CN115962101B - Stall state monitoring method and system - Google Patents
Stall state monitoring method and system Download PDFInfo
- Publication number
- CN115962101B CN115962101B CN202211548114.0A CN202211548114A CN115962101B CN 115962101 B CN115962101 B CN 115962101B CN 202211548114 A CN202211548114 A CN 202211548114A CN 115962101 B CN115962101 B CN 115962101B
- Authority
- CN
- China
- Prior art keywords
- stall
- separation
- blade
- monitoring
- target blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012544 monitoring process Methods 0.000 title claims abstract description 257
- 238000000034 method Methods 0.000 title claims abstract description 50
- 238000000926 separation method Methods 0.000 claims abstract description 198
- 238000012545 processing Methods 0.000 claims description 23
- 230000002159 abnormal effect Effects 0.000 claims description 16
- 230000007480 spreading Effects 0.000 claims description 14
- 238000010586 diagram Methods 0.000 description 17
- 238000004891 communication Methods 0.000 description 11
- 238000004422 calculation algorithm Methods 0.000 description 8
- 238000013461 design Methods 0.000 description 8
- 230000009471 action Effects 0.000 description 5
- 238000012360 testing method Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 238000004590 computer program Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 3
- 238000007726 management method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000001960 triggered effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000013473 artificial intelligence Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000013480 data collection Methods 0.000 description 1
- 238000013500 data storage Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000010295 mobile communication Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Abstract
The application discloses a stall condition monitoring method and system, comprising the following steps: firstly, each monitoring point of the target blade is obtained according to stall separation monitoring coordinates, and stall separation signals of each monitoring point are respectively collected through a piezoelectric sensor; based on stall separation signals of the monitoring points, stall separation states of section wing profiles of the target blades at different spanwise positions are obtained; and finally, obtaining the stall state and stall degree of the target blade based on the stall separation states of the section wing profiles at the different spanwise positions. The stall judgment is more accurate based on the three-dimensional flow field characteristics of the target blade and the consideration of power stall, and the operation safety of the blade is improved.
Description
Technical Field
The application relates to the technical field of wind power generation, in particular to a stall condition monitoring method and a stall condition monitoring system.
Background
The wind turbine generator is a system for converting kinetic energy of wind into electric energy, the blades are core components for capturing wind energy of the wind turbine generator, and the running state of the wind turbine generator is directly related to the utilization efficiency of the wind energy.
Serious flow separation on the surface of the blade in a large range is an important cause of the reduction of the generating efficiency of the wind turbine generator, power loss (namely blade stall), load fluctuation, fatigue load increase and even flutter instability. Therefore, how to monitor the flow state and stall condition of the blade surface has important significance for stall control, unit safety protection and corresponding blade power increasing technology. In the prior art, more than one airfoil stall condition of a blade is monitored, a pitot tube is often adopted to directly measure the pressure difference of a specific point near the trailing edge of the airfoil suction surface, and the pressure difference is used as a criterion of airfoil separation stall to judge whether the blade is in the stall condition or not, and is combined with a complete machine control system to provide reference for stall control of the non-rated working condition of the blade, so that the running condition of the blade can be correspondingly adjusted.
However, in the above scenario, the local airfoil stall of the blade does not represent a "stall" throughout the operation of the blade, resulting in reduced operational safety of the blade.
Disclosure of Invention
The application provides a stall condition monitoring method and a stall condition monitoring system, stall judgment of a blade is more accurate, and operation safety of the blade is improved.
In one aspect, a stall condition monitoring method is provided, the method comprising:
acquiring each monitoring point of the target blade according to the stall separation monitoring coordinates; the stall separation monitoring coordinates comprise blade spanwise coordinates and chord wise coordinates;
stall separation signals of all monitoring points are respectively collected through piezoelectric sensors; the stall separation signal comprises at least one of a speed signal and a pressure signal;
based on stall separation signals of the monitoring points, stall separation states of section wing profiles at different unfolding positions of the target blade are obtained;
and obtaining the stall state and the stall degree of the target blade based on the stall separation states of the wing profiles with different spanwise positions.
In yet another aspect, a stall condition monitoring system is provided, the system comprising: a piezoelectric sensor and a data acquisition processing unit; the piezoelectric sensors are arranged at all monitoring points;
The data acquisition processing unit is used for:
acquiring each monitoring point of the target blade according to the stall separation monitoring coordinates; the stall separation monitoring coordinates comprise blade spanwise coordinates and chord wise coordinates;
stall separation signals of all monitoring points are respectively collected through piezoelectric sensors; the stall separation signal comprises at least one of a speed signal and a pressure signal;
based on stall separation signals of the monitoring points, stall separation states of section wing profiles at different unfolding positions of the target blade are obtained;
and obtaining the stall state and the stall degree of the target blade based on the stall separation states of the wing profiles with different spanwise positions.
