1315 results about "Gas compressor" patented technology

The invention discloses an energy-saving control method and device for a gas compressor and a medium. The method comprises the steps that historical operation data of a gas compressor are collected, and the historical operation data comprise compressor operation parameters, environment parameters, gas parameters and pipe network operation parameters; training a compressor performance model, a load prediction model and an energy efficiency optimization model according to the preprocessed historical operation data; performing operation data prediction according to the collected real-time operation data by using a compressor performance model, a load prediction model and an energy efficiency optimization model to obtain predicted operation data in a future predetermined time period; calculating the predicted operation data by adopting a non-dominated sorting genetic algorithm, and determining an optimal operation scheme; and the control parameters of the optimal operation scheme are issued to control systems of all the compressors for energy-saving control over the compressors.

The invention discloses a stator blade shape-following frequency modulation design method based on a bending vibration mode and application, belongs to the field of vibration design of stator blades of aero-engines and gas turbines, and is suitable for vibration frequency modulation design of non-cantilever type stator structure blades (such as fans and gas compressor stators) with inner rings and outer rings in the aero-engines or the gas turbines. According to the method, firstly, static frequency and dynamic frequency modal analysis is carried out through finite element modeling, and dangerous resonance points and corresponding vibration modes in a working rotating speed range are recognized by combining a Campbell diagram; based on a vibration mode amplitude normalization result, setting a vibration degree parameter and a scale factor, selecting a high response node and carrying out directed disturbance, and updating a structure model to improve a target vibration mode frequency; and through frequency amplification verification and iterative optimization, geometric reconstruction and frequency modulation confirmation are finally completed in combination with aerodynamic performance and processing requirements. The method can realize rapid and accurate frequency modulation of a specific bending vibration mode, avoids introduction of new resonance, and has the advantages of high efficiency, strong adaptability and the like.

The invention discloses a gas compressor surge precursor identification method fusing image feature migration and domain self-adaption, and belongs to the field of aero-engine modeling and fault diagnosis. The method comprises the steps that firstly, blade tip pressure signal data in the process from steady-state throttling to stall of the gas compressor are preprocessed to obtain a plurality of samples, and each sample is converted into a recurrence plot; secondly, constructing a ConvLSTM network to extract spatial and temporal features of the recurrence plot, and extracting graph topology features from the output of the ConvLSTM network through a graph convolutional network; thirdly, a ConvLSTM-GCN model is constructed, and graph topological features including space-time features are extracted; carrying out graph topology feature alignment between the source domain data and the target domain data; the ConvLSTM-GCN model is trained to obtain a prediction model; and finally, performing real-time prediction on the test data set to obtain the surge prediction probability. According to the invention, the problem of low prediction precision of the existing RNN, CNN and variant deep learning models thereof can be solved; in combination with a transfer learning method based on domain self-adaption, the problem that the feature distribution difference between a target domain and a source domain is large is solved, and the generalization ability of the model is improved.

The invention belongs to the technical field of aviation second power systems, and provides a dual-fuel aircraft combined power system which comprises an air compressor, a heat regenerator, a main combustion chamber, a gas turbine, a PEM fuel cell and a starting / power generator, the starting / power generator, the air compressor and the gas turbine are of a coaxial structure, air compressed by the air compressor is divided into two paths, and the two paths are communicated with each other. One path of compressed air enters the main combustion chamber through the cold end of the heat regenerator, and the rear end of the main combustion chamber is connected with a gas turbine; the other path of compressed air enters the PEM fuel cell, the PEM fuel cell supplies power to the electric bus bar, and the reaction rear end of the PEM fuel cell is connected with the gas turbine; the gas turbine is jointly driven by the main combustion chamber and the PEM fuel cell, and an exhaust channel of the gas turbine passes through the hot end of the heat regenerator. The fuel cell power generation unit composed of the H2 fuel tank, the PEM fuel cell and the secondary combustion chamber is used for receiving high-temperature compressed gas from the gas compressor, the high-temperature and high-pressure gas of the gas compressor can conduct hot air purging on cold start of the fuel cell, low-temperature start of the PEM fuel cell is helped, and the fuel cell power generation efficiency is improved. And meanwhile, high-temperature and high-pressure air at the outlet of the compressor is humidified and cooled through cooling of liquid water, and the requirement for system accessories is simplified.

