40 results about "Compressor stall" patented technology

The invention relates to an electrical subsystem to power a vehicle refrigeration system. The electrical subsystem includes an AC drive electrically coupled to a high voltage DC bus. The AC drive provides “refrigeration compressor AC power” responsive to a cooling demand. The electrical subsystem also includes a “low voltage DC bus”. The low voltage DC bus powers a plurality of low voltage refrigeration components including refrigeration fans. A microcontroller sets the compressor AC voltage and the compressor AC frequency. A method of preventing vehicle refrigeration system compressor stall includes the step of limiting the electrical AC power to the compressor such that the AC voltage does not droop causing a compressor stall. Also, an electrical subsystem for powering a compressor in a vehicle refrigeration system includes “V/f” operating information for the compressor, and a microcontroller commands the AC voltage and the AC frequency to the compressor.

Systems, tangible non-transitory machine readable computer media, and methods are provided. In one embodiment a system includes an industrial controller having at least one processor configured to: receive a measured input from a turbomachinery having a compressor, execute a hybrid model of the compressor, receive a measured output, compare the measured input to the measured output to derive an error value, perform a signature analysis if the error value is beyond a range; and derive a probability of compressor stall based on the signature analysis.

This invention is a means for preventing loss of flame and compressor section instability in a turbine engine. The invention uses an Electronic Control Unit to modify the fuel system demand signal to the final controlling element or elements of a turbine engine to prevent rapid changes either for increasing or decreasing the amount of fuel to the engine. The invention offers the simplicity and reliability of electronic control over previously used mechanical means such as dashpots, variable orifices, springs, and cams. The use of an electronic delay means further allows for reduction in the weight of the overall engine due to elimination of the mechanical apparatus, the ability to change the delay constants in a simple fashion by changing a preprogrammed value rather than physically changing the mechanical hardware, and the ability to have one or more differing delay rates for increasing or decreasing fuel delivery and operating conditions.

A method and system for detecting precursors to compressor stall and surge in which at least one compressor parameter is monitored to obtain raw data representative of said at least one compressor parameter. The raw data is pre-processed using a frequency demodulator to produce pre-processed data, and the pre-processed raw data is post-processed using a Kalman filter to obtain stall precursors.

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: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 thedata dimension according to the input requirement of the LR-WaveNet prediction model; according to the time sequence, by adopting an LR-WaveNet prediction model, giving the surge prediction probability of each sample; and by adopting an LR-WaveNet prediction mode, giving the surge probability of data with noise points along with time, and testng 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.

The invention discloses an axial flow compressor stall surge prediction device based on frequency characteristic change. An inlet dynamic pressure/flow sensor is mounted at an inlet casing wall of a compressor, an outlet dynamic pressure/flow sensor is mounted on the periphery of an outlet casing wall of the compressor, the inlet dynamic pressure/flow sensor and the outlet dynamics/flow pressure sensor are correspondingly connected with a signal acquisition card at the same time, the signal acquisition card is connected with a single-chip microcomputer established with a spectrum characteristic database, a noise energy ratio threshold valve is arranged in the spectrum characteristic database, and the single-chip microcomputer is connected with a controller conducting the surge early warning when the radiation noise energy ratio of the outlet end of the compressor reaches a set noise energy ratio threshold valve. By establishing the spectrum characteristic database, the pressure fluctuation frequency change in a working process of detecting and monitoring the compressor in real time, the frequency spectrum characteristics of the inlet air pressure and the outlet air pressure can becompared, the early warning is effectively conducted on the occurring of the surge before the surge occurs, and the reliability is high.

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.

A hybrid electric propulsion system includes a gas turbine engine having a low speed spool and a high speed spool. The low speed spool includes a low pressure compressor and a low pressure turbine, and the high speed spool includes a high pressure compressor and a high pressure turbine. The hybrid electric propulsion system also includes an energy storage system, an electric motor configured to augment rotational power of the high speed spool, and a controller. The controller is operable to detect a start condition of the gas turbine engine, control power delivery from the energy storage system to the electric motor based on detecting the start condition, and provide a compressor stall margin using a power-assist provided by the electric motor to the high speed spool over a targeted speed range during starting of the gas turbine engine.

An apparatus for a unique wind tunnel useable for testing aerospace specific sensors and probes is presented. The apparatus utilizes an effective variable nozzle, allows testing of aerospace devices over a near infinite Mach and Reynolds numbers in subsonic flow. The variable nozzle allows for quick and easy adjustment over a minimum 1×10{circumflex over ( )}7 range of Reynolds number conditions from flow velocity of Mach 0.01 to 0.99. The optimal design of the apparatus allows for adaptation to different size test tunnels, using existing facilities to reduce cost, enabling various aerospace design applications. The apparatus of the present invention, provides a highly variable test environment in order to improve the development of advanced aerospace sensors, including benefits such as: development of flow sensors to prevent compressor stall; development of optical sensors to optimize turbine and compressor airflow; and, development of temperature sensors to increase efficiency of turbine engine operation.

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 an implementation method of an unsteady plasma excitation layout. The method comprises the steps of obtaining flow characteristics of a blade tip area of a compressor rotor under a near stall condition by utilizing numerical simulation; determining the change rule of the direction of the volume force formed by plasma excitation induction based on the flow characteristics ofthe blade tip area of the compressor rotor under the near stall condition; and obtaining a bent plasma excitation layout according to the curve of the function f(t). According to the method, an unsteady plasma excitation layout is designed on the basis of the flow characteristics of the rotor blade tip of the near-stall-point compressor, the direction of the plasma excitation induced volume forcecontinuously changes in the circumferential direction and is always perpendicular to the main/backflow interface, unsteady excitation of the flow field of the blade tip area of the compressor rotor is achieved, and thus efficient inhibition of compressor stall is achieved.

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.