1928 results about "Gas generator" patented technology

The invention discloses a gas generator and energy storage battery hybrid energy supply scheduling strategy, belongs to the technical field of storage and charging, and mainly solves the problems that in an energy supply mode of a gas generator in existing oil and gas drilling operation, the power generation efficiency of the gas generator is low, and the gas generator is prone to flameout when coping with an impact load. Measuring and acquiring data of voltage and current of oil and gas drilling operation energy consumption equipment, the starting number of gas generators and the residual electric quantity of an energy storage battery; 2, calculating the real-time total power, the power abrupt change rate and the load rate of the gas generator according to the measured data; 3, the number of gas generators needing to be started and the charging and discharging state of energy storage electricity are determined according to the calculation and analysis result; and 4, repeating the steps 1-3 until the drilling operation is finished. The scheduling strategy depends on an existing energy management system, the starting number of the gas generators and the charging and discharging states of the energy storage batteries are reasonably controlled by combining the total power fluctuation characteristics of oil and gas drilling operation, comprehensive management of hybrid energy supply of the gas generators and the energy storage batteries in the oil and gas drilling operation is achieved, the power generation efficiency of the gas generators is improved, and the energy consumption is reduced. Meanwhile, flameout of the gas generator is avoided, and operation safety is guaranteed.

A gas generator includes a housing, one or more first discharge ports provided in the housing and configured to discharge the combustion gas, one or more second discharge ports provided in the housing configured to discharge the combustion gas, and a closing member covering at least one of the one or more first discharge ports and at least one of the one or more second discharge ports together. The closing member includes a portion covering the at least one first discharge port and configured to rupture at a first rupture pressure and a portion covering the at least one second discharge port and configured to rupture at a second rupture pressure, and the closing member includes a breakage assisting portion configured to reduce a strength of the closing member at at least a boundary portion between the at least one first discharge port and the at least one second discharge port.

The invention discloses a starter over-rotation protection control method and system, electronic equipment and a storage medium, and the method comprises the steps: firstly collecting a power turbine transmission chain tail end rotation speed signal and a gas generator rotation speed signal, and then judging whether the gas generator rotation speed reaches a first preset rotation speed or not; and if the rotating speed of the gas generator reaches a first preset rotating speed, the decreasing rate of the rotating speed at the tail end of the power turbine transmission chain is larger than a rotating speed decreasing rate threshold value, and the duration time exceeds preset time, or if the decreasing amplitude of the rotating speed at the tail end of the power turbine transmission chain exceeds a preset value, parking protection is started. If the rotating speed of the gas generator does not reach the first preset rotating speed all the time, it can be judged that the starter is not really ignited, the starter is in the test run test process of starting (oil) sealing, false starting, cold running and the like, at the moment, the power turbine does not have the over-rotating problem, and even if the decreasing rate or the decreasing amplitude of the rotating speed of the tail end of a power turbine transmission chain meets the preset conditions, the engine cannot be ignited. And the parking protection is not started, so that the normal test run test is not influenced.

A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.

The invention discloses a filter, a gas generator and a vehicle, the filter comprises a filter body, the filter body comprises a plurality of filter layers arranged along the inside and outside direction, a plurality of flow guide holes are formed in the filter layers, and at least two flow guide holes have different flow guide directions for fluid. Therefore, the flowing direction of fluid is changed when the fluid flows through the filter body, the flowing path of the fluid in the filter is lengthened, the contact time of the fluid and the filter body is prolonged, the flowing speed of the fluid in the filter is slowed down, and the heat exchange efficiency between the fluid and the filter is improved; the change of the flowing direction is also beneficial to improving the filtering effect of the filter body on impurities in the fluid, and the safety and reliability of the filter are improved.

The invention provides an intelligent control gas generator set and a control system, and relates to the technical field of gas power generation. The gas generator set comprises a compression ignition type internal combustion engine, a synchronous generator, an intelligent control box and a plurality of sensors. The intelligent control box comprises a display screen, a data memory, a central processing unit and a unit regulator; the central processing unit is used for receiving collected data of the sensors and processing the collected data to obtain adjustment parameters of the compression ignition type internal combustion engine; the unit regulator regulates the input air flow of the engine, the piston motion state and the rotating speeds of the engine and the synchronous generator according to the regulation parameters; the synchronous generator converts mechanical energy obtained by the engine into electric energy to be output, the operation efficiency and economical efficiency of the gas generator set are improved, emission is reduced, and environment-friendly power generation is achieved.