In yet another aspect, a stall condition monitoring apparatus is provided, the apparatus being applied to a data acquisition processing unit in a stall condition monitoring system, the system further comprising a piezoelectric sensor and a data acquisition processing unit; the piezoelectric sensors are arranged at all monitoring points;
the device comprises:
the monitoring point acquisition module is used for acquiring each monitoring point of the target blade according to the stall separation monitoring coordinates; the stall separation monitoring coordinates comprise blade spanwise coordinates and chord wise coordinates;
The stall separation signal acquisition module is used for acquiring stall separation signals of the monitoring points through the piezoelectric sensor respectively; the stall separation signal comprises at least one of a speed signal and a pressure signal;
the section airfoil type stall state acquisition module is used for acquiring stall separation states of section airfoils at different unfolding positions of the target blade based on stall separation signals of the monitoring points;
and the target blade stall state acquisition module is used for acquiring the stall state and stall degree of the target blade based on the stall separation states of the wing profiles with the different position section.
In one possible implementation, the monitoring point acquisition module is further configured to:
the relation curve acquisition module is used for acquiring a relation curve of a power loss coefficient of the target blade and a coverage duty ratio of a stall separation area on the surface of the blade based on aerodynamic profile information of the target blade;
and each monitoring point acquisition module is used for acquiring each monitoring point of the three-dimensional surface stall separation of the target blade based on the relation curve.
In a possible implementation manner, the relation acquisition module is further configured to:
And determining a reference wind speed, and establishing a relation curve of the power loss coefficient of the target blade and the coverage ratio of the stall separation area on the surface of the blade at the reference wind speed based on the aerodynamic profile information of the target blade.
In one possible implementation manner, the monitoring point acquisition modules are further configured to:
and based on the relation curve, acquiring blade spanwise coordinates of the coverage points of the separation areas corresponding to the power loss thresholds of the target blade under different stall degrees, and determining the coverage points of the separation areas as monitoring points.
In one possible embodiment, the apparatus further comprises:
the blade spanwise coordinate acquisition unit is used for acquiring the blade spanwise coordinate of each monitoring point of the target blade;
the section wing section acquiring unit is used for acquiring section wing sections of the monitoring points at the spreading positions based on the blade spreading direction coordinates of the monitoring points;
the pressure distribution curve acquisition unit is used for acquiring the pressure distribution curve of the section airfoil profile of each monitoring point under the stall attack angle;
and the chord coordinate acquisition unit is used for acquiring chord coordinates of the stall separation area corresponding to each monitoring point covered on the section airfoil according to each pressure distribution curve.
In a possible embodiment, the chord coordinate obtaining unit is further configured to:
according to each pressure distribution curve, obtaining the approximate separation point starting position of the leeward surface of the blade corresponding to the section airfoil of each monitoring point and the pressure reference position of the section airfoil;
and acquiring chord coordinates corresponding to each monitoring point according to the approximate separation point starting position of each monitoring point and the pressure reference position of the section airfoil.
In one possible embodiment, the section airfoil stall condition acquisition module is further configured to:
obtaining stall condition criterion parameters of the section wing profile of the target blade according to the pressure distribution characteristics of the section wing profile corresponding to each monitoring point;
and obtaining stall separation states of the section wing profiles of the monitoring points of the target blade according to comparison results of the stall separation signals corresponding to the chord direction coordinates of the section wing profiles and the stall state criterion parameters.
In one possible embodiment, the target blade stall condition acquisition module is further to:
acquiring the coverage range of a surface stall separation area of the target blade based on the stall separation state of each section airfoil;
And obtaining the stall state and the stall degree of the target blade according to the coverage range of the surface stall separation area of the target blade.
In one possible embodiment, the apparatus is further for:
selecting abnormal stall monitoring points from the monitoring points; the abnormal stall monitoring point is a monitoring point close to the tip position of the target blade;
and when the section airfoil profile of the abnormal stall monitoring point is subjected to stall separation, carrying out protection control operation on the target blade.
In yet another aspect, a computer device is provided that includes a processor and a memory having at least one instruction stored therein that is loaded and executed by the processor to implement a stall condition monitoring method as described above.
In yet another aspect, a computer readable storage medium having stored therein at least one instruction loaded and executed by a processor to implement a stall condition monitoring method as described in any of the above is provided.
The technical scheme that this application provided can include following beneficial effect:
according to the scheme, based on the three-dimensional flow field characteristics of the target blade and the consideration of power stall, stall of the partial section airfoil of the target blade does not necessarily cause stall of the whole target blade in aerodynamic aspects, when stall monitoring is carried out on the target blade, each monitoring point can be determined according to specific aerodynamic profile information of the target blade, stall states of the airfoil of the corresponding section are monitored on each monitoring point, further coverage of a stall separation area on the surface of the blade is judged, stall states and stall degrees of the target blade are finally judged, and the stall judgment is more accurate compared with the existing approximate pitot tube-based airfoil stall measurement technology based on the three-dimensional flow field characteristics of the target blade and the consideration of power stall per se.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram illustrating a stall condition monitoring system according to one example embodiment.
