2370results 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.

The invention relates to the field of mine ventilation, in particular to an intelligent adjusting method and system for mine ventilation. The method comprises the following steps: constructing a dynamic topology model taking a roadway as an edge and taking a fan and an air door as nodes based on a mine CAD drawing; acquiring the actual wind pressure and the actual wind volume of each roadway branch in real time, performing inversion to obtain the current wind resistance, and updating the wind resistance attribute of the edge in the dynamic topology model by using the current wind resistance; calculating the optimal air volume of the roadway branch by using the updated dynamic topology model; based on the optimal air volume, target regulation and control parameters of the draught fan and the air door are obtained through solving by means of a particle swarm algorithm; and according to the target regulation and control parameters, the fan and the air door are adjusted through a fuzzy PID algorithm. The problem that in the prior art, mine ventilation adjustment is not intelligent and safe enough is solved, the theoretical optimal air volume is obtained through deep analysis of the mine, then ventilation adjustment is conducted step by step, and the scientificity and efficiency of ventilation adjustment are improved.

The invention discloses a fan control method and device, and relates to the technical field of heat dissipation, and the method comprises the steps: partitioning and numbering a hard disk region, enabling each hard disk to correspond to a fan according to a corresponding number, obtaining the obtaining temperature of a hard disk backboard and hard disk information through a master control node or a slave control node, and dynamically calculating fan control parameters, the heat dissipation efficiency of the server is improved, and the problems that in the related technology, the rotating speed of the fan is controlled only depending on the single temperature sensor parameter and the fan parameter, server fan redundancy control cannot be achieved when the node breaks down, and the reliability of the server is poor are solved. The technical problem that the heat dissipation efficiency and flexibility are poor in the prior art is solved, and the technical effect that the heat dissipation efficiency of the double-control high-density server is effectively improved by dynamically adjusting the rotating speed of the fan according to the working state, the read-write rate and the real-time temperature of the hard disk and achieving partition control is achieved.

An aircraft gas turbine engine includes a combustor, with a combustion chamber and fuel spray nozzles to inject fuel into the chamber. The nozzles include first and second subsets. The first subset of nozzles is supplied with fuel at a greater rate than each of the second subset. A ratio of nozzles in the first subset to the second subset is 1:3 to 1:6. A lean cruise nvPM emissions index ratio isEIcruise⁡(lean),SAFEIcruise⁡(lean),FF,where EIcruise(lean),SAF isEImaxTO,SAF+EIclimb,SAF2and EIcruise(lean),FF isEImaxTO,FF+EIclimb,FF2.EImaxTO,SAF is nvPM emissions index operating at 100% available thrust and EIclimb,SAF is the nvPM emissions index operating at 85% available thrust if fuel includes sustainable aviation fuel. EImaxTO,FF is the nvPM emissions index operating at 100% available thrust and EIclimb,FF is the nvPM emissions index at 85% available thrust if fuel is a fossil-based hydrocarbon. The lean cruise nvPM emissions index ratio is less than 1.

A gas turbine engine for an aircraft is disclosed. The gas turbine engine comprises: a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. A thrust nvPM emissions index ratio is defined as:EImaxTO / FmaxTOEIidle / Fidlewhere: EIidle is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 7% available thrust for given operating conditions; EImaxTO is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 100% available thrust for the given operating conditions; FmaxTO is the thrust of the gas turbine engine at around 100% available thrust in kN for the given operating conditions; and Fidle is the thrust of the gas turbine engine at around 7% available thrust in kN for the given operating conditions. The thrust nvPM emissions index ratio is greater than 0.001. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the plurality of fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

A gas turbine engine for an aircraft is disclosed. The gas turbine engine comprises: a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:3 to 1:6. A MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles. Also disclosed are methods of operating the gas turbine engine.

