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40 results about "Compressor stall" patented technology

A compressor stall is a local disruption of the airflow in the compressor of a gas turbine or turbocharger. A stall that results in the complete disruption of the airflow through the compressor is referred to as a compressor surge. The severity of the phenomenon ranges from a momentary power drop barely registered by the engine instruments to a complete loss of compression in case of a surge, requiring adjustments in the fuel flow to recover normal operation.

Integrated multiple power conversion system for transport refrigeration units

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.
Owner:CARRIER CORP

Hybrid model based detection of compressor stall

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.
Owner:GENERAL ELECTRIC CO

Method and Apparatus for Prevention of Compressor Stall and Combustion Flameout in a Turbine Engine

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.
Owner:PEARCE KEVIN P

Method and system for detecting precursors to compressor stall and surge

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.
Owner:GENERAL ELECTRIC CO

Axial flow compressor stall surge prediction method based on deep learning

ActiveCN112001128AImprove the performance of active controlImprove forecast accuracyGeometric CADSustainable transportationAviationData set
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.
Owner:DALIAN UNIV OF TECH

Systems and Methods for Detecting the Onset of Compressor Stall

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.
Owner:GENERAL ELECTRIC CO

Axial flow compressor stall surge prediction method based on deep learning

InactiveCN111737910AImprove the performance of active controlImprove forecast accuracyGeometric CADSustainable transportationAviationData set
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.
Owner:DALIAN UNIV OF TECH

Prediction method of multistage axial-flow compressor stall margin on the basis of characteristic value theory

The invention relates to a prediction method of a multistage axial-flow compressor stall margin. The prediction method comprises the following steps: according to a situation of the rotating stall inception of an axial-flow compressor, adopting a small perturbation theory to establish a three-dimensional compressible Euler equation which describes a flow field; applying harmonic decomposition and a dispersion relation to establish a boundary condition on the hub and the leaf opex of each drainage basin; adopting a three-dimensional semi-actuator model to carry out modelling on a stator and a rotor, and adopting a mode matching technology, the conservation law and the representation condition of compressor loss characteristics on an interface to obtain a characteristic value problem which solves a linearized flow field; and solving the characteristic value problem to obtain the characteristic disturbance frequency of a compression system, and judging system stability through the characteristic disturbance frequency, wherein a judgement standard is that the disturbance frequency [Omega] is a complex number, [Omega] is [Omega]R+i[Omega]I, disturbance is attenuated along with time evolution when the imaginary part [Omega]I of the frequency is greater than 0, the system is stable, otherwise, [Omega]I is less than 0, the disturbance is amplified along with time, and the system loses stability. The prediction method can be used for predicting the rotating stall inception of the multistage axial-flow compressor.
Owner:BEIHANG UNIV

Axial flow compressor stall surge prediction device based on frequency characteristic change

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.
Owner:JIANGXI UNIV OF SCI & TECH

Method and apparatus for detecting compressor stall precursors

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.
Owner:GENERAL ELECTRIC CO

Rotating stall detection using optical measurement of blade untwist

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.
Owner:PRIME PHOTONICS LC

Aircraft engine power-assist start stability control

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.
Owner:RAYTHEON TECH CORP

Wind tunnel with an effective variable nozzle for testing various aerospace specific sensors and probes

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.
Owner:BIRCH BRIAN JEFFREY

Compressor stall pre-warning signal reconstruction and identification method based on single-path sensor signal

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.
Owner:NORTHWESTERN POLYTECHNICAL UNIV

Unsteady plasma excitation layout design method for inhibiting compressor stall

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.
Owner:AIR FORCE UNIV PLA

Prediction Method of Stall Boundary of Multistage Axial Compressor Based on Eigenvalue Theory

The invention relates to a prediction method of a multistage axial-flow compressor stall margin. The prediction method comprises the following steps: according to a situation of the rotating stall inception of an axial-flow compressor, adopting a small perturbation theory to establish a three-dimensional compressible Euler equation which describes a flow field; applying harmonic decomposition and a dispersion relation to establish a boundary condition on the hub and the leaf opex of each drainage basin; adopting a three-dimensional semi-actuator model to carry out modelling on a stator and a rotor, and adopting a mode matching technology, the conservation law and the representation condition of compressor loss characteristics on an interface to obtain a characteristic value problem which solves a linearized flow field; and solving the characteristic value problem to obtain the characteristic disturbance frequency of a compression system, and judging system stability through the characteristic disturbance frequency, wherein a judgement standard is that the disturbance frequency [Omega] is a complex number, [Omega] is [Omega]R+i[Omega]I, disturbance is attenuated along with time evolution when the imaginary part [Omega]I of the frequency is greater than 0, the system is stable, otherwise, [Omega]I is less than 0, the disturbance is amplified along with time, and the system loses stability. The prediction method can be used for predicting the rotating stall inception of the multistage axial-flow compressor.
Owner:BEIHANG UNIV

Axial seam processing casing

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.
Owner:INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI

Compressor Stall Premonition Signal Reconstruction and Recognition Method Based on Single Sensor Signal

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.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
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