3793results 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.

An engine for aeromechanical instability abatement includes a sensor configured to capture data from rotating blades of the engine system, a airflow effector device, and an engine controller. The engine controller is configured to control the airflow effector device according to a nominal schedule, detect, based on a signal from the sensor indicating a vibration amplitude of the rotating blades within a frequency band, an incipient instability condition, in response to the incipient instability condition being present, determine a modified control parameter for at least one of the airflow effector device, and control the airflow effector device according to the modified control parameter, deviating from the nominal schedule.

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.

A method for fueling an aircraft comprises (a) predicting a sequence of fuel-burn quantities over a planned flight based on at least one sequence of multivariate flight data recorded during a prior flight and on a hidden state of a trained machine. For each of a pre-selected series of prior flights, a corresponding sequence of multivariate flight data recorded during the prior flight is processed in a trainable machine to develop the hidden state, which minimizes an overall residual for replicating the fuel-burn quantities in each corresponding sequence. The method further comprises (b) summing the fuel-burn quantities over the planned flight to obtain a fueling estimate; and (c) fueling the aircraft based in part on the fueling estimate.

The invention discloses a water pump station operation adjusting device and method, and relates to the technical field of pump station operation adjusting, a first prediction result is output through operation data of a water pump station, and whether the first prediction result needs to be corrected or not is judged based on environment characteristics, equipment state data and water quality data to obtain inlet and outlet valve adjusting parameters; constructing a water pump station digital model, receiving a simulation regulation feedback result, and optimizing inlet and outlet valve regulation parameters by utilizing the simulation regulation feedback result; an inlet and outlet valve adjusting stability threshold value is obtained, relation feedback verification is conducted through the inlet and outlet valve adjusting stability threshold value, and whether a protection mechanism is triggered or not is judged through the simulation adjusting feedback result and the relation feedback verification result; and when the protection mechanism is triggered, the dynamic current stabilizer is started, and the current stabilization parameters of the dynamic current stabilizer are adjusted. Intelligent accurate control, active protection and energy efficiency optimization are realized, the system stability is improved, and the operation and maintenance cost is reduced.

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.

The invention relates to a wind power plant yaw control method based on a wind process. The method comprises the following steps: 1, establishing a wind power plant simulation model; 2, acquiring operation state data of the wind power plant as an initial state of the wind power plant simulation model; 3, acquiring a wind speed fluctuation sequence and a wind direction fluctuation sequence of the wind power plant as the state of the wind power plant yaw control model; 4, performing off-line learning to obtain optimal yaw angle set values under different wind regime sequences; enabling the wind power plant yaw control model to observe the environment and guide a wind turbine generator to act, and completing online learning; the wind power plant yaw control model is established, the optimal yaw angle of each wind turbine generator in the wind power plant is obtained through the wind speed sequence and the wind direction sequence, and the total generated power of the wind power plant is greatly improved; and the timeliness requirement of solving the wind power plant yaw control model in practical engineering is met.

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.

The invention relates to the technical field of fan blade deicing, and discloses an intelligent temperature control type fan blade electric heating deicing control system and method, and the system comprises a meteorological sensing module which is used for collecting the environment temperature, humidity, wind speed and rainfall type; the blade state monitoring module is used for acquiring blade surface temperature distribution and ice layer thickness data; the dynamic decision-making module is used for generating a partition heating instruction based on the data of the weather sensing module and the blade state monitoring module; the temperature control execution module is used for converting the instruction into a gradient signal; the heating array module is used for executing electric heating deicing operation in the blade surface subareas; and the energy coordination module is used for dynamically constraining the total power of the system. The meteorological sensing module and the blade state monitoring module are integrated through the system, real-time collection and fusion of multi-source data of blade surrounding environment parameters and the thickness of an ice layer are achieved through the design, comprehensiveness and accuracy of icing monitoring are improved, a reliable basis is provided for dynamic decision making, and therefore the response capacity and early warning precision of the system to icing risks are improved.