A gas turbine engine includes a combustor with a combustion chamber and fuel spray nozzles to inject fuel into the combustion chamber. The nozzles include a first and second subset. Each of the nozzles of the first subset is supplied with fuel at a greater rate than each of the second subset. A ratio of nozzles in the first subset to nozzles in the second subset from 1:3 to 1:6. A fuel-flow nvPM emissions index ratio isEIidle×Wf,idleRImaxTO×Wf,maxTO.EIidle and EImaxTO are the system loss corrected nvPM emissions index in mg / kg operating at around 7% and 100% available thrust for the given operating conditions, respectively. Wf,idle and Wf,maxTO are the rate of fuel flow to the fuel spray nozzles in kg / s at around 7% and 100% available thrust for the given operating conditions, respectively. The fuel-flow nvPM emissions index ratio of the gas turbine engine is less than 0.3.

A gas turbine engine includes: a rich burn, quick quench, lean burn combustor having a number of fuel spray nozzles in the range 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An nvPM emissions index ratio is defined as:EIidle×Wf,idleEImaxTO×Wf,maxTOwhere: EIidle and EImaxTO are respectively the nvPM emissions index in mg / kg of gas turbine engine if operating at around 7% or 100% available thrust for given operating conditions; Wf,idle and Wf,maxTO are respectively the rate of fuel flow to fuel spray nozzles in kg / s at around 7% or 100% available thrust for given operating conditions. The fuel-flow nvPM emissions index ratio is less than 0.08. The gas turbine engine is configured to provide fuel including sustainable aviation fuel to fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

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 for an aircraft is disclosed. The gas turbine engine comprises: a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:3 to 1:6. A MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF is the nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles. Also disclosed are methods of operating the gas turbine engine.

A gas turbine engine includes: a rich burn, quick quench, lean burn combustor having a number of fuel spray nozzles in range of 14-22 or a number of fuel spray nozzles per unit engine core size in range 2 to 6. An MTO nvPM emissions index ratio is:EImaxTO,SAFEImaxTO,FF×Wf,maxTOwhere: EImaxTO,SAF and EImaxTO,FF are respectively the nvPM emissions index in mg / kg when operating around 100% available thrust for given operating conditions if fuel provided to fuel spray nozzles includes either sustainable aviation fuel (SAF) or fossil-based hydrocarbon fuel; Wf,maxTO is mass flow rate of fuel provided to fuel spray nozzles in kg / s when gas turbine engine is operating at around 100% available thrust for given operating conditions. MTO nvPM emissions index is less than 2. The gas turbine engine is configured to provide fuel including SAF to fuel spray nozzles. Also disclosed is method of operating gas turbine engine.

The invention discloses a control method and device of a wind driven generator, a terminal and a storage medium, particularly relates to the technical field of operation control of the wind driven generator, and is used for solving the problem that a supporting structure bears violent asymmetric loads due to dynamic response differences of wind and wave load directions in a marine environment in an existing control method. Wind direction and wave direction data are synchronously obtained in real time, the wind direction change rate is calculated, supporting structure vibration signals are analyzed to recognize wave excitation dominant frequency components, and when it is detected that wave excitation energy suddenly changes and the wind direction change rate exceeds the limit, the wind wave direction difference is analyzed; meanwhile, a wave spectrum energy concentration frequency band is determined by analyzing the tower top movement track, the load asymmetry risk level is evaluated by combining the direction difference and the wave energy concentration frequency band, finally, the yaw speed and the variable pitch speed are adjusted in a self-adaptive mode according to the risk level, and accurate recognition and early warning of the wind wave load direction mismatching working condition are achieved. And the operation reliability of the wind driven generator in extreme weather is improved.

The invention belongs to the technical field of intelligent control, and provides a double-fan parallel operation control system and method based on dynamic flow balance, and the system comprises a flow guide assembly, an electric control valve, a flow sensor and a control assembly; the flow sensors are used for collecting air flow data at the inlets and outlets of the corresponding fan branches and sending the air flow data to the control assembly; the control assembly is used for inputting the air flow data into the three-dimensional dynamic fluid mechanics model to obtain a flow deviation value between the current air flow and the target air flow, inputting the flow deviation value into the control decision model to obtain a control instruction, and issuing the control instruction to the flow guide assembly and / or the electric adjusting valve. And the flow guide direction of the flow guide assembly and / or the opening degree of the electric control valve are / is controlled. According to the scheme, the three-dimensional dynamic fluid mechanics model and the control decision model can be combined, the accurate control instruction is obtained, and the accuracy, reliability and convenience of the double-fan parallel operation control link are improved.