The invention provides an ammonia / kerosene dual-fuel precooling engine and a fuel cell power generation system, and belongs to the technical field of aviation systems. The problems of poor variable working condition performance of an engine, difficulty in matching of a gas compressor and a turbine, low working efficiency, fuel waste and the like due to the fact that working of the gas compressor is limited by overhigh total temperature of flying incoming flow air under the high Mach number of an aircraft are solved. According to the invention, the electric energy generated by the solid oxide fuel cell system is supplied to the aircraft load and the motor, and the motor drives the secondary gas compressor to do work in a manner of coaxial installation with the secondary gas compressor, so that the previous single-pole compression is changed into multi-stage compression. A dual-fuel pre-cooling propulsion method is adopted, liquid ammonia and aviation kerosene are selected as dual fuels of the system, the heat sink requirement for incoming flow air pre-cooling can be met, the fuel heat value requirement needed when the aircraft flies at the high Mach number can also be met, and therefore stable and safe flight of the aircraft at the hypersonic speed becomes possible.

The invention relates to the technical field of equipment running state monitoring, in particular to a gas compressor running state monitoring method and system.The method comprises the steps that a real-time monitoring data sequence of a gas compressor under each preset dimension in the current compression period is obtained, and the real-time monitoring data sequence of the gas compressor under each preset dimension in the current compression period is obtained for any sampling moment of the current compression period; obtaining a basic weight of each preset dimension at any sampling moment according to a preset number of groups of historical data; performing stage division on the current compression period to obtain a stage weight set of each stage, and according to the stage weight set, adjusting the basic weight of each preset dimension at any sampling moment to obtain a dynamic weight; performing weighting processing on the real-time monitoring data of each preset dimension by using the dynamic weight to obtain an equipment health index at any sampling moment; and according to the change rate of the equipment health indexes at the adjacent sampling moments in the current compression period, abnormal early warning is performed on the gas compressor, so that the operation state of the gas compressor is monitored more accurately.

The invention discloses a voiceprint monitoring method, system, medium and equipment for rotation stall of an aero-engine compressor, and the method comprises the steps: determining the layout of a microphone array through the model parameters of the compressor of the aero-engine, and carrying out the synchronous collection of sound pressure time domain signals of multiple channels of the compressor of the aero-engine through the microphone array; arranging the multi-channel sound pressure time-domain signals in sequence to construct a time-domain signal matrix; performing spectral analysis on the sound pressure time-domain signals by adopting a fast Fourier transform algorithm to obtain a spectrogram of the sound pressure time-domain signals of each channel, monitoring whether an abnormal single-tone frequency peak value lower than one time of rotation frequency appears in the spectrogram or not, obtaining an acoustic mode spectrogram of the abnormal single-tone frequency peak value by adopting a single-frequency acoustic mode decomposition method, and obtaining an acoustic mode spectrum of the abnormal single-tone frequency peak value; and whether the rotating stall characteristic of the gas compressor occurs in the acoustic mode spectrogram is monitored to judge whether the rotating stall characteristic of the gas compressor occurs or not.

The invention discloses a flow control method of a gas compressor, which relates to the technical field of flow control of gas compressors, and comprises the following steps of: deploying a sensor in the gas compressor, monitoring various parameters of gas flow in real time, and providing gas flow monitoring data for the whole system; performing preprocessing operation on the original data acquired from the sensor; dividing the gas flow data into a plurality of monitoring windows according to the time length, and for each monitoring window, extracting an index of potential gas reverse flow from the preprocessed data by adopting a feature engineering technology as a feature vector to represent a potential risk of gas flow reverse flow. The air flow parameters are monitored in real time, data preprocessing is carried out, the feature engineering technology and the deep learning model are combined, the potential risk in the air flow is accurately predicted, the rotating speed of the compressor and the opening degree of the air inlet valve are adjusted in time when the risk occurs, and therefore effective control over reverse flowing of the air flow is achieved; and long-term operation of the compressor in a safe and efficient state is ensured.