FIG. 2 is a method flow diagram illustrating a stall condition monitoring method according to one example embodiment.
FIG. 3 is a method flow diagram illustrating a stall condition monitoring method according to one example embodiment.
FIG. 4 illustrates an example plot of blade power loss coefficient versus blade surface stall separation area coverage ratio for embodiments of the present application.
FIG. 5 illustrates a schematic diagram of the location of a monitoring point on a blade under normal design conditions in accordance with an embodiment of the present application.
Fig. 6 shows a schematic diagram of the positions of corresponding monitoring points on the blade when the blade power loss is 5% according to the embodiment of the application.
Fig. 7 shows a schematic diagram of the chord-wise coordinate distribution of a section airfoil at a monitoring point Pi according to an embodiment of the present application.
FIG. 8 is a block diagram illustrating the structure of a stall condition monitoring apparatus according to one example embodiment.
Fig. 9 shows a block diagram of a computer device according to an exemplary embodiment of the present application.
Detailed Description
The following description of the embodiments of the present application will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
It should be understood that, in the description of the embodiments of the present application, the term "corresponding" may indicate that there is a direct correspondence or an indirect correspondence between the two, or may indicate that there is an association between the two, or may indicate a relationship between the two and the indicated, configured, or the like.
FIG. 1 is a schematic diagram illustrating a stall condition monitoring system according to one example embodiment. The system comprises a server (a host control algorithm unit), a piezoelectric sensor and a data acquisition processing unit.
Wherein the piezoelectric sensor is disposed at each of the monitoring points of the target blade (illustratively, in fig. 1, each of the monitoring points is P1, P2, pi, pn, pt in fig. 1).
The data acquisition processing unit is used for:
acquiring each monitoring point of the target blade according to the stall separation monitoring coordinates; the stall separation monitoring coordinates include blade spanwise coordinates and chordwise coordinates;
stall separation signals of all monitoring points are respectively collected through piezoelectric sensors; the stall separation signal comprises at least one of a speed signal and a pressure signal;
based on stall separation signals of the monitoring points, stall separation states of section wing profiles at different unfolding positions of the target blade are obtained;
based on the stall separation condition of the various stall position section airfoils, a stall condition and a stall degree of the target blade are obtained.
Further, the stall separation monitoring coordinate may be a predetermined information stored as input to the data acquisition processing unit or set into the data acquisition processing unit.
Optionally, when the system monitors the stall condition of the target blade of the wind turbine generator, the piezoelectric sensors at each monitoring point collect stall separation signals of each monitoring point respectively, the data collection processing unit receives the stall separation signals of each monitoring point and processes each stall separation signal to obtain the stall separation condition of each section airfoil corresponding to each monitoring point, and finally the stall condition and stall degree of the target blade are obtained.
Optionally, the server may be a host control algorithm unit of the wind turbine generator, and after the data acquisition processing unit acquires the stall state and the stall degree of the target blade, the host control algorithm unit may perform corresponding control operation on the target blade according to the stall state and the stall degree of the target blade.
Illustratively, the stall control action is triggered by the host control algorithm unit when the target blade is in a severe stall condition, such as when the stall separation area of the target blade covers more than 50% of the root-to-blade.
Optionally, the data acquisition processing unit is in communication connection with the server through a transmission network (such as a wireless communication network), and the data acquisition processing unit can upload the calculated stall state and stall degree of the target blade to the server through the wireless communication network so as to control the target blade by the server.
Optionally, the server may also perform wireless communication connection with the wind turbine generator through a wireless communication network, and send corresponding algorithm information to a target blade of the wind turbine generator, so as to trigger a stall control action for the target blade.
Optionally, the server may be a server cluster or a distributed system formed by a plurality of physical servers, and may also be a cloud server that provides cloud services, cloud databases, cloud computing, cloud functions, cloud storage, network services, cloud communication, middleware services, domain name services, security services, CDNs, and technical computing services such as big data and artificial intelligence platforms.
Optionally, the system may further include a management device, where the management device is configured to manage the system (e.g., manage a connection state between each module and the server, etc.), where the management device is connected to the server through a communication network. Optionally, the communication network is a wired network or a wireless network.
Alternatively, the wireless network or wired network described above uses standard communication techniques and/or protocols. The network is typically the internet, but may be any other network including, but not limited to, a local area network, a metropolitan area network, a wide area network, a mobile, a limited or wireless network, a private network, or any combination of virtual private networks. In some embodiments, techniques and/or formats including hypertext markup language, extensible markup language, and the like are used to represent data exchanged over a network. All or some of the links may also be encrypted using conventional encryption techniques such as secure socket layer, transport layer security, virtual private network, internet protocol security, etc. In other embodiments, custom and/or dedicated data communication techniques may also be used in place of or in addition to the data communication techniques described above.
