9 results about "Compressor stall" patented technology

The present application proposes a method, device, electronic device, and storage medium for predicting the stall boundary of a compressor, relating to the technical field of compressor aerodynamic design. The method comprises: performing flow calculations on the compressor to obtain flow calculation results; determining the stage static pressure lift coefficients and diffusion factors of different blade height sections of the compressor based on the flow calculation results; determining the first stall section from the different blade height sections based on the stage static pressure lift coefficients and diffusion factors of the different blade height sections; determining the limit value that the stage static pressure lift coefficient of the first stall section can reach; and predicting that the compressor has reached the stall boundary in response to the stage static pressure lift coefficient of one level on the first stall section reaching the limit value. As a result, the present solution improves the accuracy and speed of predicting the compressor stall boundary, thereby achieving rapid and accurate prediction of the compressor stall boundary.

By means of a device for compressing a gas stream, comprising: at least one feed line (2) feeding a gas stream comprising at least one gaseous compound to a compressor unit (4), and at least one discharge line (3) for discharging the compressed gas stream from the compressor unit; a compressor unit (4) comprising at least one first compressor stage (1) and one final compressor stage (F) wherein the feed pipe (2) is in fluid communication with the gas inlet of the first compressor stage (1) and the gas outlet of the first compressor stage (1) is in fluid communication with the gas inlet of the last cooling device (WA00F), and the gas outlet of the last cooling device (WA00F) is in fluid communication with the gas inlet of the final compressor stage (F) and the discharge line (3) is in fluid communication with the gas outlet of the final compressor stage (F); at least one first bypass (6a) connecting the exhaust line (3) to a fluid connection between the last cooling device (WA00F) and an immediately preceding compressor stage, in which the exhaust line (3) is connected by means of a first flow regulator (5a) located in the first bypass (6a) and comprising at least one valve (10), the amount of gas carried in the bypass gas flow can be controlled and thus the through-flow of the gas flow through the final compressor stage (F) can be adjusted; at least one second bypass (6b) provided with a second flow regulator (5b), in which the bypass connects the fluid connection between the last cooling device (WA00F) and the final compressor stage (F) to the feed line (2), and by means of a corresponding method which can be carried out using this device, the cooling device (WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, WA00F, compressor stall of the compressor unit (4) can be better coordinated with individual compressor stages, and condensation of the returned compressed gas stream can be avoided. The final compressed gas stream produced by the method provides a compressed hot gas that can be used to integrate heat into the process steps after compression.

The invention discloses a deep learning-based online identification method for stall and surge of an aviation compressor, and belongs to the field of aviation compressor stability research. A three-layer architecture is adopted, wherein a data layer collects dynamic pressure signals of a gas compressor in real time, and 512-dimensional feature vectors are obtained through FFT preprocessing; the logic layer constructs and trains a CNN model, an LSTM model and a CNN-GRU model, and an optimal model is screened out; and the presentation layer realizes interaction and visual presentation of upper and lower computers through LabVIEW. According to the method, stall surge can be pre-warned more than 50 ms in advance, manual dependence is reduced, embedded deployment is adapted, and the running safety and economical efficiency of the aero-engine can be improved.

The invention discloses a compressor stall fault acoustic identification method and system, and relates to the field of engine state monitoring and fault diagnosis, and the method comprises the steps: collecting an acoustic signal in the operation process of a compressor; framing and windowing the acoustic signal; performing spectrum analysis and frequency band division on each frame of windowed signal to generate a frame energy vector; evaluating the importance of each frequency band based on a random forest out-of-bag replacement method, and screening out key frequency bands; constructing a triangular filter bank by taking each frequency in the key frequency set as a vertex, and performing neighborhood expansion when the spacing between adjacent frequencies exceeds a spacing threshold to obtain a reconstructed adaptive filter bank and a final filter energy feature vector; and inputting the final filter energy feature vector into a deep neural network model to obtain an identification result of whether the gas compressor is in a stall state or not. The method has the advantages that the equipment cost is reduced, the installation process is simplified, the stall feature pertinence analysis capability is improved, and the recognition result robustness is enhanced.