The invention provides a gas generator set fault detection method and device, equipment and a storage medium, and belongs to the technical field of gas power generation, and the method comprises the steps: obtaining target detection data collected by different types of sensors of a gas generator set, and calculating a correlation coefficient between the target detection data and a target parameter; adding the target detection data of which the correlation coefficient is greater than a set threshold value into a fusion candidate set, and calculating a target weight corresponding to each target detection data in the fusion candidate set; based on each piece of target detection data in the fusion candidate set and the target weight corresponding to each piece of target detection data, obtaining comprehensive detection data; performing feature extraction on the comprehensive detection data to obtain time domain features and frequency domain features corresponding to the comprehensive detection data; and determining the fault type of the fault of the gas generator set based on the time domain feature and the frequency domain feature. According to the gas generator set fault detection method and device, the equipment and the storage medium provided by the invention, the accuracy of fault detection can be improved.

The invention relates to a new energy vehicle power battery protection flame-retardant system and method, and belongs to the technical field of new energy vehicle protection. The system comprises a controller, a power source, an unfolding device and sensors, the power source, the unfolding device and the sensors are electrically connected with the controller, the unfolding device comprises a gas generator and flame-retardant cloth, and the sensors comprise a temperature sensor arranged on a vehicle power battery, a smoke sensor and collision sensors arranged on a vehicle body and the power battery; and the unfolding device is arranged corresponding to a power battery of the vehicle. The invention has the following beneficial effects: when the vehicle power battery burns due to high temperature or accident collision, flames, high temperature and a large amount of smoke generated by burning are isolated, the escape time of passengers is prolonged, the medical cost caused by casualties is reduced, and the economic loss is effectively reduced; and meanwhile, by reducing the number of casualties in traffic accidents, the overall safety level of the society is improved, and the social stability is maintained.

A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.

There is provided a safety apparatus including a push-up member in which an ejected object is hardly displaced even during transportation, and an aerial vehicle including the safety apparatus. A safety apparatus 100 includes a cylinder 14 that accommodates a piston member 10 and is provided with a bore 13 through which the piston member 10 protrudes to the outside (upward in FIG. 1) during operation, a push-up member 15 that is pushed up in one direction by the piston member 10, an ejected object 16 that is pushed up while being supported by the push-up member 15, a gas generator 17 as a power source that moves the piston member 10 in the cylinder 14, a container 18 that has a bottomed cylindrical shape and accommodates the piston member 10, the cylinder 14, the push-up member 15, the ejected object 16, and the gas generator 17, and a lid 21 that closes an opening end of the container 18. A movement preventing member 27 that prevents the ejected object 16 from moving in a circumferential direction of a bottomed cylindrical portion 19 is provided on an upper surface of a support 20 of the push-up member 15.

A gas generator includes an igniter, a partition member that axially partitions a space in the inside of a housing into a gas generating agent accommodation chamber and a filter chamber, and a gas generating agent and a coil spring accommodated in the gas generating agent accommodation chamber. The coil spring is interposed between the partition member and the gas generating agent and fixes the gas generating agent while it keeps the gas generating agent away from the partition member. V1 represents a volume of the gas generating agent accommodation chamber and V2 represents a volume of a non-filled space which is a space where the gas generating agent is not arranged in the inside of the gas generating agent accommodation chamber as a result of arrangement of the coil spring, where V1 and V2 satisfy a condition of 0.05≤V2 / V1≤0.32.

The utility model relates to a gas flow device for calibrating a float flowmeter. The gas flow device comprises a gas generator; a pressure control assembly; the flow regulating valve is used for regulating the flow of the gas medium; the etalon assembly at least comprises a first etalon, a first valve body connected with the first etalon and the measured float flowmeter, a second etalon and a second valve body connected with the second etalon and the measured float flowmeter, and the measuring range of the first etalon is different from that of the second etalon; the measured float flowmeter is selectively communicated with the first valve body or the second valve body; the controller, the pressure control assembly, the flow regulating valve and the standard device assembly are all connected with the controller, when the standard device with at least two measuring ranges is arranged in different flow ranges, the standard device with the measuring ranges does not need to be independently connected again, only the controller needs to control opening and closing of a valve body of the corresponding standard device, shutdown installation is not needed, operation is easy, and the cost is low. The structure is simple, operation is convenient, automation is high, and meanwhile work efficiency can be improved.

