6123results about "Engine fuctions" patented technology

A handheld fan includes a housing, a fan module, a power module, and a retractable cable module. The fan module is disposed in the housing, the power module is disposed in the housing and configured to supply power to the fan module, the retractable cable module is disposed in the housing and includes a cable retractable relative to the housing to be withdrawn into the housing or extended out of the housing, and the cable is configured to connect to an external electronic device, and supply power to the external electronic device through the power module. When a user carries the handheld fan and has a charging need, the cable is capable of being pulled out of the housing of the handheld fan, and connected to the external electronic device including a mobile phone. The power module is configured to supply power to the external electronic device.

Heat exchangers for cryogenic fuel distribution systems and related methods are disclosed herein. An example aircraft disclosed herein includes a cryogenic fuel system including a cryogenic fuel, a hydraulic system including a hydraulic fluid, a gas turbine engine fluidly coupled to the cryogenic fuel system, and a heat exchanger fluidly coupled to the cryogenic fuel system, the heat exchanger is used to exchange heat between the cryogenic fuel and at least one of (1) hydraulic fluid or (2) working fluid thermally coupled to the hydraulic system.

A pump side part for use with a centrifugal slurry pump for pumping a fluid mixture containing particulate matter, the pump side part comprising a main body having a main axis, the main body including a side wall section which extends laterally with respect to the main axis and has opposite facing first and second sides, a plurality of formations on a surface of the second side including an inner formation and an outer formation in spaced relation to the inner formation, the formations being configured so that in use the formations generate a flow of the fluid mixture across the surface which detaches from the surface the particulate matter adjacent thereto.

The invention discloses a wind generating set fault prediction method and system based on edge computing, and the method comprises the steps: collecting the vibration, temperature, rotating speed and other parameters of a wind generating set in real time through a data collection module deployed by edge computing equipment, carrying out the preliminary screening and packaging through a built-in data processing unit, and synchronizing to a constructed digital twinborn model; establishing an edge calculation fault analysis model based on model data, identifying potential fault features, comparing a physical unit operation state with a digital twin model simulation state parameter by parameter, performing preliminary diagnosis in combination with the fault features, evaluating a unit health state according to a fault mechanism model, and outputting a fault prediction result and part information. The system is correspondingly provided with six units including a data acquisition interaction unit, a data processing unit and a model construction updating unit, and all the units work cooperatively, so that accurate prediction and health management of faults of the wind generating set are realized.

An integrated hydrogen-electric engine includes, an air compressor system; a hydrogen fuel source; a fuel cell; an elongated shaft connected to the air compressor system or a propulsor; and a motor assembly disposed in electrical communication with the fuel cell, wherein the air compressor system includes a plurality of electrically driven compressors configured to run in series or parallel.

Disclosed is an explainable method for monitoring a state of a generator of a wind turbine generator system on the basis of a spatio-temporal graph. The method includes: S1: acquiring data collected by a supervisory control and data acquisition (SCADA) system; S2: carrying out data understanding on the SCADA data, selecting features associated with the generator, and carrying out data preparation on the selected feature data, and obtaining valid data; S3: embedding the SCADA data, and forming a directed spatio-temporal graph data sequence; and S4: carrying out modeling of a normal behavior model of the generator on the constructed directed spatio-temporal graph data sequence, computing a full-graph-level residual and a node-level residual, computing a residual through an exponentially weighted moving average (EWMA) control chart method, carrying out full-graph-level state monitoring on the generator, forming a fault information transmission chain relation, and enhancing explainability and robustness of a monitoring result.

A method is provided for operating a powerplant. During this method, a hydrocarbon fuel is delivered to a turbine engine for combustion within a combustion chamber of the turbine engine during initial startup operation of the turbine engine. Ammonia is at least partially cracked into hydrogen gas and nitrogen gas. A non-hydrocarbon fuel is delivered to the turbine engine for combustion within the combustion chamber of the turbine engine during post-startup operation of the turbine engine. The non-hydrocarbon fuel is or otherwise includes the hydrogen gas or a combination of the hydrogen gas and the nitrogen gas.

The invention discloses a wind turbine generator state monitoring method driven by network fusion of a knowledge graph and a space-time diagram. The method comprises the following steps: S1, collecting time sequence SCADA data and wind power text data of a wind turbine generator; s2, constructing the wind power text data into a wind power operation and maintenance knowledge graph; s3, generating time sequence diagram data by querying a wind power operation and maintenance knowledge graph and combining the preprocessed SCADA data; s4, carrying out normal behavior modeling on the time sequence diagram data by utilizing the time-space diagram neural network model, predicting each node in the diagram data in the healthy operation time period of the unit in the normal behavior modeling process, and calculating the maximum absolute value of the difference between the predicted value and the actual value of each node as the maximum absolute value of the difference between the predicted value and the actual value; the maximum absolute error is used as a health threshold value of each node to perform state monitoring; in the state monitoring stage, the matching condition of the mapping information of each node in the graph structure in the monitoring result of the real-time data and the fault transmission chain is compared, the health state of the unit is judged, and the fault early warning time is determined. According to the invention, the accuracy and robustness of the monitoring result are enhanced.