In summary, the above scheme is based on the three-dimensional flow field characteristics of the target blade and the consideration of power stall, the stall of the airfoil of the partial section of the target blade does not necessarily cause the stall of the whole target blade in aerodynamic aspects, when the target blade is subjected to stall monitoring, each monitoring point can be determined according to the specific aerodynamic profile information of the target blade, and the stall state of the airfoil of the specific section of the target blade is monitored on each monitoring point, so that the coverage area of the stall separation area on the surface of the blade is judged, and finally the stall state and the stall degree of the target blade are judged.
FIG. 2 is a method flow diagram illustrating a stall condition monitoring method according to one example embodiment. The method may be performed by a data acquisition processing unit as shown in fig. 1. As shown in fig. 2, the method may include the steps of:
s201, acquiring each monitoring point of the target blade according to stall separation monitoring coordinates; the stall separation monitoring coordinates include blade spanwise coordinates and chordwise coordinates.
In a possible embodiment, the stall of the blades of the wind turbine is different from the stall of the section airfoil of the blade, which is defined in wind engineering as the output power of the rotor of the blade composition being lower than the design power value, corresponding to the stall of the section airfoil of the blade in a certain range. That is, a stall of the section airfoil over a certain range of blades does not necessarily result in a stall of the entire wind turbine blade, but the stall of the blade may be caused by a stall of the section airfoil over a large range. Therefore, when the stall condition of the target blade of the wind turbine generator is monitored, firstly, according to the aerodynamic profile information of the target blade, the blade spanwise coordinate of each monitoring point for stall separation of the three-dimensional surface on the target blade (a piezoelectric sensor system is arranged at the blade spanwise coordinate of each monitoring point to acquire flow field monitoring signals such as pressure or speed of each monitoring point), then, according to the chord coordinate in the stall separation monitoring coordinate, the flow field monitoring signals such as pressure or speed are acquired and judged to judge the stall separation condition of each section airfoil corresponding to the stall separation coordinate of each blade, and finally, according to the stall separation condition of each section airfoil corresponding to the stall separation coordinate of each blade, the stall condition and stall degree of the target blade are obtained.
Further, aerodynamic profile information refers to the geometric profile of the target blade used to improve wind energy conversion efficiency, and aerodynamic profile information may be different for different blades.
Further, the individual monitoring points are separation zone coverage points for critical stall levels of the target blade.
Further, the chord-wise coordinate indicates that the stall separation area of the monitoring point corresponding to the chord-wise coordinate covers the position of the section airfoil of the monitoring point, so that the chord-wise coordinate is used for collecting pressure information to judge the airfoil stall state at the span-wise coordinate of the blade; the blade spanwise coordinate is used for judging which section wing profiles on the target blade are in a stall state, and then judging stall separation coverage of the whole target blade. The spanwise coordinates and chordwise coordinates of each blade form the stall separation monitoring coordinate and also form the position of each monitoring point, and preferably, the position of the monitoring point defined in the embodiment is the spanwise coordinate of each blade, that is, each spanwise coordinate of each blade forms each monitoring point of the target blade, and a piezoelectric sensor system is arranged at the spanwise coordinate of each blade; and the chord-wise coordinates on each section airfoil may also constitute chord-wise monitoring points for each section airfoil.
Further, the piezoelectric sensor system at each blade spanwise coordinate comprises two piezoelectric sensors which are respectively arranged at two chordwise positions corresponding to the blade spanwise coordinate.
S202, stall separation signals of all monitoring points are respectively collected through piezoelectric sensors; the stall separation signal includes at least one of a speed signal and a pressure signal.
In one possible implementation manner, each monitoring point is provided with a corresponding piezoelectric sensor, each piezoelectric sensor, a server (a host control algorithm unit) and a data acquisition processing unit form a stall condition monitoring system, stall separation signals of the target blade at the monitoring point are acquired through the piezoelectric sensors, and then stall separation states of the section airfoil profiles corresponding to each monitoring point are analyzed.
Further, the stall separation signal can be a speed signal or a pressure signal, that is, in practical application, the pressure signal at the monitoring point of the target blade can be collected through the piezoelectric sensor so as to analyze the stall separation state of the section airfoil profile corresponding to each monitoring point through the pressure signal at each monitoring point, or the pressure signal at the monitoring point of the target blade can be collected through the piezoelectric sensor first, and the speed signal is further obtained through conversion of the pressure signal so as to analyze the stall separation state of the section airfoil profile corresponding to each monitoring point through the speed signal at each monitoring point.
S203, based on stall separation signals of the monitoring points, stall separation states of section wing profiles at different unfolding positions of the target blade are obtained.
Optionally, for each monitoring point, after the stall separation signal of the monitoring point is obtained, the difference value of the stall separation signals of the section wing profiles at each monitoring point can be analyzed first, so that the stall separation state of each section wing profile of the target blade can be obtained.
S204, based on stall separation states of the wing profiles with the different unfolding positions and the section, obtaining stall states and stall degrees of the target blade.