The invention discloses a cloud edge cooperative fault diagnosis method for a gas generator set, and the method comprises the following steps: S1, obtaining fault criteria and symptoms of a gas turbine based on domain knowledge, carrying out the fault diagnosis analysis of the gas turbine based on technology fusion according to multiple criteria and symptoms, and building a logic rule database of different faults; s2, establishing a gas turbine modular simulation model, and performing energy efficiency diagnosis and optimization operation on the simulation model based on the logic rule database; s3, analyzing a fault influence mechanism of the optimized simulation model, and evaluating the service life of the core component of the gas turbine based on the fault influence mechanism of the simulation model; and S4, performing overall health assessment on the gas turbine based on the service life assessment result of each core component. According to the method, the effect of accurately mapping the relationship between the equipment health state and the working condition parameters can be achieved, so that the effect of comprehensively and dynamically evaluating the health level of the gas generator set is achieved, and the effect of efficiently and accurately diagnosing the fault of the gas turbine is achieved.

The invention discloses a combustion experiment system of a rotary fuel gas generator. The combustion experiment system comprises a rotary fuel gas generator experiment table, a supply system, a measurement and control system and an ignition system, the rotary fuel gas generator experiment table is respectively connected with the supply system, the ignition system and the measurement and control system; the supply system is used for stably supplying fuel and oxidant gas to the fuel gas generator on the rotary fuel gas generator experiment table, and the gas flow can be adjusted through a computer; the ignition system is used for igniting the rotary fuel gas generator, the measurement and control system is used for collecting and recording the temperature, pressure and rotating speed of the rotary fuel gas generator during working, and the gas flow and pressure can be adjusted through a computer, so that closed-loop control over the rotating speed of the rotary fuel gas generator is achieved. The combustion performance of the rotary gas generator under different flow rates and equivalence ratios can be simulated, closed-loop control can be carried out on the rotating speed of the rotary gas generator, and accurate control over the combustion process is achieved.

The invention discloses an ejection device, a control method of the ejection device and electric mobile equipment, and the ejection device comprises a guide structure which is connected to a body; the ejected body is contained in the guide structure and is connected to the body in a releasable manner through a fastener; the parachute is accommodated in the guide structure in a foldable manner and is connected with the ejected body; the gas generator is mounted on the outer wall of the guide structure; wherein the fastener releases the catapulted body when responding to ignition current to be broken, and the gas generator inflates the parachute when responding to the ignition current, so that the parachute is converted into an unfolded state from a folded state, and the catapulted body is driven to fall. The dangerous source or the unit needing to be protected serves as the ejected body to be ejected from the body, damage to the body caused by fire of the dangerous source is effectively reduced, the safety of passengers is greatly improved, and an efficient and practical safety solution is provided for various scenes related to flight safety and equipment protection.

The invention provides a control method and device of a mixed gas power generation system, equipment and a storage medium, and belongs to the technical field of new energy power generation. The method comprises the following steps: calculating the introduction rate of each target gas based on load operation data, the type of gas introduced into the gas generator set at present, the type of target gas introduced into the gas generator set after a first duration in a combustion stage and the proportion of the target gas, based on the introduction rate and the total heat per unit time of the exhaust gas output by the gas generator set after the second duration, the exhaust gas proportion used for heating each target gas is calculated, each target gas is heated based on the exhaust gas proportion, and the temperature value of the gas in the gas generator set is monitored in real time; and regulating and controlling the operation state of the mixed gas power generation system based on the temperature value. The proportion of gas input into the gas generator can be flexibly adjusted, and the energy utilization rate of the system is increased.