The invention relates to an oil-proof emulsification control method and system for an air compressor of an urban rail vehicle, and solves the problem of lubricating oil emulsification caused by insufficient working efficiency of the air compressor and environment humidity change by constructing a comprehensive control system comprising the compressor, an oil-proof emulsification device and a controller. The system monitors lubricating oil temperature and environment humidity in real time through a temperature sensor and a humidity sensor; the working rate of the air compressor is accurately calculated, wherein the vehicle operation time t2 takes the operation speed larger than 10 km / h as the calculation starting point; the controller comprehensively judges whether the oil-proof emulsification device is started or not based on temperature, humidity and working rate data, and the control strategy comprises the step of dynamically adjusting the working rate judgment node according to the real-time temperature and humidity. According to the method, accurate and reliable control over the oil-proof emulsification process is achieved, emulsification of the lubricating oil is effectively prevented, and energy consumption and maintenance cost can be reduced.

The invention discloses a gas-steam combined cycle unit denitration system control method and system, and relates to the technical field of gas turbine control, and the method comprises the steps: obtaining the operation parameters of the gas-steam combined cycle unit denitration system control process, and correcting the gas turbine load through the air temperature of the inlet of a gas compressor, calculating a load feed-forward control quantity and an exhaust flow feed-forward control quantity through a feed-forward function based on the corrected gas turbine load and gas turbine exhaust flow; calculating feedback control quantity through a PID (Proportion Integration Differentiation) controller on the basis of the nitrogen oxide concentration set value at the outlet of the waste heat boiler and the actual nitrogen oxide concentration; summing the feedforward control quantity and the PID feedback control quantity to obtain a feedforward-feedback control quantity, and correcting the feedforward-feedback control quantity through an SCR spray gun input rate correction function to obtain a final urea solution flow regulating valve instruction. The method disclosed by the invention has better effects in the aspects of rapidity, reliability and stability of the denitration control system.

The invention discloses a gas compressor inlet air filtering device, and relates to the technical field of compressor inlet air filtering, the gas compressor inlet air filtering device comprises a base, a support frame, a fixed sleeve, a rotating sleeve, a filter screen, a partition plate, an air inlet pipe and a backflushing pipe, one side of the fixed sleeve is provided with a vent hole and an ash discharge hole, and the other side of the fixed sleeve is provided with an air inlet hole and a backflushing hole; the rotating sleeve is rotatably arranged in the fixed sleeve, the filter screen is fixedly arranged at one end of the rotating sleeve, the partition plates are fixedly arranged in the rotating sleeve and divide the rotating sleeve into a plurality of independent cavities, and one end of the air inlet pipe and one end of the backflushing pipe are slidably arranged in the air inlet hole and the backflushing hole respectively. And the other ends of the air inlet pipe and the back-flushing pipe are propped against the filter screen. The back-flushing cleaning process of the air inlet filtering device does not need to stop the operation of the compressor, so that the production continuity is ensured, the production efficiency is improved, the production stagnation time caused by shutdown is reduced, the overall production efficiency is improved, and the economic loss caused by shutdown is reduced.

The invention provides an aero-engine surge margin screening method based on gas compressor parameters. The aero-engine surge margin screening method comprises the following steps that firstly, pressure value parameter collection is conducted in the engine test run rotating speed rising process through two outlet total pressure measuring sensors; 2, processing based on the collected pressure value parameter to obtain a secondary processing pressure value parameter; and 3, calculating by utilizing the secondary processing pressure value parameter, and returning a characteristic curve. According to the method, the surge margin of the engine is quickly and efficiently judged by performing data feature processing on the pressure monitoring parameters of the conventional compressor of the aero-engine, and a new method and thought are provided for screening the surge margin of the aero-engine; the method is applied to the surge screening work of the aero-engine; theoretical analysis and test verification show that after the method is applied, the surge screening result optimization effect is obvious, the surge screening requirement is fully met, and the test cost is reduced.

