - an abradable material (8) having a wear end (80) adapted to be in contact with a gaseous fluid flow (F) flowing from upstream to downstream of the gas turbine engine when the gas turbine engine is running, the abradable material (8) being electrically conductive; - a magnetic field generator (7) adapted to emit a magnetic field in the abradable material (8); - an electronic board (10) configured to calculate information enabling the characterization of the wear of the gas turbine engine from data relating to a physical response of said abradable material (8) to said magnetic field. Figure for the abbreviation: Figure 2.

The invention relates to activation of a pitch controller for controlling the pitch of a rotor blade of a wind turbine. The invention includes receiving a sensor signal from at least one sensor of the wind turbine, the sensor signal being indicative of oscillatory movement of a component of the wind turbine. The invention includes determining an amplitude of the oscillating motion of the component based on the received sensor signal, and determining a rate of change of the amplitude of the oscillating motion based on the determined amplitude. The invention includes controlling the activation of the pitch controller based on the determined rate of change of the amplitude of the oscillating motion.

A lean-burn combustor (16) comprising a plurality of lean-burn fuel injectors (50), each lean-burn fuel injector comprising a fuel supply arm (52) and a lean-burn fuel injector head (54) with a lean-burn fuel injector head tip (72), wherein the lean-burn fuel injector head tip has a lean-burn fuel injector head tip diameter (d), the lean-burn fuel injector head comprises a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially with the pilot fuel injector and radially outwardly; and a combustor chamber (60) extending in an axial direction (62) for a length (L) and comprising a radially inner annular wall (64), a radially outer annular wall (66) and a metering plate (68) defining the size and shape of the combustor chamber, wherein the combustor chamber comprises a primary combustion zone (80) and a secondary combustion zone (82).

Module (30) for an aircraft turbomachine (10), this module (30) comprising: - a lubrication chamber (38), - an oil supply circuit (40) for the chamber (38), - at least one pressure sensor (60) interposed in the flanges (32a, 34a) of the bearing supports (32, 34), and - an electronic control circuit (62) connected to said at least one pressure sensor (60) and to said oil supply circuit (40), this electronic circuit (62) being capable of commanding an emergency closure of said oil supply circuit (40) when said at least one sensor (60) detects a pressure below a predetermined threshold corresponding to a failure of the shear screws (42). Figure for the abbreviation: Figure 5

Disclosed is a method for quickly stopping the propulsion rotor of a helicopter after landing, comprising, following a request (100) by a pilot of the helicopter to quickly stop the engine, the following steps managed by the control unit of the turbomachine: - detecting (110) the absence of a thermal stabilisation phase of the gas generator of at least one turbomachine, - controlling (130) the extinguishing of the combustion chamber of the gas generator of at least one turbomachine, - maintaining the rotation of the gas generator (140) whose combustion chamber has been extinguished by means of the at least one electrical machine in order to ventilate the gas generator, and - stopping (160) the main rotor of the helicopter by means of a mechanical brake.

A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors (305) and main injectors (306), a fuel metering system (211) configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller (212). The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.

The invention belongs to the field of wind power generation, and particularly relates to a matrix double-helix wind generating set control system which comprises an energy capture and conversion module, a direct-current bus voltage stabilization and protection module, an intelligent power management module, a grid-connected inversion module and an intelligent monitoring and data interaction module which are electrically connected in sequence. The energy capture and conversion module comprises a wide-range high-efficiency rectification and active voltage stabilization unit, and the wide-range high-efficiency rectification and active voltage stabilization unit comprises a three-phase full-bridge rectification module and a super capacitor module. Three-phase alternating current output by the generator is converted into direct current through the three-phase full-bridge rectifier module, and the output end of the three-phase full-bridge rectifier module is connected with the super capacitor module in parallel. And the direct current bus voltage stabilization and protection module comprises a multi-protection and intelligent switching unit. The matrix double-helix wind generating set control system integrates wide-area energy management, active safety protection and intelligent state monitoring.

A hydraulically driven fluid injection system comprising a reservoir having a first and second chamber and a piston separating the first and second chamber. A reservoir control valve to control the input of a first fuel source to the first chamber. The reservoir control may operate by having an open and a closed state. Alternatively, the reservoir control may have a first mode, a second mode, and a third mode. A second fuel may be provided to the second chamber and a metering valve may be utilized to control the flow of the second fuel to an injector. When the secondary fuel is desired, the reservoir control valve may open to allow the primary fuel to pressurize the first chamber. The result of the pressure on the first chamber causes the piston to apply a pressure to the second chamber. The metering valve may then allow the secondary fuel to flow from the second chamber to an injector.

A method for controlling a wind turbine is disclosed. The wind turbine comprises three or more wind turbine blades, and blade connecting wires, each blade connecting wire extending between a connection point on one wind turbine blade and a connection point on a neighbouring wind turbine blade. The wind turbine further comprises pre-tension wires, each pre-tension wire being connected to one of the blade connecting wires and to a pre-tension adjustment mechanism. The method comprises measuring at least one parameter of the wind turbine blades of the wind turbine, and deriving an estimate for a blade flap load for each wind turbine blade from the at least one measured parameter. The pre-tension adjustment mechanism is controlled in response to the estimated blade flap loads of the wind turbine blades, thereby adjusting the pre-tension provided by the pre-tension wires.

The present invention relates to a pump-operation support method and a pump-operation support apparatus. The pump-operation support method includes: a performance-characteristic acquisition process of acquiring a flow-rate vs. total-pump-head typical performance curve in a rated operation and a rated rotational speed as performance characteristics of a support target device identified by the model number of a pump device; an installation-state acquisition process of acquiring an actual pump head as an installation state of the support target device; an operation-state acquisition process of acquiring operating frequency, suction pressure, and discharge pressure as an operation state of the support target device; and a first operation support process of calculating operating conditions in a reference operation of the support target device when the support target device is operated in the installation state and the operation state, wherein the first operation support process includes calculating flow rate and total pump head in the reference operation based on the performance characteristics, the installation state, and the operation state.