The invention provides a landing and life-saving system adaptive to a non-fully-coated single aircraft. The landing and life-saving system comprises a helmet for wearing, a flying suit connected with the aircraft and used for wearing, and a plurality of mechanical feet mounted on the aircraft, the helmet comprises a shell and a non-trigger air cushion arranged in the shell, and a visual window is arranged on the front side of the shell; the flying suit comprises a vest, a back air bag installed on the back of the vest, a thoracico-abdominal air bag installed on the front portion of the vest and a gas generator connected with the air bags through pipelines, the gas generator is installed on the vest or the aircraft, and a trigger switch for inflating the air bags is arranged on the gas generator. The mechanical foot comprises a supporting rod, a rotating rod and a mounting block, the mounting block is connected to the aircraft, one end of the rotating rod is rotationally connected with the mounting block or the aircraft, one end of the supporting rod is rotationally connected with the other end of the rotating rod, and the other end of the supporting rod serves as a supporting foot. The system is used for assisting normal flight landing of a manned flight non-coated single aircraft, and realizes forced landing and lifesaving.

A two-stage gas generator for ejection comprises a barrel, a first gas generation assembly and a second gas generation assembly. The first gas generation assembly comprises a first igniter, a first rupture disk and a throttling valve. The second gas generation assembly comprises a second igniter and a second rupture disk. The first igniter comprises an electric detonator I which is used for blasting the first rupture disk to enable high-pressure inert gas in the barrel body to sequentially flow through a third gas guide hole in the throttling valve, the position of the first rupture disk and a first gas guide hole in the first igniter to enter a working chamber in the launching barrel; the second igniter comprises a second electric detonator which is used for blasting the second rupture disk to be matched with the first igniter so that the remaining high-pressure inert gas in the barrel can enter the working cavity in the launching barrel through the position of the second rupture disk and a second gas guide hole in the second igniter. The device can meet the initial low overload requirement of a launched object in the takeoff stage and the cylinder outlet speed requirement in the middle and later periods, is simple in structure and light in weight, and a generated pushing air source is clean and free of residues and cannot expose a launching point.

The invention relates to an assembly (1) comprising an aircraft turbine engine (2), a pylon (40) for mounting the turbine engine on an element of the aircraft, and a system for suspending the turbine engine from the pylon, the turbine engine having a longitudinal axis (X) and comprising, from upstream to downstream, in the gas flow direction: > a fan casing (11) centred on the longitudinal axis (X) and having a first axial end (12) located upstream of the fan (10); and > a gas generator (16) configured to receive an air flow generated by a fan, the pylon (40) being generally elongate along the longitudinal axis (X) and being able to be attached to the element of the aircraft, characterised in that the suspension system comprises at least one intake force uptake link (30, 30a, 30b), a first end (31, 31a, 31b) of which is connected to an attachment point (11a, 11b) of the fan casing (11) located on the first axial end or on an upstream portion of the fan casing, and a second, opposite end (32, 32a, 32b) of which is connected to the pylon.

The invention discloses an intelligent inspection system of a gas generator set, and particularly relates to the field of intelligent inspection, which comprises a multi-dimensional operation parameter real-time acquisition module, a data processing module, an equipment operation evaluation module, a dynamic adjustment module, a fault analysis module, a fault disposal and effect verification module and an equipment health trend prediction module. The multi-dimensional operation parameter real-time acquisition module is used for acquiring key operation parameters in real time in the operation process of the gas generator set by utilizing a multi-parameter sensor array; the data processing module is used for carrying out preprocessing and feature extraction on the collected key operation parameters; the equipment operation evaluation module is used for carrying out operation risk analysis according to the extracted equipment state characteristics and constructing a risk evaluation model; according to the method, comprehensive sensing of the running state of the gas generator set is achieved by deploying the multi-parameter sensor array, multiple dimension parameters are collected, deep feature extraction and analysis are carried out on each parameter, and the one-sidedness of traditional inspection is avoided.

The invention describes an airbag module (10), specifically a knee airbag module, comprising at least a module housing (12), an airbag, specifically a knee airbag, and an inflator (16), as well as a holding element (14), the holding element (14) including a seat (18) for the inflator (16) and enclosing the inflator (16) at least partly, in particular in a cage-like manner, the holding element (14) including securing elements (20) at least for securing the holding element (14) and the airbag to the module housing (12), the holding element (14) and / or the module housing (12) comprising a fixing element (24) for fixing the inflator (16) in the holding element (14). The invention further describes a method for replacing an inflator (16) of an airbag module (10).

