9324results about "Engine fuctions" patented technology

An online testing and diagnosis method for vibration characteristics of blades of wind turbine is disclosed. Steps of testing and diagnosing blade vibration comprises: S1: installing vibration sensors at key positions of a blade, designing an adaptive data acquisition strategy, and automatically adjusting a sampling rate according to a vibration amplitude and environmental changes monitored in a real time; S2: extracting key features reflecting health status of the blade from massive data, and evaluating an impact of wind speed, temperature, and environmental factors on vibration characteristics; S3: designing a customized deep learning model for damages of the blade of a wind turbine, extracting a time sequence data and a vibration signal, identifying a damage among different types of damages and evaluating a damage degree; and S4: automatically adjusting a warning threshold based on a real-time data stream and a historical trend, and drafting a preventive maintenance plan.

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the retractable cable module is disposed in the housing and includes a cable retractable relative to the housing to be withdrawn into the housing or extended out of the housing, and the cable is configured to connect to an external electronic device, and supply power to the external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.

The invention relates to the technical field of wind turbine generator data analysis, and discloses an offshore wind turbine generator operation data analysis and prediction system. The system comprises a marine environment data integration module for collecting data to generate a multi-source time-space synchronization data set; the multi-modal feature fusion module is used for extracting cross-modal correlation features to generate a high-dimensional fusion feature tensor; the dynamic fault prediction module is used for constructing a two-way gating circulation network model to predict the degradation probability and the residual life of key components of the equipment; and the self-adaptive optimization control module is used for constructing a multi-target dynamic programming model to optimize a fan operation strategy. In addition, the system is further provided with a feedback correction module for correcting prediction model parameters, and a virtual sensor module based on a physical information neural network is used for monitoring tower stress and diagnosing sensor faults. According to the system, comprehensive monitoring, accurate fault prediction and optimal control of the offshore wind turbine generator are realized, the operation efficiency, reliability and safety of the wind turbine generator are effectively improved, and the operation and maintenance cost is reduced.

The invention discloses a matrix yaw system of a wind power plant. The matrix yaw system comprises a data acquisition module, a wind plant modeling module, a parameter extraction module and a yaw control module. The data acquisition module acquires a wind field original data set containing three-dimensional space coordinates and timestamps by using a multi-source sensor; the wind field modeling module calculates correlation between points by combining a covariance function through a Gaussian process regression algorithm, and constructs a three-dimensional dynamic wind field model; the parameter extraction module is used for extracting wind regime parameter vectors in the model by adopting a nearest neighbor interpolation algorithm on the basis of actual space coordinates of a fan; and the yaw control module utilizes a depth deterministic strategy gradient reinforcement learning model to generate a yaw angle adjustment instruction in combination with the wind regime parameter vector, the current yaw state of the fan and a preset maximum cumulative reward function. Through multi-module cooperation and intelligent algorithm optimization, accurate matching of wind field dynamic modeling and yaw control is achieved, and the energy efficiency and operation stability of the wind generating set are improved.

Systems and methods for providing lubrication to a gas turbine engine are described. An example gas turbine engine includes a plurality of bearings disposed along an axial length of a rotatable shaft to provide rotational support between a static structure and at least one of a compressor and a turbine of the gas turbine engine. The gas turbine engine further includes a fuel system operable to deliver a mixture of fuel and lubricant sequentially to at least one of the plurality of bearings and the combustor so that during operation of the gas turbine engine, at least the lubricant within the mixture is in a liquid phase prior to being received by the at least one of the plurality of bearings, and in a vapor phase once the lubricant is delivered to the at least one of the plurality of bearings.

A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT / (AHPCExit2×1000).

An aircraft engine, has: a turbine; a scroll case having an inlet connected to a source of combustion gases and an outlet connected to the turbine, and a conduit extending from the inlet to the outlet; a bearing housing including a support flange; an exhaust case downstream of the turbine; and a turbine support case secured to the bearing housing and to the exhaust case, the turbine support case having spokes extending along a direction having an axial component, the spokes extending through the scroll case and radially supported by the bearing housing, a spoke having a distal end secured to the support flange via: one or more fasteners, and a retaining member at the distal end, the retaining member defining an abutment face facing an axial direction and circumferentially overlapping the support flange, a portion of the support flange located axially between the distal end and the abutment face.

A gas turbine engine is provided, having: a bifurcation; and a turbomachine further including a cooled cooling air (CCA) system, the CCA system having: a cold side bleed assembly defining an inlet positioned to be in fluid communication with an airflow over the bifurcation; a CCA heat exchanger in thermal communication with the cold side bleed assembly downstream of the inlet of the cold side bleed assembly; and a hot side bleed assembly defining an inlet in fluid communication with a working gas flowpath through a compressor section, at a compressor discharge cavity, or both, the hot side bleed assembly in thermal communication with the CCA heat exchanger to cool an airflow through the hot side bleed assembly, the hot side bleed assembly further in thermal communication with a hot component of the turbomachine to cool the hot component of the turbomachine.

A thermal management system defines a thermal management system flowpath to provide a flow of a fluid to an electric machine and a power electronics assembly electrically connected to the electric machine. The thermal management system includes a first heat exchanger thermally connected to the thermal management system flowpath and to the electric machine, and a second heat exchanger thermally connected to the thermal management system flowpath downstream of the first heat exchanger. The second heat exchanger is thermally connected to the power electronics assembly.

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.