The invention provides an anti-surge control method. The anti-surge control method comprises the following steps: acquiring historical data of a surge point; inputting the historical data of the surge points into the to-be-trained model to obtain an anti-surge model; based on the anti-surge model, determining an anti-surge line of the fan; the anti-surge line is generated by translating the abscissa of the surge line of the fan in the anti-surge coordinate system rightwards by a first preset unit and translating the ordinate downwards by the first preset unit; the real-time fan inlet flow and the real-time fan total energy head of the fan are obtained, and the real-time working condition point of the fan is determined; whether the real-time working condition point is located below an anti-surge line or not is judged, and if not, the opening degree of an anti-surge valve is adjusted to 100%; if yes, the anti-surge opening degree and the anti-surge valve opening time are determined based on the real-time working condition point, the anti-surge valve is opened according to the anti-surge valve opening time, the anti-surge valve is controlled to operate at the anti-surge opening degree, and the problem that the position area where the working condition point of the draught fan is located cannot be accurately and automatically adjusted at present is solved.

An apparatus for an aircraft powerplant includes an impeller rotor and a seal runner. The impeller rotor includes a plurality of fluid circuits. Each of the fluid circuits includes a first outlet passage, a second outlet passage and an inlet passage fluidly coupled to the first outlet passage and the second outlet passage in parallel. The seal runner includes a bore, an inner guide surface and an outer land surface. The seal runner extends circumferentially about the axis and radially between the inner guide surface and the outer land surface. The bore is fluidly coupled to the first outlet passage of each fluid circuit. The inner guide surface forms a radial outer peripheral boundary of the bore. The inner guide surface radially diverges away from the axis as the inner guide surface extends axially away from the impeller rotor and to a distal end of the seal runner.

An engine system for an aircraft includes a first turbofan engine and a second turbofan engine. The first turbofan engine includes a first low-pressure shaft, a first fan having a first fan shaft, and a counterclockwise gearbox assembly. The first fan shaft is drivingly coupled to the first low-pressure shaft through the counterclockwise gearbox assembly. The first low-pressure shaft rotates in a counterclockwise direction. The first fan shaft rotates in the counterclockwise direction such that the first fan rotates in the counterclockwise direction. The second turbofan engine includes a second low-pressure shaft, a second fan having a second fan shaft, and a clockwise gearbox assembly. The second fan shaft is drivingly coupled to the second low-pressure shaft through the clockwise gearbox assembly. The second low-pressure shaft rotates in the counterclockwise direction. The second fan shaft rotates in a clockwise direction such that the second fan rotates in the clockwise direction.

A double-liquid vibration-damping liquid-shaking tank for a wind turbine tower drum oriented to source network load storage coordination belongs to the technical field of wind turbine vibration-damping equipment, is a liquid-shaking damping structure externally arranged on a wind turbine main body, and comprises a wind direction plate and a liquid-shaking tank structure consisting of an annular liquid-shaking tank, a liquid partition plate, upper-layer liquid and lower-layer liquid, and the turntable fixing structure consists of a rotor and a rotor flange plate. The annular liquid shaking cabin is provided with a central through hole, is sleeved on the tower drum, is internally provided with a liquid partition plate, and is filled with two-phase liquid which has density difference and is immiscible with each other; the wind direction plate is arranged on the outer side of the annular liquid shaking cabin; the liquid shaking damping structure is fixed to the wind turbine tower fixing section through the rotor flange plate. Single shaking liquid is replaced by stably layered immiscible double liquid, the vibration reduction effect of the shaking liquid damping structure is improved, and the shaking liquid damping structure is accurately adaptive to all working conditions; and through linkage of the wind direction plate and the liquid partition plate, the vibration reduction effect of the shaking liquid damping structure is improved, the resonance effect is restrained, and the stability of the vibration reduction effect of the shaking liquid damping structure is enhanced.

An arrangement for fixing a housing of a wind turbine gearbox in a nacelle, including a housing-fixing means, a nacelle-fixing means, and at least two spring devices. The spring devices support the housing-fixing means against the nacelle-fixing means in opposite directions along a support axis. The spring devices are arranged on different sides of a plane extending parallel to an axis of rotation of an input shaft of the wind turbine gearbox.