The invention relates to an indoor transformer with an automatic fire extinguishing system, the transformer comprises a bearing frame, a fixing plate, a rotating shaft, a non-stored pressure type buffer fire extinguisher, a connecting pipe, a top frame spraying device and the like, through the design of the non-stored pressure type buffer fire extinguisher, a fire extinguishing agent can be quickly sprayed; in addition, the system is provided with a secondary suction pipe, unused dry powder can be recycled, the resource utilization rate is increased, the operation cost is reduced, the system is further provided with a standby fire extinguisher, when the main fire extinguisher cannot completely extinguish the fire, the standby system is automatically started, and the fire extinguishing efficiency is improved. A non-stored pressure type buffer fire extinguisher is adopted, when a fire occurs, an external power source is not needed, after a gas generator is triggered through a UPS power source, a fire extinguishing agent can be rapidly released, and fire extinguishing dry powder is sprayed to a fire source area through a connecting pipe and a spraying device.

The utility model discloses a bridge ship collision prevention active protection device which comprises a laser range finder, a control assembly, a main bridge pier, a main bridge bearing platform, a separation type ship collision prevention facility structure, a polyurethane foam rotary drum and a riverbed, the laser range finder and the control assembly are arranged on the upper portion of the main bridge pier, and the main bridge bearing platform is arranged at the bottom of the main bridge pier. A plurality of separated ship collision prevention facility structures are arranged on the periphery of the main bridge bearing platform on the main bridge piers, polyurethane foam rotating cylinders are arranged on the separated ship collision prevention facility structures, and the other ends, away from the polyurethane foam rotating cylinders, of the separated ship collision prevention facility structures are used for being buried in a riverbed to be fixed. When the distance between the ship and the main bridge pier is detected to be smaller than a certain range through the optical distance measuring instrument, the control assembly controls the gas generator to inflate the gas bag to generate buoyancy, the polyurethane foam rotating drum is pulled to the water surface through the buoyancy to make contact with the ship, and the situation that the ship collides with the main bridge pier and consequently the main bridge pier is damaged is prevented.

An assembly for an aircraft propulsion system (20) includes a propulsion module (24), a gas generator (26) and an anti-icing system (28). The propulsion module (24) includes an open propulsor rotor (30). The gas generator (26) is configured to drive rotation of the open propulsor rotor (30) and includes a flowpath (74), a compressor section (69), a combustor section (70), a turbine section (71) and an exhaust section (72). The flowpath (74) extends through the compressor section (69), the combustor section (70), the turbine section (71) and the exhaust section (72). The turbine section (71) is axially between the combustor section (70) and the open propulsor rotor (30) along the axis (22). The anti-icing system (28) is configured to bleed gas from the flowpath (74) in the exhaust section (72) to provide heated gas and to direct the heated gas to the propulsion module (24) to reduce or prevent ice accumulation on an exterior surface (50, 66, 108) of the propulsion module (24).

An assembly is provided for an aircraft propulsion system. This assembly includes a propulsion module, a gas generator and an anti-icing system. The propulsion module includes an open propulsor rotor. The gas generator is configured to drive rotation of the open propulsor rotor about an axis. The gas generator includes a flowpath, a compressor section, a combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section. The turbine section is axially between the combustor section and the open propulsor rotor along the axis. The anti-icing system is configured to bleed gas from the flowpath in the exhaust section to provide heated gas. The anti-icing system is configured to direct the heated gas to the propulsion module to reduce or prevent ice accumulation on an exterior surface of the propulsion module.

