40 results about "Compressor stall" patented technology

The invention discloses an axial flow compressor stall surge prediction method based on deep learning, and belongs to the technical field of aero-engine modeling and simulation. The method comprises the steps of: firstly, preprocessing aircraft engine surge data, and dividing a test data set and a training data set from experimental data; secondly, sequentially constructing an LR branch network module, a WaveNet branch network module and an LR-WaveNet prediction model; and finally, performing real-time prediction on the test data: firstly, preprocessing the test set data in the same way, and adjusting the data dimension according to the input requirement of the LR-WaveNet prediction model; according to the time sequence, adopting an LR-WaveNet prediction model to give the surge predictionprobability of each sample; and adopting an LR-WaveNet prediction model to give the surge probability of data with noise points along with time, and testing the anti-interference performance of the model. According to the method, the time domain statistical characteristics and the change trend are integrated, the prediction precision is improved, and certain anti-interference performance is achieved; and the active control performance of the engine can be improved, and certain universality is achieved.

A method of detecting onset of a gas turbine condition, such as compressor stall, includes receiving data indicative of an operating parameter of a compressor of the gas turbine. The method also includes performing a wavelet transformation on the data to generate wavelet transformed data. The wavelet transformation is configured to affect a processing characteristic regarding a performance of the wavelet transformation. Features indicative of onset of the gas turbine condition in the wavelet transformed data are then identified to provide an indication for controlling the gas turbine to prevent compressor stall from occurring. A system for detecting onset of compressor stall in a gas turbine includes a sensor for providing data indicative of an operating parameter of the compressor and a processor for performing a wavelet transform on the data to identify features of the optimized wavelet transformed data indicative of onset of stall.

A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode.

Embodiments of the present application include a stall detection system for a gas turbine engine. The system may include a compressor and a number of variable stator vanes associated with the compressor. The variable stator vanes may form one or more variable stator vane stages. The system may also include one or more resolvers associated with one or more of the variable stator vanes. The resolvers may be configured to detect a flutter in an angle of the variable stator vanes. The flutter may be indicative of the onset of compressor stall.

An apparatus for preventing an axial-flow compressor from stalling by employing a casing treatment includes an outer casing having an inner wall with a slot formed to face a rotor blade, an inner casing moveable so as to open the slot in an unstable operating region and close the slot of the outer casing in a stable operating region, and a drive means for moving the inner casing along the axial direction of the outer casing. Thus, the apparatus can be applied not only to a casing treatment structure where the slope of a slot does not vary with the rotational position of the rotor, but also to a casing with a variously shaped slot such as a radial slot or an axial skewed slot.

Systems and methods are provided for real-time detection of the onset of stall in turbomachinery, such as compressor stall. The methods are capable of detecting and analyzing time of arrival of the chord of the blade at a sensor array to provide an indication of the onset of compressor stall. Systems for detecting the onset of compressor stall include: light sources; a plurality of linearly arranged optical fibers for transmitting light from the light sources and for receiving transmitted light reflected from a blade; a detector for measuring intensity of the reflected light; and a processor for analyzing the intensity of the reflected light to determine blade twist angle and from the blade twist angle identify onset of compressor stall. The invention can prevent the needless loss of life and assets caused by compressor stall that may lead to unexpected catastrophic failure of an engine.

This application belongs to the field of aero-engine design, and is a method for designing the fuel supply filling rate at the start of an aero-engine. Through calculation, the expression of the acceleration rate of the high-pressure rotor and the filling rate at the start-up stage is obtained, and the corresponding relationship between the acceleration rate of the high-pressure rotor and the filling rate at the start-up stage is found. , that is to use the acceleration rate of the high-pressure rotor to calculate the filling rate. The filling rate obtained in this way is only affected by the acceleration rate of the high-pressure rotor and is not affected by the high-voltage conversion speed. It can accurately control the speed at the end of filling and improve the supply of the starting filling section. Oil consistency, improve the success rate of starting ignition, and reduce the possibility of compressor stall caused by ignition. At the same time, considering the limitation of the filling rate, the coefficients in the calculation formula of the filling rate are updated in real time to ensure the consistency of filling and improve the adaptability of the method.