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 relates to the technical field of variable-frequency centrifugal fans, and discloses an energy-saving optimization control method and system for a variable-frequency centrifugal fan, and the method comprises the steps: collecting a real-time parameter data set of the variable-frequency centrifugal fan through a sensor network, and carrying out the digital filtering and feature extraction, and obtaining a target feature vector; inputting the target feature vector into a trained VentNet dual-network deep neural network for prediction calculation to obtain an optimal rotating speed prediction value and an energy consumption prediction value under the current load condition; calculating control error data and inputting the control error data into a hyperbolic law of arrival controller for processing to obtain a frequency adjustment instruction of the frequency converter; the frequency adjusting instruction is sent to the frequency converter, the actual rotating speed of the variable-frequency centrifugal fan is adjusted, and the variable-frequency centrifugal fan operates in the optimal energy-saving state, real-time energy-saving optimization control over the variable-frequency centrifugal fan under different load conditions is achieved, the energy consumption amplitude is reduced, and meanwhile the stability and reliability of operation of the fan are guaranteed.

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 system for compensating for a relative motion between a probe and an apparatus. The system includes a probe assembly, a sensor, and a computer. The probe assembly includes an actuator pack positioned exterior to the apparatus and a probe insertable into the apparatus. The probe includes a first end coupled to the actuator pack, a second end, and an elongated body extending therebetween. The sensor senses data indicative of a relative motion between the apparatus and the probe assembly. The computer is operably coupled with the sensor and the probe assembly to move the probe of the probe assembly in response to the sensor sensing the data indicative of the relative motion between the apparatus and the probe assembly.

The invention discloses a variable-pitch coordinated optimization control method and system for a wind turbine generator, and relates to the technical field of wind turbine generator control, and the variable-pitch coordinated optimization control method comprises the following steps: obtaining operation characteristic data of the wind turbine generator; analyzing the obtained operation characteristic data of the wind turbine generator by using a factor analysis algorithm, and identifying key factors influencing the variable pitch performance of the wind turbine generator; predicting the variable pitch of the wind turbine generator at the future moment by using the variable pitch coordination control model to obtain a blade angle change trend; and dynamically adjusting the variable pitch angle of each blade based on the obtained blade angle change trend in combination with the real-time operation state of the wind turbine generator, and optimizing a variable pitch coordination control strategy. The variable-pitch coordinated control model is utilized to predict the variation trend of the blade angle, a scientific basis can be provided for variable-pitch angle adjustment at the future moment, the hysteresis of variable-pitch control is effectively reduced, and the control is more prospective and real-time adaptive.

This invention relates to a method for controlling a motor assembly (100). This motor assembly (100) comprises at least a first electric machine (300) and a gas turbine engine (200). The gas turbine engine (200) comprises a low-pressure shaft (210) and a high-pressure shaft (220). The electric machine (300) is coupled to the low-pressure shaft (210), and the control method comprises a step in which a take-off of mechanical work is ordered from the first electric machine (300) to brake a rotation of the low-pressure shaft (210) in response to an activation of a thrust reverser (281) of the gas turbine engine (200) and / or a disturbance of the air flow in a transverse plane at an air intake of the gas turbine engine (200). The invention also relates to a control unit (500) suitable for carrying out this method, a motor assembly (100) incorporating this control unit (100), the electric machine (300) and the gas turbine engine (200), and a computer program to carry out this method.

The invention provides a pumping method based on multi-agent reinforcement learning control, and belongs to the technical field of deep reinforcement learning. S2, feature extraction and fusion; s3, time sequence modeling; s4, generating an action; s5, carrying out environment interaction; s6, virtual experience generation; s7, experience pool management; s8, performing network training; and S9, performing closed-loop control. Discrete and continuous actions are controlled through the DQN and the DDPG respectively, collaborative optimization of start-stop and frequency adjustment of the water pump is achieved by combining the Critic network, and the problem that a traditional single agent cannot process a mixed action space is solved.

The invention relates to the technical field of power dispatching, and discloses a water-wind-light complementary dispatching optimization method and system, and the method comprises the steps: obtaining meteorological data and reservoir water level data, and carrying out the alignment segmentation of the data, and forming a corresponding data sequence; a multi-time-scale coupling prediction model is constructed, and the aligned data sequences are predicted on the corresponding output; establishing a hybrid nonlinear programming objective function, configuring constraint conditions, and minimizing the comprehensive cost of hydropower, wind power and photoelectricity; and setting a plurality of hierarchies according to the predicted duration, and solving the hybrid nonlinear programming objective function. According to the invention, a multi-meteorological-element-multi-energy-form coupling prediction model is established, a coordinated scheduling optimization architecture suitable for complex weather is further constructed, and water-wind-light complementary scheduling optimization is realized in combination with a dynamic optimization weight mechanism based on a meteorological risk coefficient. The method is suitable for peak regulation scheduling of a multi-energy complementary micro-grid and a power grid in a large-scale renewable energy source grid-connected scene.