A system and method for controlling a cleaning system for motor vehicle components, wherein the cleaning system includes a fluid conveying device, a pressure sensor for determining a pressure generated by the fluid conveying device, a fluid distribution device with at least one input port fluid-connected to the fluid conveying device and with at least two output ports fluid-connected to the input port, wherein each output port is adjustable between an open position and a closed position, at least two cleaning devices, each fluid-connected to a respective output connection via a fluid line, and a control device, which is data-coupled to the fluid conveying device, the pressure sensor and the fluid distribution device for transmitting and / or receiving signals, the method achieving simplified control of the cleaning system and a reduction in the susceptibility of the cleaning system to errors.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. A first idle-MTO nvPM emissions index ratio is defined as:EIidle / EImaxTO where: EIidle is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 7% available thrust for given operating conditions; and EImaxTO is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 100% available thrust for the given operating conditions. The first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 0.8. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the fuel spray nozzles. A method of operating the gas turbine engine is also disclosed.

The invention provides a heavy duty gas turbine control system which comprises a signal conditioning module and a plurality of parameter control modules, and a rotating speed control module, a load control module, a temperature limit control module and an acceleration control module in the parameter control modules are all used for achieving closed-loop control according to the deviation between a set value and a corresponding observation value; the starting control module is used for acquiring a starting fuel quantity instruction through a designed control strategy; the IGV and VGVs control module obtains an IGV and VGVs angle instruction according to the turbine inlet temperature set value, the turbine outlet temperature set value and the deviation maximum value of the corresponding observation value; the fuel quantity control module obtains a total fuel quantity instruction based on a full working condition range fuel quantity control strategy; the fuel gas distribution control module is used for obtaining an opening degree instruction of each fuel valve according to the total fuel quantity instruction; the adaptability, the reliability and the usability of the control system in application scenes such as autonomous design and technical improvement are improved.

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 system including a engine having a low spool and a high spool, a first hybrid electric motor connected to the low spool and a second hybrid electric motor connected to the high spool. An auto-throttle controls an amount of power provided to the engine responsive to at least one aircraft parameter. A power splitting algorithm implemented between the auto-throttle and at least one of the first and second hybrid electric motors determines a power split dividing the total engine power into the power produced by burning fuel and electrical power provided to the at least one of the first and second hybrid electric motors responsive to control signals from the auto-throttle.

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:EIidleEImaxTO,where: Elidle is the nvPM emissions index in mg / kg operating at around 7% available thrust; ElmaxTO 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 tunnel oxygen supply control method based on multi-parameter coordination, and relates to the technical field of tunnel construction, and the method comprises the steps: constructing a multi-source environment monitoring data set, training a target ventilation quantity prediction model fused with a high-altitude correction coefficient based on the data set, and outputting an initial target ventilation quantity and an oxygen supply parameter; generating a pre-regulation instruction based on the initial target ventilation quantity and the oxygen supply parameters, simulating an instruction execution process through a digital twin virtual simulation model, and outputting oxygen supply evaluation parameters of oxygen content distribution, wind pressure loss and energy consumption of each block of the tunnel; constructing a tunnel oxygen supply evaluation model, and comparing oxygen supply evaluation parameters obtained by simulation with a safety threshold; and executing the formal adjustment instruction. Through multi-dimensional sensing treatment, high-altitude self-adaptive calculation, digital twinborn simulation verification, multi-scene parameter optimization, multi-device collaborative linkage and model dynamic evolution technologies, the breakthrough of tunnel oxygen supply from static experience control to dynamic precise intelligent regulation is realized.

A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a geared architecture including a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the geared architecture.

The invention provides for controlling a wind turbine comprising pitch-adjustable rotor blades. The invention involves determining, based on detected wind conditions, wind turbine control parameters for controlling the wind turbine in accordance with a defined wind turbine control strategy, where the control parameters include a reference pitch angle for the rotor blades. The invention involves obtaining bearing control parameters each indicative of a parameter for controlling pitch bearings of the wind turbine that is for adjusting pitch of the rotor blades. The invention involves determining whether a defined set of operational parameters of the wind turbine, including the bearing control parameters, in combination correspond to a combination of operational parameters defined to be indicative of a level of wear above a threshold wear level. The pitch bearings are then controlled based on the reference pitch angle and on the threshold determination.