In a possible implementation manner, in general, a target blade of a wind turbine generator set of conventional design, a stall separation range is gradually expanded from a section airfoil of a blade root area to a section airfoil of a blade tip area in consideration of flexible deformation and three-dimensional effect of the target blade, so that a stall state of each section airfoil of the target blade can be monitored to judge the coverage area of the stall separation area on the surface of the target blade, and further judge the stall state and stall degree of the target blade.
The stall separation state of the section airfoil is divided into a non-stall state or a stall state by an example, and the target blade is assumed to be in a non-stall state when the section airfoil of the monitoring point P1 is in the non-stall state under the assumption that the monitoring point P1, the monitoring point P2 and the monitoring point P3 are sequentially arranged on the target blade from the blade root, and the monitoring point P1 is the monitoring point closest to the blade root area; when the section wing profile of the monitoring point P1 is in a stall state and the section wing profile of the monitoring point P2 is in a non-stall state, the target blade is in a stall state 1, and the stall degree is 0-P2 y; when the section wing profile of the monitoring point P1 is in a stall state, the section wing profile of the monitoring point P2 is in a stall state, and the section wing profile of the monitoring point P3 is in a non-stall state, the target blade is in a stall state 2, and the stall degree is from P2y to P3y; and judging stall separation states of all the monitoring points in sequence, so that the stall state and stall degree of the target blade can be obtained.
In summary, the above scheme is based on the three-dimensional flow field characteristics of the target blade and the consideration of power stall, the stall of the airfoil of the partial section of the target blade does not necessarily cause the stall of the whole target blade in aerodynamic aspects, when the target blade is subjected to stall monitoring, each monitoring point can be determined according to the specific aerodynamic profile information of the target blade, and the stall state of the airfoil of the specific section of the target blade is monitored on each monitoring point, so that the coverage area of the stall separation area on the surface of the blade is judged, and finally the stall state and the stall degree of the target blade are judged.
FIG. 3 is a method flow diagram illustrating a stall condition monitoring method according to one example embodiment. The method may be performed by a data acquisition processing unit as shown in fig. 1. As shown in fig. 3, the method may include the steps of:
s301, acquiring a relation curve of a power loss coefficient of a target blade and a coverage ratio of a stall separation area on the surface of the blade based on aerodynamic profile information of the target blade.
In one possible embodiment, a reference wind speed is determined and a power loss coefficient of the target blade versus blade surface stall separation area coverage ratio curve is established at the reference wind speed based on aerodynamic profile information of the target blade.
Further, when the stall state of the target blade of the wind turbine generator is monitored, a certain key wind speed point is selected as a reference wind speed, and then a BEM method (a blade element momentum method) or a CFD numerical simulation method is adopted to calculate wind power curves with different blade surface stall separation area ratios (namely, a relation curve of the power loss coefficient of the target blade and the coverage ratio of the blade surface stall separation area) according to the aerodynamic profile layout (namely, the aerodynamic profile information) of the target blade. Referring to an exemplary graph of the relationship between the blade power loss coefficient and the coverage ratio of the stall separation area on the blade surface shown in fig. 4, it should be noted that fig. 4 is a schematic diagram, and the specific relationship is determined by the blade profile of the wind turbine generator.
Further, the critical wind speed point may be a certain reference wind speed, e.g. before the rated wind speed, or a certain reference wind speed of an optimal Cp (wind energy utilization coefficient) wind speed segment.
Optionally, in the case of a change in the stall characteristics of the section airfoil/blade due to surface roughness, a change in the environmental turbulence, etc., the surface of the blade may be roughened after actually running in the wind field for a period of time, the running condition of the blade may deviate from the design condition, and the relationship curve of the blade and the section airfoil thereof may also change, so that the relationship curve may be updated in real time. At this time, in the prototype test process of the wind turbine generator, the calibration can be performed through a flow field test, that is, the calibration is performed on fig. 4 through a power loss-separation area curve of the wind field actual test.
Furthermore, the stall monitoring mode provided by the embodiment obtains the relation curve of the power loss coefficient of the target blade and the coverage ratio of the stall separation area on the surface of the blade according to the specific aerodynamic profile information of the target blade, and determines each monitoring point based on the relation curve, thereby not only realizing stall condition monitoring of the early running period of the target blade, but also monitoring stall conditions under the condition of rough states of different degrees on the surface of the blade
Furthermore, compared with the existing stall monitoring mode which judges stall through wind turbine generator set operation characteristic parameters, such as power, load characteristics, acceleration characteristics, indirectly measured local attack angles and the like, or the mode of measuring the frequency of the vortex motion of the separated flow through the motion of the trailing edge accessory, the stall monitoring method is more accurate in judging stall states based on the flow field measurement at the key expansion position of the target blade.
S302, based on the relation curve, acquiring each monitoring point of the stall separation of the three-dimensional surface of the target blade.
In one possible implementation manner, based on the relation curve, blade spanwise coordinates of separation area coverage points corresponding to power loss thresholds of the target blade at different stall degrees are obtained, and each separation area coverage point is determined to be each monitoring point.