The present disclosure discloses a method for controlling coordinated operation of multiple wind generators to avoid secondary frequency drop. The method includes the following steps: first, the Doubly Fed Induction Generator (DFIG) required for frequency support is dynamically selected based on a real-time disturbance power of a power grid and the rotating speed level of each DFIG; second, the virtual inertial control parameters are adaptively regulated according to the system frequency and the change in the rotating speed of the DFIG participating in frequency support, ensuring that the frequency support requirements are satisfied; and finally, the remaining DFIGs are controlled to release the rotor kinetic energy to support the rotating speed recovery of the selected DFIG, so as to reduce the extra energy absorbed from the power grid in the process.

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 disclosure relates to a system and method for adjusting a tool with a plurality of segments for inserting into a cavity of a machine. The method includes determining an initial alignment measurement of at least a portion of the tool; comparing the initial alignment measurement to a target alignment measurement to determine an adjustment amount; and adjusting at least one of the plurality of segments based on the adjustment amount. The tool includes a plurality of segments moveably coupled, where one or more of the plurality of segments comprises a unique dimensional measurement affecting a fit tolerance.

The invention discloses an intelligent control cooling fan driving method, relates to the technical field of intelligent cooling, and solves the problems that the working mode of a traditional fan is irrelevant to an electric control working state, the fan always runs at the maximum rotating speed after electric control is started, and electric energy is wasted. The cooling fan driving method comprises the steps that the controller conducts power sampling and dynamic calibration on the direct-current side and the alternating-current side of the inverter circuit respectively, and voltage and current are obtained; calculating corresponding power and a power loss value according to the corresponding voltage and current on the two sides, performing temperature compensation on the power loss value according to the junction temperature of the field effect transistor to obtain real-time power loss, and recording loss duration; according to the environment temperature, a loss power threshold value and a loss time threshold value are preset and compared with the real-time power loss and the loss duration time, and meanwhile the real-time power loss and the loss duration time are stored to the controller; and establishing a nonlinear mapping model of the PWM duty ratio and the voltage of the electric control high-power output port, and regulating and controlling the rotating speed of the fan in combination with a multi-stage speed regulation mechanism so as to complete the driving control of the fan.

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 of operating an aircraft gas turbine engine including: a core including a turbine, a compressor, a combustor, and a core shaft connecting the turbine to the compressor; a fan upstream of the core; a fan shaft; at least one bearing supporting the fan shaft; at least one auxiliary system using some of the fuel; an oil loop system to supply oil to the bearing; and a heat exchange system including: a primary fuel-oil heat exchanger through which oil in the oil loop system and substantially all the fuel flow to transfer heat between the oil and the fuel; and a secondary fuel-oil heat exchanger through which oil in the oil loop system and a portion of the fuel flow, to transfer heat between the oil and the fuel; and a fuel pump; wherein, under cruise conditions, fuel temperature on leaving the second heat exchanger is 120° C. to 200° C.

The invention discloses a rapid dynamic response control method for a turboshaft engine. According to the method, a gas turbine rotation acceleration cascade control structure is used for controlling the turboshaft engine; a feed-forward compensation form with predicted required power as a feed-forward compensation amount is introduced into an inner ring fuel flow instruction control position of a gas turbine rotation acceleration cascade control structure; introducing a feed-forward compensation form which takes a required power prediction error as a feed-forward compensation amount into an outer ring gas turbine rotation acceleration instruction control position of the gas turbine rotation acceleration cascade control structure; and a recursive least square algorithm is used to carry out adaptive adjustment on feed-forward compensation parameters of the two loops. The invention further discloses a rapid dynamic response control system for the turboshaft engine. Compared with the prior art, the technical scheme can effectively improve the response speed of the engine control system.