A foamed liquid dispensing system includes a container for receiving a liquid to be dispensed connectable to, and removable from, a gas charging unit. The gas charging unit includes a gas compressor, gas pressure sensing means, a control unit and a user interface. The user interface permits a user to input a desired final gas pressure from a minimum value to a maximum value in discrete steps. The control unit instructs the gas compressor to charge the container with gas to the desired final pressure. The gas pressure is continuously monitored and the flow of gas into the container is stopped once the desired final gas pressure has been reached. The user interface displays the gas pressure in the container as the charging cycle proceeds. Once charged with gas and removed from the gas charging unit, the container substantially retains the final desired gas pressure until the liquid is dispensed.

The utility model relates to a gas diffusion cascade device for preparing high-abundance nitrogen-15 isotopes by taking nitrogen as a medium. The gas diffusion cascade device comprises a first gas diffusion cascade, a second gas diffusion cascade, a photocatalysis / electro-catalysis device and a high-speed magnetic suspension gas compressor, the first gas diffusion cascade and the second gas diffusion cascade are ladder cascade and respectively comprise a plurality of gas diffusion separation devices; the photocatalysis / electrocatalysis device is positioned between the first gas diffusion cascade and the second gas diffusion cascade; the high-speed magnetic suspension gas compressor is positioned in front of each gas diffusion and separation device in the nitrogen flowing direction; and obtaining the high-abundance nitrogen-15 isotope prepared by taking nitrogen as a medium from the heavy fraction end of the second gas diffusion cascade. The gas diffusion cascade device is high in separation coefficient, large in flow and high in efficiency, the prepared nitrogen-15 isotope abundance is high, and the gas diffusion cascade device is suitable for industrial application.

A hydrogen storage and delivery system delivering storing and dispensing cryogenic liquid and gaseous hydrogen, comprising cryogenic liquid hydrogen storage vessels with heaters 1, 2, 3, ambient tempe

The invention relates to a methanol internal combustion engine high-temperature fuel cell hybrid power system based on double-path waste heat gradient utilization. The invention relates to the technical field of internal combustion engine waste heat recovery and new energy power system integration. The system comprises a fuel tank, a first pump body, a heat exchanger, a methanol internal combustion engine, a turbine, a gas compressor, an air compressor, a reformer, a high-temperature proton exchange membrane fuel cell, an evaporator and a second pump body. A methanol-water vapor mixture generated by heat exchange of a mixed solution of methanol and water and a high-temperature fuel cell stack coolant in a heat exchanger is introduced into a reforming reactor and is subjected to catalytic reforming to produce hydrogen by utilizing waste heat of high-temperature tail gas of an engine, and the produced hydrogen is directly supplied to an anode of a high-temperature fuel cell. Through a double-path methanol distribution strategy, collaborative design of internal combustion engine waste heat recovery, electric pile heat management and reforming hydrogen production is realized, and the comprehensive energy efficiency of the system is improved.

A light-weight gas compressor convenient to move relates to the field of gas compressors, and is characterized in that three forward cylinders and three reverse cylinders which are arranged in a staggered manner are uniformly fixed on the outer edge surface of an annular plate; the forward air cylinder B is connected with the reverse air cylinder A, the reverse air cylinder A is connected with the forward air cylinder A, the forward air cylinder A is connected with the reverse air cylinder B, the reverse air cylinder B is connected with the forward air cylinder C, the forward air cylinder C is connected with the reverse air cylinder C, and the reverse air cylinder C is connected with an exhaust pipe; the power of the double-end piston rod hydraulic oil cylinder is provided by an oil supply hydraulic oil cylinder A and an oil supply hydraulic oil cylinder B; the double-end piston rod hydraulic oil cylinder arranged in the annular plate is used for controlling the three reverse air cylinders and the three forward air cylinders to achieve gas compression, and the purpose of gas compression which is light in weight and convenient to move is achieved.