Further, in order to effectively monitor and quantitatively characterize the stall condition of the target blade, it is necessary to parametrize the stall of the target blade, and the stall degree of the blade is characterized by the power loss of the blade in this embodiment, that is, the ordinate parameter in fig. 4. Therefore, based on the relation curve shown in the step 4, the separation area coverage points of the key stall degree of the target blade can be obtained according to the relation curve, and each separation area coverage point is the spanwise position of each monitoring point of the three-dimensional surface stall separation of the target blade. According to project monitoring needs, selecting the coverage range points of the separation areas corresponding to the power loss thresholds with different stall degrees, namely, the blade span-wise positions of P1, pi, … and Pn in FIG. 4 as main monitoring points.
For example, referring to fig. 5, a schematic diagram of a position of a monitoring point on a blade under a normal design condition is shown, and a coverage area of a stall separation area of a section airfoil under the normal design condition is about 20% of a direction from a blade root to a blade tip of the blade under a certain reference wind speed, when the corresponding blade is in a stall-free state, that is, a power loss of the blade corresponding to a design power value is 0, as shown by a monitoring point P1 in fig. 5. Referring to fig. 6, a schematic diagram of a position of a corresponding monitoring point on a blade when the power loss of the blade is 5% is shown, and as shown in fig. 6, when the power loss of the blade reaches 5%, the coverage area of the airfoil stall separation area is about 30% of the direction from the blade root to the blade tip.
In one possible implementation, after obtaining the vane spanwise coordinates of each monitoring point of the target vane;
acquiring section wing profiles at the spreading positions of the monitoring points based on the vane spreading coordinates of the monitoring points;
acquiring pressure distribution curves of section wing profiles of all the monitoring points under a stall attack angle;
and acquiring chord coordinates of the stall separation area covered to the section airfoil corresponding to each monitoring point according to each pressure distribution curve.
In one possible implementation, according to each pressure distribution curve, an approximate separation point starting position of a leeward surface of the blade corresponding to the section airfoil of each monitoring point and a pressure reference position (generally arranged near a tail edge of the leeward surface) of the section airfoil are obtained;
and acquiring chord coordinates corresponding to each monitoring point according to the approximate separation point starting position of each monitoring point and the pressure reference position of the section airfoil.
Further, according to the vane spanwise coordinate of the monitoring point determined from the relation curve, the section airfoil shape of each monitoring point at the corresponding spanwise position is obtained, the pressure distribution curve of each section airfoil under the stall attack angle is obtained through analysis, and the starting position of the approximate separation point of the leeward surface of the target vane and the pressure reference position of the section airfoil are obtained to serve as stall separation chordwise coordinates (Pi 0, pi 1) of the section airfoil of the monitoring point. Referring to a stall separation chord coordinate distribution diagram of a section airfoil at a monitoring point Pi shown in fig. 7, the chord coordinate and the spanwise coordinate of the monitoring point Pi are combined to form a three-dimensional surface position of the monitoring point Pi.
Furthermore, the stall monitoring mode provided by the embodiment is realized through the piezoelectric sensor based on the piezoelectric effect, compared with the existing pitot tube and the like, the piezoelectric sensor is high in stability, is not easily influenced by environmental (sand dust, rainfall and other blocking pitot tubes) factors, and is high in environmental and weather adaptability.
Furthermore, the stall monitoring mode provided by the embodiment obtains the pressure or speed and other signals of each monitoring point through the approximate separation point starting position of the leeward surface of the blade corresponding to the section airfoil of each monitoring point and the pressure reference position of the section airfoil, namely directly measuring the flow field parameters of the leeward surface of the target blade, analyzing the flowing and stall states of the target blade, and keeping the integrity of the aerodynamic design of the blade without changing the local aerodynamic shape of the blade.
S303, respectively collecting stall separation signals of all monitoring points through piezoelectric sensors; the stall separation signal includes at least one of a speed signal and a pressure signal.
In one possible implementation mode, during the operation process of the target blade, pressure signals of all monitoring points are collected in real time, and whether the target blade is in a stall state and the stall degree are determined by monitoring the stall separation state and the stall separation coverage of the section airfoil.
S304, based on stall separation signals of the monitoring points, stall separation states of section wing profiles at different unfolding positions of the target blade are obtained.
In one possible implementation manner, stall condition criterion parameters of the section airfoil profile of the target blade are predefined and obtained according to the pressure distribution characteristics of the section airfoil profile corresponding to each monitoring point;
and obtaining stall separation states of the section wing profiles of all the monitoring points of the target blade according to comparison results of the stall separation signals corresponding to the chord direction coordinates (the pressure reference positions and the approximate separation point starting positions) of the section wing profiles obtained through real-time monitoring and comparison results of stall state criterion parameters.
Furthermore, according to the pressure gradient (numerical calculation or wind tunnel test result) distributed in the separation area of each section airfoil of the target blade, stall condition criterion parameters DPR of each section airfoil of the target blade can be obtained, and stall separation conditions of each section airfoil can be judged by taking the stall condition criterion parameters DPR as judgment basis.