The invention belongs to the technical field of wind power generation, and particularly relates to a fault diagnosis and early warning method and system for a wind power plant, and the method comprises the steps: collecting the state data of a plurality of physical fields through a plurality of types of sensor arrays disposed at key parts of a fan; performing preprocessing and feature extraction on the data to obtain high-dimensional feature data; driving the field-level digital twinborn model to perform real-time simulation based on the high-dimensional feature data, and determining an initial fault recognition result and severity by comparing a simulation predicted value with actual sensing data and combining with an unsupervised anomaly detection algorithm; a diagnosis result is calibrated through multi-modal high-dimensional feature data fusion; predicting the remaining useful life of the key component based on the fault severity and the evolution trend thereof, and generating a collaborative operation and maintenance decision by using a multi-objective optimization algorithm; and an operation and maintenance decision is automatically executed through a closed-loop feedback execution mechanism. According to the invention, the accuracy of fault diagnosis and early warning of the wind power plant is improved.

Disclosed herein is an integrated in-line emergency lube pump assembly for a planetary gearbox, including a main lube pump, a coaxial lube pump coaxially aligned with and coupled to the planetary gearbox, and an oil tank having a main section and an auxiliary section. There is no physical boundary between the main section and the auxiliary section of the oil tank. When the detected pressure in the oil supply line is equal to or exceeds a predetermined pressure threshold, the main lube pump operates to causes the main pump to pump oil from the main section of the oil tank to the planetary gearbox. Alternatively, when the detected pressure in the oil supply line is less than the predetermined pressure threshold the main lube pump ceases operation to cause the coaxial lube pump to draw oil from the auxiliary section of the oil tank to the planetary gearbox.

An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

A surface polishing method for micro inner flow channel, a micro inner flow channel part and a polishing medium. The diameter of the micro inner flow channel is less than or equal to 3 mm and length-diameter ratio is greater than or equal to 50:1. A polishing medium including a liquid phase and a solid phase, and viscosity of the liquid phase <1000 cP, the solid phase includes abrasive particles; a predetermined pressure being set on the polishing medium, making the polishing medium flow in the micro inner flow channel at a flow velocity more than 5 m / s, and flow rate of the polish polishing medium flowing into the micro inner flow channel at one end reaches a saturation flow rate allowed by the bore of the micro inner flow channel, making the hydraulic pressure inside the inner flow channel be in a pressure holding state.

A vibration absorber arrangement (1) is provided, in particular for tall slender structures, comprising a supporting structure (8), an absorber mass (2) which comprises a center of mass (3), and at least one wheel (4, 5) by means of which the absorber mass (2) is movable on a concavely curved rail arrangement (6), which is connected to the supporting structure (8), from a stable central position in two opposite directions, wherein a friction damper device (9) is provided. One wants to be able to adapt such a vibration absorber arrangement in a simple manner to different operating requirements. For this, it is provided that the friction damper device (9) is adjustable between a first state, in which it does not interact with the absorber mass (2) or only dampeningly, and a second state, in which it controlledly brings a movement of the absorber mass (2) to a standstill.

A cooled brush seal for use with a CMC component of a gas turbine engine having a hot side exposed to a hot gas path and an opposing side having a cavity for feeding a cooling flow to at least one film cooling hole. The cooled brush seal includes: an OD backing plate; an ID backing plate; a plurality of brush seal bristles sandwiched between the OD backing plate and the ID backing plate; a first hole extending through the OD backing plate, the brush seal bristles, and the ID backing plate; and a cover plate attached to an inner surface of the ID backing plate and including a second hole circumferentially offset from the first hole and forming a second passage into the cavity, wherein the ID backing plate and the cover plate form a circumferential cooling passage extending between the first hole and the second hole.

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.

The invention provides a supercritical carbon dioxide compressor performance evaluation method which can be applied to the technical field of compressors. The method comprises the following steps: acquiring total enthalpy and theoretical sound velocity from a physical property database according to total temperature and total pressure under the condition that the compressor operates in an inlet working condition; according to the total temperature, the total pressure, the total enthalpy, the theoretical sound velocity and a given axial Mach number, determining an iterative sound velocity from a physical property database; under the condition that a first error between the iteration sound velocity and the theoretical sound velocity is larger than a first preset threshold value, the theoretical sound velocity is updated to the iteration sound velocity, the steps are executed repeatedly till the first error is smaller than the first preset threshold value, and the target sound velocity is obtained; based on the target sound velocity, determining mass flow and rotating speed; fluid simulation is conducted on the compressor through the mass flow and the rotating speed, and performance parameters are obtained; and the performance of the compressor is evaluated through the incidence relations corresponding to the multiple sets of different inlet working condition parameters.