The invention relates to a surge margin prediction method and device of a gas compressor, equipment and a storage medium. The method comprises the steps that key parameter point sets obtained through load step iteration of the gas compressor in all the operation stages are obtained, all the key parameter point sets are mapped to performance diagrams of temperature identification to obtain corresponding mapping performance diagrams, discrete points in the same temperature layer in all the mapping performance diagrams are fitted, and the corresponding mapping performance diagrams are obtained; and the thermal state performance curves of the gas compressor in all the operation stages are determined, the surge critical points of all the thermal state performance curves are obtained, the predicted surge margin of the gas compressor in all the operation stages is determined according to the surge critical points of all the thermal state performance curves and all the key parameter point sets, and load step iteration is achieved based on multi-physics field coupling of the gas compressor. By adopting the method, the surge margin of the gas compressor in different operation stages can be predicted based on the key parameter point set obtained by load step iteration realized by considering multi-physics field coupling in each operation stage of the gas compressor, so that the accuracy of a prediction result is improved.

The invention discloses a split-flow type flexible dynamic green ammonia synthesis system which comprises a synthesis gas compressor unit, a recycle gas compressor unit, a hot gas-gas heat exchanger, an ammonia synthesis tower, a water cooler, a cold gas-gas heat exchanger, at least one ammonia cooler and an ammonia separator, the method is characterized in that the feed gas is divided into two streams, one stream enters the hot gas heat exchanger to exchange heat with the reacted synthesis gas, and the other stream directly enters the ammonia synthesis tower through a first shunting pipeline to adjust the temperature of a bed layer in the ammonia synthesis tower. The condensation temperature of the synthesis gas, including the condensation temperature of the synthesis gas at the outlets of the water cooler, the cold gas heat exchanger and the ammonia cooler, is adjusted step by step according to the operation load condition of the device, so that the ammonia content in the synthesis loop is controlled step by step, the loop circulation gas amount is adjusted step by step, and the stable fluctuation of the pressure of the ammonia synthesis loop is maintained; and flexible dynamic operation of the device is realized.

The invention belongs to the technical field of turbine engine design, and particularly relates to a turbine interstage combustion chamber supersonic cruise engine and a control method thereof.The turbine interstage combustion chamber supersonic cruise engine comprises a fan adopting a FLADE fan; the gas compressor is arranged behind the fan; the main combustion chamber is arranged behind the gas compressor; the high-pressure turbine is arranged behind the main combustion chamber and is connected with the gas compressor through a high-pressure shaft; the mixing chamber is arranged behind the high-pressure turbine and is communicated with the fan through an outer duct; the interstage combustion chamber is arranged behind the mixing chamber; the low-pressure turbine is arranged behind the combustion chamber and is connected with the fan through a low-pressure shaft; the spraying pipe is arranged on the low-pressure turbine; and after the injection valve is arranged on the high-pressure turbine, the injection valve deflects to the inner runner surface of the outer duct when the injection valve is opened, and deflects to the outer runner surface of the outer duct when the injection valve is closed.

The invention discloses a five-section anti-surge control method for a cracked gas compressor. Comprising two sets of anti-surge systems in a cracking compressor cold and hot reflux control mode, wherein the anti-surge systems are composed of five-return five-hot reflux valves B connected to an outlet of a cracking gas compressor and a cracking gas feeding end and five-return five-cold reflux valves A connected to an outlet of a reflux tank of a high-pressure depropanizing tower and the cracking gas feeding end; the two compressor anti-surge control systems carry out coordinated control on backflow of the five-return five-hot-backflow valve B and backflow of the five-return five-cold-backflow valve A. Anti-surge control over the five-return five-cold-backflow valve A is added. The cold reflux control compressor anti-surge control system is provided with flow low limit control of a five-section outlet C2 hydrogenation unit and 30% opening limit of a hot anti-surge valve. The anti-surge line of the five-return five-cold-backflow A valve is consistent with that of the five-return five-hot-backflow B valve, and the anti-surge line is 1.2 times that of the five-return five-hot-backflow B valve. According to the invention, the technical problem of more stable control of the five-section anti-surge valve can be solved.