The stall separation condition of the section airfoil at the monitoring point Pi is illustratively determined as follows: when Pi1-Pi0> DPR (namely, the pressure Pi1 of the approximate separation point starting position of the section airfoil of the monitoring point Pi minus the pressure value Pi0 of the reference pressure position is larger than the stall condition criterion parameter DPR), judging that the stall condition exists; when Pi1-Pi0< DPR (i.e. the approximate separation point start position Pi1 of the section airfoil at the monitoring point Pi minus the pressure value Pi0 of the reference pressure position is less than the stall condition criterion parameter DPR), the stall separation condition of the section airfoil is determined.
S305, obtaining the stall state and the stall degree of the target blade based on the stall separation states of the section wing profiles at the different unfolding positions.
In one possible embodiment, the coverage of the surface stall separation region of the target blade is obtained based on the stall separation state of the respective section airfoil;
and obtaining the stall state and the stall degree of the target blade according to the coverage range of the surface stall separation area of the target blade.
In one possible implementation, an abnormal stall monitoring point is selected from the various monitoring points; the abnormal stall monitoring point is a monitoring point close to the tip position of the target blade;
and when the section airfoil profile of the abnormal stall monitoring point is subjected to stall separation, carrying out protection control operation on the target blade.
Further, according to the stall separation state of each section airfoil, the coverage area of the stall separation area on the surface of the target blade is judged, the stall state and stall degree (power loss degree) of the target blade are finally obtained, the stall judgment is more accurate, and the operation safety of the blade is improved.
Further, in any case, when stall separation occurs in the section airfoil profile at the abnormal stall monitoring point Pt on the outer side of the target blade, the target blade is judged to be in an abnormal stall state, and a host control algorithm unit is required to be fed back to perform stall protection control actions such as pitching.
Optionally, starting from the blade root of the target blade, the monitoring point P1 is generally near the 15-20% spreading position from the blade root to the blade tip, and the monitoring point P2 is generally near the 25-30% spreading position from the blade root to the blade tip; the monitoring point P3 is generally near the 40% -50% spreading position from the blade root to the blade tip, and the abnormal stall monitoring point Pt is generally near the 75% -85% spreading position from the blade root to the blade tip. In general, when the stall separation area coverage of the blade exceeds 50% of the blade root to the blade, the blade can be judged to belong to a serious stall state, a host control algorithm unit is required to execute control actions, and once the stall state of an abnormal stall monitoring point Pt is judged to be true, the stall control actions are required to be triggered.
In summary, the above scheme is based on the three-dimensional flow field characteristics of the target blade and the consideration of power stall, the stall of the airfoil of the partial section of the target blade does not necessarily cause the stall of the whole target blade in aerodynamic aspects, when the target blade is subjected to stall monitoring, each monitoring point can be determined according to the specific aerodynamic profile information of the target blade, and the stall state of the airfoil of the specific section of the target blade is monitored on each monitoring point, so that the coverage area of the stall separation area on the surface of the blade is judged, and finally the stall state and the stall degree of the target blade are judged.
FIG. 8 is a block diagram illustrating the structure of a stall condition monitoring apparatus according to one example embodiment. The device is applied to a data acquisition and processing unit in a stall condition monitoring system, and the system also comprises a piezoelectric sensor and a data acquisition and processing unit; the piezoelectric sensors are arranged at all monitoring points;
the device comprises:
the monitoring point acquisition module 801 is used for acquiring each monitoring point of the target blade according to the stall separation monitoring coordinates; the stall separation monitoring coordinates include blade spanwise coordinates and chordwise coordinates;
the stall separation signal acquisition module 802 is configured to acquire stall separation signals of the monitoring points through piezoelectric sensors respectively; the stall separation signal comprises at least one of a speed signal and a pressure signal;
the section airfoil stall state acquisition module 803 is used for acquiring stall separation states of section airfoils at different unfolding positions of the target blade based on stall separation signals of the monitoring points;
a target blade stall condition acquisition module 804 is configured to acquire a stall condition and a stall degree of the target blade based on stall separation conditions of the respective different spread position section airfoils.
In one possible implementation, the monitoring point acquisition module 801 is further configured to:
the relation curve acquisition module is used for acquiring a relation curve of the power loss coefficient of the target blade and the coverage ratio of the stall separation area on the surface of the blade based on the aerodynamic profile information of the target blade;
and each monitoring point acquisition module is used for acquiring each monitoring point of the three-dimensional surface stall separation of the target blade based on the relation curve.
In a possible implementation manner, the relation acquisition module is further configured to:
and determining a reference wind speed, and establishing a relation curve of the power loss coefficient of the target blade and the coverage ratio of the stall separation area on the surface of the blade at the reference wind speed based on the aerodynamic profile information of the target blade.