A fuel system for a hydrogen fuelled aircraft propulsion system comprises a fuel tank configured to store hydrogen fuel, a main fuel conduit configured to provide fuel to a combustor of a gas turbine engine, a fuel heater comprising a catalytic combustor configured to catalytically combust a portion of the hydrogen fuel prior to delivery to the combustor and a heat exchanger configured to exchange heat between exhaust gases from the fuel heater and hydrogen fuel in the fuel conduit.

A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine comprising: a turbomachine comprising, in serial flow order, a compressor section, a combustion section, and a turbine section, the turbomachine defining a working gas flow path and a fan duct flow path; a primary fan driven by the turbomachine, the primary fan defining a primary fan tip radius R1 and a primary fan hub radius R2; a secondary fan downstream of the primary fan and driven by the turbomachine, at least a portion of airflow from the primary fan being configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3 and a secondary fan hub radius R4, wherein the secondary fan is configured to provide, during operation, a fan duct airflow through the fan duct flow path to generate a fan duct thrust, wherein the fan duct thrust is equal to a %Fn of a total engine thrust during operation of the gas turbine engine at rated speed during standard day operating conditions 3S ; wherein a ratio of R1 to R3 is equal to wherein EFP is between 1.5 and 11, wherein RqR Prim.‑Fan is a ratio of R2 to R1, and wherein RqR Sec.‑Fan is a ratio of R4 to R3.

A heat exchanger for a turbomachine of an aircraft, the heat exchanger having a plurality of fins intended to be swept by a first fluid in a first direction, the fins extending in a second direction between a first panel and a second panel, being arranged in several rows in a third direction, and being arranged in a staggered manner, each row of fins being parallel and connected to one another. The heat exchanger can be annular, centered on the third direction and can have an inner cylindrical surface defining an inlet and an outer cylindrical surface defining an outlet, and the fins can have a length which decreases radially in the heat exchanger, in the first direction, between the inner cylindrical surface and the outer cylindrical surface.

A turbine engine rotor has a central shaft and a disk stack having disks encircling the shaft. A seal has in central axial cross-section: a rearwardly-open channel receiving a portion of one of the disks; a sleeve extending rearward from the channel and between the disk and the shaft; and a portion extending radially inward from the sleeve and having a forward surface restrained against forward movement relative to the shaft.

The embodiment of the invention provides a fan service life prediction method and system, a fan, a storage medium and a program product. The fan service life prediction method comprises the steps that the environment temperature of the fan is obtained; if the environment temperature of the fan meets the first condition, the mechanical factor service life and the environment factor service life of the fan are calculated; the first condition is that the environment temperature is smaller than or equal to first preset temperature or larger than or equal to second preset temperature, and the first preset temperature is smaller than the second preset temperature; and outputting the residual life of the fan after fusing the mechanical factor life and the environmental factor life. By fusing the mechanical factor life and the environmental factor life of the fan, the prediction precision of the fan life is improved, the cost does not need to be increased, and the residual life of the fan can be output in real time; and secondly, by monitoring the residual service life of the fan, the effects of good thermal management performance of the equipment and prolonging of the service life of the equipment can be achieved.

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.

A cooling flow arrangement for a ceramic matrix composite (CMC) component of a turbine engine, wherein the CMC component includes a hot side configured for exposure to a hot gas path of the turbine engine and an opposing cold side. At least one cavity is provided in the CMC component, the at least one cavity having an entrance disposed on the cold side that is configured for receiving a cooling flow. A seal is disposed adjacent the at least one cavity and the cold side of the CMC component and is configured to provide a seal between the CMC component and an upstream turbine component. At least one hole extends through the seal and is positioned to provide the cooling flow to the at least one cavity of the CMC component.

The invention discloses a fault diagnosis method, system, equipment and medium for a wind power gear box, and relates to the technical field of fault detection, and the method comprises the steps: collecting a vibration signal of the wind power gear box, and obtaining a time-frequency diagram of the vibration signal; capsule feature tensors in the time-frequency graph are obtained, a time-frequency two-dimensional network is formed in space, and corresponding query tensors are extracted from a time axis and a frequency axis of the time-frequency two-dimensional network by adopting different convolution kernels; dot product matching is carried out on the corresponding query tensors and a preset shared key value pair, attention distribution of each query tensor is obtained, and aggregation output in the directions of the time axis and the frequency axis is fused through the attention distribution; and performing class activation mapping on the aggregated output, determining a fault category of the wind power gear box, generating a class activation graph focused on the key time-frequency region through the fault category, and displaying a discrimination basis. The method can focus on a key time-frequency region with clear physical significance, and obviously improves the discrimination transparency and engineering credibility of the model.

A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by:VGVG⁢B·VGis a gutter volume of the gutter and VGB is a gearbox volume.