The application discloses a compressor stall failure acoustic identification method and system, and relates to the field of engine state monitoring and fault diagnosis. The method comprises the following steps: collecting acoustic signals in the operation process of the compressor; performing frame division and windowing processing on the acoustic signals; performing spectrum analysis and frequency band division on each frame of windowed signals to generate a frame energy vector; evaluating the importance of each frequency band based on the random forest out-of-bag replacement method to screen out key frequency bands; constructing a triangular filter bank with each frequency in the key frequency set as a vertex, and performing neighborhood expansion when the interval between adjacent frequencies exceeds a threshold interval to obtain a reconstructed adaptive filter bank and a final filter energy feature vector; and inputting the final filter energy feature vector into a deep neural network model to obtain an identification result of whether the compressor is in a stall state. The application has the advantages of reducing equipment cost, simplifying installation process, improving stall feature targeted analysis capability, and enhancing the robustness of the identification result.

The utility model discloses a cross beam structure of a compressor locked-rotor test cabinet and a test cabinet mounting rack, the cross beam structure comprises a cross beam body and an electricity measurer, and the electricity measurer is used for detecting whether an instrument chamber is electrified when a circuit fault occurs; the cross beam body is provided with a first rectangular insulating plate, the side, deviating from the cross beam body, of the first rectangular insulating plate extends outwards to form a first mounting area, the cross beam body is provided with a second rectangular insulating plate, and the side, deviating from the cross beam body, of the second rectangular insulating plate extends outwards to form a second mounting area. The cross beam body is detachably installed on the cabinet body of the test cabinet through the cooperation of the first installation area and the second installation area. According to the cross beam structure of the compressor locked-rotor test cabinet, the instrument chamber and the circuit breaker chamber are isolated through cooperation of the cross beam body and the first rectangular insulating plate and the second rectangular insulating plate which are arranged at the two ends of the cross beam body, and meanwhile the electricity measurer detects the electrification condition of the instrument chamber in real time; and the injury to operators caused by misoperation is effectively avoided.

The water spraying structure of the water vapor compressor, the water vapor compressor and the water spraying control method are used for the water vapor compressor, the water spraying structure of the water vapor compressor comprises a water supply system, a plurality of cartridge receiver water spraying hole assemblies and a hub water spraying hole assembly, and the cartridge receiver water spraying hole assemblies are arranged in the circumferential direction of a cartridge receiver; the hub water spraying hole assembly comprises a plurality of hub water spraying hole assemblies arranged in the circumferential direction of the hub and the same axial plane of the casing, the casing water spraying hole assembly comprises a plurality of casing water spraying holes formed in the air inlet flowing direction, and the casing water spraying holes are distributed in the front edge area, the middle area and the rear edge area of the blade. Along the same axial plane of the hub, the hub water spraying hole assembly comprises a plurality of hub water spraying holes formed in the air inlet flowing direction. And the water supply system is respectively connected with the casing water spraying holes and the hub water spraying holes. The water spraying structure of the water vapor compressor can destroy the blade tip leakage flow and inhibit the generation of stall surge of the water vapor compressor.

The application belongs to the field of gas turbine stall identification, and is a kind of gas turbine aerodynamic instability identification method in the starting process. The gas turbine aerodynamic test of the gas turbine single rotor generator is carried out to collect the aerodynamic test data, and then the equal speed characteristic line is established as a variable to disperse the compressor working point influence curve to obtain a series of discrete working points. The starting process working line and the parking and speed reduction process working line in the discrete working line are compared. Whether the instability is judged by comparing the difference between the combustor oil-gas ratio of the aerodynamic process working line and the combustor oil-gas ratio of the parking and speed reduction process working line. The method for quickly and accurately identifying whether the compressor stalls and the degree of aerodynamic instability in the starting process by using the aerodynamic measurement parameters in the gas turbine operation process supports taking measures as soon as possible to ensure the safe operation of the gas turbine and analyzes the causes of the gas turbine failure.