A gas turbine engine includes a turbomachine comprising compressor, combustion, and turbine sections. The gas turbine engine defines a maximum exhaust gas temperature, a maximum drive turbine shaft torque, and a corrected specific power. The gas turbine engine includes a controller configured to autonomously regulate performance of the gas turbine engine in response to at least one of: a thrust demand, an energy efficiency target, or a flight profile condition.

A wave energy power generation device includes a plurality of up-down moving mechanisms configured to move up and down along a spiral rod under the action of waves, a mass block arranged at a lower part of the power generation device; a buoyancy barrel arranged in the middle of the power generation device, a guide rail arranged on one side of the up-down moving mechanism, and a spiral rod. Through the interaction of the up-down moving mechanism and the spiral rod, the up-down movement of waves can be converted into rotational kinetic energy, a scroll spring is used for storing energy, then the rotating speed is stabilized through an escapement mechanism, a power generation assembly accelerates energy output, and finally a generator is driven to generate power.

A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows:(TOUT / √{square root over (ADTExit)})2*EGT / AHPCExit*10−11;wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

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.

An air / oil heat exchanger arranged in a vein. The exchanger includes internal parietal corridors and / or external parietal corridors and central corridors, the radial height of the internal and / or external parietal corridors increasing from the inlet of the exchanger to its outlet.

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 system for supplying power to a portable battery pack including a battery enclosed by a wearable and replaceable pouch or skin using at least one solar panel is disclosed, wherein the pouch or skin can be provided in different colors and / or patterns. Further, the pouch or skin can be MOLLE-compatible. The battery comprises a battery element housed between a battery cover and a back plate, wherein the battery element, battery cover, and back plate have a slight curvature or contour. Further, the battery comprises flexible leads.

A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.

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 present application relates to the field of metal material manufacturing, and in particular to a GH4151 alloy bar and a preparation method therefor and a use thereof. The method comprises the following steps: (1) carrying out homogenization heat treatment on a GH4151 alloy cast ingot to obtain a heat treated bar; (2) forging the heat treated bar to obtain a forged bar; (3) carrying out hot rolling treatment on the forged bar to obtain a hot rolled bar; (4) carrying out solution treatment on the hot rolled bar to obtain a solid solution bar; (5) carrying out cold drawing treatment on the solid solution bar to obtain a cold drawn bar; and (6) carrying out aging treatment on the cold drawn bar to obtain a GH4151 alloy bar. According to the GH4151 alloy bar prepared in the present application, grains can be effectively refined, the surface dimensional precision is improved, and the tensile strength of the prepared GH4151 alloy bar is improved, so that the GH4151 alloy bar has excellent mechanical properties.

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.

A lubrication system for a turbine engine. The turbine engine includes a propulsor and one or more rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a strain energy storage system. The sump stores lubricant therein. The primary lubrication system supplies the lubricant from the sump to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump including an auxiliary pump shaft. The strain energy storage system includes a spring drivingly coupled to the auxiliary pump shaft. The spring stores strain energy during normal operation of the turbine engine and releases the strain energy when the propulsor is windmilling to rotate the auxiliary pump shaft to power the auxiliary pump such that the auxiliary pump pumps the lubricant from the sump to the one or more rotating components.

A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.

The present invention discloses a surge-reducing and low-noise wind turbine blade with adjustable blade angle, which relates to the technical field of wind turbine blades. It comprises a hub body, a connecting shaft is fixedly mounted on the hub body, the interior of the hub body is divided into a power supply chamber, a mounting chamber and a drive chamber, an adjustment component is provided inside the drive chamber, a wind turbine blade is mounted on the adjustment component, a blade tail is fixedly mounted on the tail of the wind turbine blade, the side edge of the wind turbine blade is set as a notch, a linkage component is provided inside the mounting chamber, and a guide component is provided on the linkage component. The invention concentrates the airflow by synchronously rotating the guide vanes with the wind turbine blades. This design can effectively improve the flow characteristics of the airflow on the blade surface, increase lift, and reduce noise. Combining the guide vanes with the blade angle adjustment mechanism enhances its adaptability and effectively improves the use effect of the wind turbine blades.

A tail cone ventilation system including a tail cone case defining a tail cone interior and a tail cone exterior, the tail cone having a forward portion and an aft portion separated axially along a tail cone axis; a distribution manifold located within the tail cone interior proximate the forward portion, wherein the distribution manifold comprises nozzles arranged radially around the axis, the nozzles configured to direct a cooling air over at least one electronic component within the tail cone interior and along an inner surface of the tail cone case; an air inlet fluidly coupled with the distribution manifold through ducting, the air inlet located externally from the tail cone interior; and a tail cone discharge located proximate the tail cone aft portion, the tail cone discharge being fluidly coupled with the distribution manifold.

A system for an aircraft includes a fan rotor, an engine core, a fan case, a core case, a bifurcation, an inner electrical system, an outer electrical system and multiple electrical lines electrically coupling the inner electrical system to the outer electrical system. The engine core is configured to drive rotation of the fan rotor about an axis. The fan case houses the fan rotor. The core case houses the engine core. The bifurcation radially crosses a bypass flowpath. The bypass flowpath is downstream of the fan rotor and located radially between the fan case and the core case. The inner electrical system is arranged with the engine core. The outer electrical system is mounted to the fan case. The electrical lines extend between and electrically couple the inner electrical system to the outer electrical system. The electrical lines run in parallel along one another radially through the bifurcation.