The invention discloses a double-closed intercooling compressor experiment system, which comprises two compressors to be tested, a rectification and voltage stabilization unit, an air charging and deflation unit, a surge experiment unit and the like. The experimental system is capable of testing single-stage compressors or double-stage intercooled compressors, and is suitable for performance experiments on compressors with stable media such as air, carbon dioxide, and nitrogen, effectively expanding the test range of the test bench; The requirements of the air inlet parameters of the cold compressor, especially the demand for high inlet pressure, so as to truly simulate the flow state of the intercooler compressor and reveal its internal flow-heat transfer coupling mechanism; the experimental system has the ability to perform surge experiments and can carry out compression Research on the mechanism of engine stall and surge, with the ability to test from normal pressure to high pressure.

The invention provides an axial slit processing casing, which belongs to the technical field of air compressors. The processing casing includes: the moving blades of the compressor rotor are arranged in the processing casing, and the edges of the moving blades face the inner wall of the processing casing; a plurality of edges are provided on the inner wall of the processing casing from the upstream to the downstream corresponding to the edge of the moving blades. The axially extending slit structure of the processing casing, and a plurality of slit structures are uniformly and misplaced distributed along the circumferential direction of the processing casing. The treatment casing provided by the present invention can use the pressure difference between upstream and downstream in the passage to suck the low-energy fluid blocked on the top of the moving blade into the suction slot through the axially misaligned slot structure, and at the same time, it can maximize the flow close to the downstream of the passage. The low-energy fluid is sucked into the slot, and this part of the fluid is ejected upstream of the moving blade, improving the flow condition entering the top of the moving blade, delaying the occurrence of compressor stall, widening the margin of the compressor, and negatively affecting the peak efficiency of the compressor smaller.

A compressor is provided including a casing, a hub, a flowpath, a plurality of blades defining a plurality of axially extending compressor stages and an endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages. The remaining stages of the plurality of compressor stages located upstream of the at least two downstream most stage are devoid of any endwall treatment. Each of the endwall treatments faces a tip of each blade in the at least two downstream most stages. The tip of each blade and the endwall treatment are configured to move relative to each other. The endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages is configured to extend a stall margin to delay stall due to ice ingestion. A method and engine application are disclosed.

The invention provides a compressor stall pre-warning signal reconstruction and identification method based on a single-path sensor signal. The method includes obtaining the pressure signal through asingle-path sensor installed in the circumferential direction of a front-stage case of a compressor; and then according to the rotation characteristic of the compressor stall pre-warning signal, simulating the output of a multi-path sensor in the circumferential direction by adopting a signal translation method, and realizing the multi-path stall pre-warning signal reconstruction of the compressor. The reconstructed multi-path stall pre-warning signal is expressed as the superposition of the torus average and the circumferential pressure disturbance in the vector form, and the circumferentialpressure disturbance vector is subjected to the spatial Fourier transform to be decomposed into the superposition of multi-order modal waves; the first-order modal amplitude is compared with the set threshold value, and the stall is considered to occur when the threshold value is exceeded, and the identification of the stall pre-warning signal is realized. A single sensor can be used to replace aplurality of sensors, so that the defect that a plurality of sensors are installed is overcome, and the method has a large engineering application value.

The invention discloses a compressor blade top plasma stabilization system, which comprises: a compressor blade; a high-voltage electrode arranged in a casing above the compressor blade, and the high-voltage electrode is arranged opposite to the compressor blade, In addition, the upper and lower sides of the high-voltage electrode are covered with insulating materials; the pressure sensor is connected to the computer through the acquisition board; the plasma actuator is connected to the high-voltage electrode and the compressor blades, and the AM and FM circuit is also connected to the computer. With the present invention, since the whole system can be automatically controlled by a computer, and the pressure sensor is used to detect the pressure signal on the inner wall of the compressor, the one shown can automatically detect the sign of a stall when the compressor is near a stall condition and utilize the top of the blade and the discharge of the casing to generate The plasma blocks the leakage flow, thereby reducing the flow loss, widening the stability margin, and delaying the stall.