The utility model discloses a polishing device for a stator blade of a gas compressor, and relates to the technical field of blade polishing. The compressor stator blade polishing device comprises a machining table and a mounting plate, two collecting grooves penetrate through the machining table, a first dust suction pipe of an annular structure is mounted on the outer side of the mounting plate through a pipe hoop, a plurality of first dust suction nozzles are mounted on the first dust suction pipe, and a reciprocating lead screw is mounted on one side of the surface of the machining table through a fixing plate; a scraper is arranged on one side of the reciprocating lead screw, a brush is arranged at the bottom of the scraper and matched with the upper surface of the machining table, a second dust suction pipe of a U-shaped structure is installed at the top of the scraper through a pipe hoop, a plurality of second dust suction nozzles are installed on the second dust suction pipe, connecting blocks are fixed to the two ends of the scraper, and the reciprocating lead screw is in threaded fit with the connecting block on the right side and combined with the scraper. And the front-back reciprocating motion of the brush is conveniently adjusted, dust accumulated on the machining table is pushed to the direction of the collecting groove, the second dust suction nozzle is matched, dust raised in the pushing process is adsorbed, and dust flying is avoided.

The invention relates to the technical field of screw gas compressor performance detection, in particular to screw gas compressor assembly performance detection equipment, which comprises a base, two clamping units arranged left and right are mounted at the upper end of the base, the clamping units are used for clamping a screw rotor and driving the screw rotor to rotate, and detection units are distributed above the base. The shape following unit is mounted in the middle of the upper end of the base, and the detection unit is mounted on the shape following unit; the device is used for detecting the wear resistance of the screw rotor, and the wear resistance of the screw rotor is detected in a rolling friction and sliding friction combined manner, so that the actual friction state of the screw rotor during working can be simulated, and the later use effect of the screw rotor is ensured; and meanwhile, constant friction force can be applied to the surface of the screw rotor according to the spiral tooth shape of the screw rotor, so that the accuracy of the wear resistance detection result of the screw rotor is ensured.

A gas compressor is capable of adjusting a temperature of a heat recovery liquid discharged from a waste-heat-recovery heat exchanger to a desired temperature at a low cost without providing a temperature adjusting valve in a passage of the heat recovery liquid. The gas compressor includes a heat exchange liquid temperature sensor for detecting the temperature Tw2 of a heat exchange liquid discharged from a waste-heat-recovery heat exchanger, and a passage that allows at least part of a high-temperature fluid cooled by an air-cooled cooler to flow therethrough into a compressor. A controller has a heat exchange liquid temperature adjusting function to control the rotational speed of a cooling fan such that the temperature Tw2 detected by the heat exchange liquid temperature sensor gets closer to a predetermined target heat exchange liquid temperature Tw2t.

The invention relates to a low-concentration combustible gas concentration system and an operation method thereof, and the low-concentration combustible gas concentration system comprises a flame arrester, a mixing cavity, a non-combustible gas supplementing tank, a gas compressor, a primary separator, a light component secondary separator, a heavy component secondary separator and a concentration regulating valve, the premixed gas sequentially passes through a primary separator, a light component secondary separator and a heavy component secondary separator under the action of a gas compressor to carry out concentration operation on light component combustible gas, non-combustible gas is returned to a mixing cavity, and heavy component gas is discharged into the atmosphere; the invention aims to solve the technical problems of large occupied area and volume, low operation efficiency and poor separation effect of the existing combustible gas separation equipment.

The invention relates to an energy storage temperature control system and a control method thereof.The energy storage temperature control system comprises a heat supply module and a heat transfer module, and the heat transfer module comprises a first heat transfer part exchanging heat with an energy storage battery and a second heat transfer part exchanging heat with an energy storage converter; the heat supply module comprises a gas compressor, a first heat exchanger, an electronic expansion valve and a power pump which are connected through a pipeline, and the energy storage temperature control system has a first mode and a second mode. The gas compressor, the first heat exchanger, the electronic expansion valve, the first heat transfer component and the second heat transfer component are sequentially communicated through pipelines to form a circulation loop. In the second mode, the power pump, the first heat transfer component, the second heat transfer component and the first heat exchanger are sequentially communicated through pipelines to form a circulation loop. The temperature control system can cool the energy storage battery and the energy storage converter at the same time, and the energy efficiency is high.