A gas turbine engine for aircraft includes a combustor with a combustion chamber and fuel spray nozzles to inject fuel into the combustion chamber. The fuel spray nozzles include a first subset and a second subset of nozzles. Each of the first subset is supplied with fuel at a greater rate than each of the second subset. A ratio of the first subset to the second subset is 1:2 to 1:5. A MTO nvPM emissions index ratio isEImaxTO,SAFEImaxTO,FF.EImaxTO,SAF is nvPM emissions index in mg / kg of the engine when operating at around 100% available thrust if fuel provided to the fuel spray nozzles includes sustainable aviation fuel. EImaxTO,FF IS nvPM emissions index in mg / kg of the engine when operating at around 100% available thrust if fuel provided to the fuel spray nozzles is fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio is less than 1.

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.

A pressure regulating device includes an on-board storage tank, a mixing chamber, first and second lines, a recirculation line, a pressure sensor and a controller. The storage tank stores and supplies cryogenic fuel to a combustion chamber and includes a booster pump. The first line supplies cryogenic fuel in the liquid state and includes a pressurizing pump and a first regulation valve. The second line supplies cryogenic fuel in the gaseous state and includes a compressor and a first control valve. The recirculation line includes a second regulation valve and with a first heat exchanger. The pressure sensor detects the pressure inside the storage tank. The controller receives the pressure and controls the first and second regulation valves, the first control valve, the pressurizing pump, the booster pump and the compressor, as a function of a value of a setpoint pressure inside the storage tank.

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 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.

Systems and generating power in an organic Rankine cycle (ORC) operation to supply electrical power. In embodiments, an inlet temperature of a flow of gas from a source to an ORC unit may be determined. The source may connect to a main pipeline. The main pipeline may connect to a supply pipeline. The supply pipeline may connect to the ORC unit thereby to allow gas to flow from the source to the ORC unit. Heat from the flow of gas may cause the ORC unit to generate electrical power. The outlet temperature of the flow of the gas from the ORC unit to a return pipe may be determined. A flow of working fluid may be adjusted to a percentage sufficient to maintain temperature of the flow of compressed gas within the selected operating temperature range.

Provided are a multi-blade wind generator. The multi-blade wind generator relates to the technical field of wind power generation, and includes a bottom plate, where a bracket is installed at an upper end of the bottom plate, a working housing is installed at an upper end of the bracket, and a generator is arranged in a first working cavity inside the working housing, and a motor shaft of the generator is connected with a first rotating shaft through a speed-increasing and heat-dissipating mechanism; the first rotating shaft penetrates a front end of the working housing and is fixedly connected with a rotating drum, and the working housing is rotatably connected with the rotating drum, and a cavity is arranged in the rotating drum, and a motor is fixedly arranged in the cavity in the rotating drum, and the motor is fixedly connected with a first bevel gear.

The invention discloses a pumped storage power station governor parameter optimization method and system, and relates to the technical field of pumped storage power station control, and the method comprises the steps: constructing a multi-dimensional evaluation system, and defining seven indexes of a unit safety class, a rotating speed response class and a power response class, which are used for comprehensively evaluating the power regulation performance; based on historical operation data of the power station, the occurrence probability of each initial working condition and load change is counted, a weighting factor matrix is generated, and weight contributions of high-frequency and extreme working conditions to an optimization target are quantified; and parameter optimization and decision making: simulating the performance of different speed regulator parameter combinations (KP = 0.1-1.9, KI = 0.1-0.7) under 30 typical working conditions by adopting a water-electro-mechanical coupling model, carrying out normalization and comprehensive scoring on simulation results based on a TOPSIS algorithm, and screening a parameter scheme with the highest total score. According to the method, the problems of single index and insufficient working condition adaptability in parameter selection of a traditional speed regulator can be solved, and collaborative improvement of unit safety and regulation stability is realized through multi-dimensional evaluation and probability-driven optimization.