The invention describes an airbag module (10) comprising an airbag (12), an elongate gas generator (14) and a diffusor (16), wherein the gas generator (14) includes an outer housing (18) with outflow openings (20) distributed over the circumference (U) which define an outflow area (22), wherein the outflow area (22) of the gas generator (14) is enclosed by the diffusor (16), wherein the diffusor (16) has a central mount hole (24) into which the outer housing (18) protrudes so that the diffusor (16) circumferentially encloses an axial portion of the outer housing (18) which comprises the outflow area (22), wherein the diffusor (16) includes at least one contact face (26, 26a) and at least two gas guiding surfaces (28a, 28b) on the inner face of the diffusor (16) delimiting the mount hole (24), wherein the contact face (26, 26a) is directly adjacent to the outer housing (18) of the gas generator (14) and the gas guiding surfaces (28a, 28b) are radially spaced apart from the outer housing (18) while forming at least a first collection chamber (30a) and a second collection chamber (30b) into which gas flowing out of the outflow area (22) flows, wherein the first collection chamber (30a) opens into at least one first outlet opening (32a) and the second collection chamber (30b) opens into at least one second outlet opening (32b), wherein the first collection chamber (30a) is separated from the second collection chamber (30b) by the at least one contact face (26) specifically in the form of a separating web (34), wherein the diffusor (16) is completely arranged in an inflatable internal volume of the airbag (12), wherein the airbag (12) comprises at least a first airbag chamber (36a) and a second airbag chamber (36b) which are separated from each other, wherein the gas flowing into the first collection chamber (30a) flows, via the first outlet opening (32a), into the first airbag chamber (36a) of the airbag (12) and the gas flowing into the second collection chamber (30b) flows, via the second outlet opening (32b), into the second airbag chamber (36b) of the airbag (12).

A propulsion assembly for a hybrid aircraft including a first and a second engine each having a gas generator and a free turbine, a main rotor coupled to the free turbine of the first and second engines, the first engine including a first electric machine and a second electric machine of lower power than the first electric machine, one of the first or of the second electric machine being able to be coupled to the gas generator and to set the gas generator in rotation during a start phase of the engine, and being further able to be coupled to the free turbine in order to generate electrical energy after the start phase, the other of the first or of the second electric machine being coupled to the gas generator only.

In a gas generator, a plurality of gas discharge ports include a plurality of first gas discharge ports and one or a plurality of second gas discharge ports having an opening pressure higher than an opening pressure of the first gas discharge ports. An opening pressure of the first and second gas discharge ports are set, such that only the plurality of first gas discharge ports of the plurality of gas discharge ports are opened by the pressure of the gas when the igniter is actuated in a stand-alone state before the gas generator is incorporated into an airbag device, and among the plurality of gas discharge ports, the first gas discharge ports excluding some of the first gas discharge ports and at least some of the second gas discharge ports are opened by the pressure of the gas when the igniter is actuated in an assembled state.

The utility model relates to the technical field of riveting assembly, and discloses a full-automatic air cylinder riveting assembly machine which comprises an operation table, an air cylinder feeding disc, an air cylinder discharging disc, a gas generator empty material box and a gas generator feeding box are installed on the top of the operation table, and a riveting dust removal assembly, an oiling machine and a rack sealing ring are fixed to the upper portion of the operation table. An empty disc carrying mechanism is fixed above the air cylinder feeding disc, the air cylinder discharging disc, the gas generator empty material box and the gas generator feeding box. According to the full-automatic air cylinder pressing rivet assembling machine, the alloy frame is additionally arranged on the operation table to protect a machine, the two-way push-pull metal panel is clamped to the alloy frame, dust can be blocked when the machine is not used, and the machine can be conveniently overhauled in time when the machine breaks down; therefore, moving during travel is facilitated.

The invention relates to the technical field of gas generator sets, in particular to a container type gas generator set which comprises an air cooling heat dissipation mechanism, the air cooling heat dissipation mechanism comprises a plurality of wind wheels used for heat dissipation, center shafts of the wind wheels are fixedly connected with rotating shafts, and the outer walls of the rotating shafts are fixedly sleeved with three concentrically-arranged first gears. When the heating value of a certain generator set is increased, the heating condition of the generator set is monitored through the thermistor, a signal is transmitted to the PLC, the resistance of the thermistor is reduced due to heating of the thermistor, then the second gear is made to move upwards through the self-adaptive adjusting assembly, and the driving motor is controlled to stop running through the PLC. And an electric telescopic rod pushes a driving motor to move forwards so as to drive a second gear to move synchronously, so that the second gear is meshed with a first gear with a relatively small diameter, and the rotating speed of the wind wheel is increased.