The invention discloses a standby power supply system, and relates to the technical field of transformer substation power supply, a hydrogen production module is used for producing hydrogen by using commercial power or renewable power and then storing the hydrogen in a high-pressure gas storage tank of a hydrogen storage module, and the hydrogen storage module is provided with a one-way valve for the hydrogen to pass through in one way and a gas compressor for compressing the hydrogen to realize hydrogen conveying; after hydrogen stored in the hydrogen storage module is subjected to power generation through a fuel cell through the power generation module, the hydrogen is input into a storage battery pack of an uninterruptible power supply system of the transformer substation, and in the whole process, the control module detects the state of a main power supply and controls starting and stopping of the power generation module. The hydrogen production rate of the hydrogen production module and the hydrogen storage pressure of the hydrogen storage module are controlled, only water is generated in the power generation process, harmful emission is avoided, direct current generated by the fuel cell is directly matched with a UPS storage battery direct current bus, the response speed is high, conversion loss is reduced, the energy utilization efficiency is improved, the system automation degree is high, and the operation and maintenance cost is low.

The invention provides a multi-stage gas compressor pneumatic optimization method based on grid deformation, and relates to the field of gas compressors. The method comprises the following steps: performing data processing on a CGNS file of an original geometric flow field grid to obtain coordinates of all grids of the original geometric flow field grid; setting a grid boundary control method for the flow field of the multi-stage gas compressor; the original geometric flow field grid is deformed, and a deformed multi-stage gas compressor flow field grid is obtained; and performing CFD calculation on the basis of the deformed multi-stage compressor flow field grid: if the aerodynamic effect of the compressor reaches a preset target, outputting a geometric figure corresponding to the deformed multi-stage compressor flow field, otherwise, defining the deformed multi-stage compressor flow field grid as an original geometric flow field grid, and repeating deformation until the aerodynamic effect of the compressor reaches the preset target. According to the method, the full-three-dimensional CFD calculation precision is guaranteed, the number of optimized real evaluation samples is reduced, the calculation cost of the optimization iteration process is reduced, and full-three-dimensional rapid pneumatic optimization of the multi-stage gas compressor is achieved.

The invention provides a hydrocarbon fuel cell aero-engine, a gas compressor and a fan in the engine are driven by a motor and can also be driven by a turbine shaft, a fuel cell system is located behind a turbine, and a partial oxidation reforming reactor, a combustion chamber, a fuel delivery pump and an exhaust nozzle are sequentially connected. Tail gas of the fuel cell system and gas which does not react completely are used for driving the turbine to rotate, the main shaft is driven to drive the gas compressor and the fan to work, electric energy generated by electrochemical reaction in the fuel cell system can also be used for driving the generator to work, and two working modes of driving the gas compressor and the fan are adopted; the problem of poor economical efficiency caused by the fact that a turbine is used for driving the gas compressor in the high altitude is solved; through the working modes of the dual-drive air compressor and the fan, the engine can be freely switched between the high altitude and the low altitude according to requirements in the using process. The advantages of cleanness and high efficiency of the fuel cell are utilized, and the problem that a traditional aero-engine is high in oil consumption rate is solved.

The invention discloses a gas turbine TCA / FGH large temperature difference driven S-CO2 power cycle system which comprises a gas compressor, a combustion chamber, a gas turbine, a TCA heat exchanger, an FGH heat exchanger, an S-CO2 compressor and an S-CO2 turbine, a hot side inlet and outlet of the TCA heat exchanger is connected with a hot air pipeline, the cold side of the TCA heat exchanger is connected with an S-CO2 working medium circulating device, the hot side of the FGH heat exchanger is connected with the S-CO2 working medium circulating device, and the hot side of the FGH heat exchanger is connected with the S-CO2 working medium circulating device. The cold side of the TCA heat exchanger is connected with a cold natural gas pipeline, the hot side of the TCA heat exchanger absorbs heat of high-temperature air, the air temperature is reduced to a set value, meanwhile, supercritical carbon dioxide after pressure boosting is heated, an S-CO2 turbine is pushed to do work, and natural gas is heated to the set temperature in the FGH heat exchanger. The TCA / FGH temperature difference condition is utilized, the S-CO2 power cycle is driven to output extra electric energy, the peak regulation capacity of the unit is improved, and meanwhile the problem of TCA / FGH heat imbalance is solved.