In one possible implementation, the each monitoring point acquisition module is further configured to:
based on the relation curve, blade spanwise coordinates of the coverage points of the separation areas corresponding to the power loss thresholds of the target blade under different stall degrees are obtained, and the coverage points of the separation areas are determined to be monitoring points.
In one possible embodiment, the apparatus further comprises:
The blade spanwise coordinate acquisition unit is used for acquiring the blade spanwise coordinate of each monitoring point of the target blade;
the section wing section acquiring unit is used for acquiring section wing sections of the monitoring points at the spreading positions based on the vane spreading coordinates of the monitoring points;
the pressure distribution curve acquisition unit is used for acquiring the pressure distribution curve of the section airfoil profile of each monitoring point under the stall attack angle;
and the chord coordinate acquisition unit is used for acquiring chord coordinates of the stall separation area corresponding to each monitoring point covered on the section airfoil according to each pressure distribution curve.
In a possible embodiment, the chord coordinate acquisition unit is further configured to:
according to each pressure distribution curve, obtaining the approximate separation point starting position of the lee surface of the blade corresponding to the section airfoil of each monitoring point and the pressure reference position of the section airfoil;
and acquiring chord coordinates corresponding to each monitoring point according to the approximate separation point starting position of each monitoring point and the pressure reference position of the section airfoil.
In one possible embodiment, the section airfoil stall condition acquisition module 803 is further configured to:
Obtaining stall condition criterion parameters of the section wing profile of the target blade according to the pressure distribution characteristics of the section wing profile corresponding to each monitoring point;
and obtaining the stall separation state of the section airfoil of each monitoring point of the target blade according to the comparison result of the stall separation signal difference value corresponding to the chord direction coordinates of each section airfoil and the stall state criterion parameter.
In one possible embodiment, the target blade stall condition acquisition module 804 is further configured to:
acquiring the coverage range of a surface stall separation area of the target blade based on stall separation states of the wing profiles of the sections;
and obtaining the stall state and the stall degree of the target blade according to the coverage range of the surface stall separation area of the target blade.
In one possible embodiment, the device is further adapted to:
selecting abnormal stall monitoring points from the monitoring points; the abnormal stall monitoring point is a monitoring point close to the tip position of the target blade;
and when the section airfoil profile of the abnormal stall monitoring point is subjected to stall separation, carrying out protection control operation on the target blade.
In summary, the above scheme is based on the three-dimensional flow field characteristics of the target blade and the consideration of power stall, the stall of the airfoil of the partial section of the target blade does not necessarily cause the stall of the whole target blade in aerodynamic aspects, when the target blade is subjected to stall monitoring, each monitoring point can be determined according to the specific aerodynamic profile information of the target blade, and the stall state of the airfoil of the specific section of the target blade is monitored on each monitoring point, so that the coverage area of the stall separation area on the surface of the blade is judged, and finally the stall state and the stall degree of the target blade are judged.
Referring to fig. 9, a block diagram of a computer device according to an exemplary embodiment of the present application includes a memory and a processor, where the memory is configured to store a computer program, and the computer program is executed by the processor to implement a stall condition monitoring method as described above.
The processor may be a central processing unit (Central Processing Unit, CPU). The processor may also be any other general purpose processor, digital signal processor (Digital Signal Processor, DSP), application specific integrated circuit (Application Specific Integrated Circuit, ASIC), field programmable gate array (Field-Programmable Gate Array, FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof.
The memory, as a non-transitory computer readable storage medium, may be used to store non-transitory software programs, non-transitory computer executable programs, and modules, such as program instructions/modules corresponding to the methods in embodiments of the present application. The processor executes various functional applications of the processor and data processing, i.e., implements the methods of the method embodiments described above, by running non-transitory software programs, instructions, and modules stored in memory.
The memory may include a memory program area and a memory data area, wherein the memory program area may store an operating system, at least one application program required for a function; the storage data area may store data created by the processor, etc. In addition, the memory may include high-speed random access memory, and may also include non-transitory memory, such as at least one magnetic disk storage device, flash memory device, or other non-transitory solid state storage device. In some implementations, the memory optionally includes memory remotely located relative to the processor, the remote memory being connectable to the processor through a network. Examples of such networks include, but are not limited to, the internet, intranets, local area networks, mobile communication networks, and combinations thereof.
In an exemplary embodiment, a computer readable storage medium is also provided for storing at least one computer program that is loaded and executed by a processor to implement all or part of the steps of the above method. For example, the computer readable storage medium may be Read-Only Memory (ROM), random-access Memory (Random Access Memory, RAM), compact disc Read-Only Memory (CD-ROM), magnetic tape, floppy disk, optical data storage device, and the like.
Other embodiments of the present application will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the application following, in general, the principles of the application and including such departures from the present disclosure as come within known or customary practice within the art to which the application pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the application being indicated by the following claims.
It is to be understood that the present application is not limited to the precise arrangements and instrumentalities shown in the drawings, which have been described above, and that various modifications and changes may be effected without departing from the scope thereof. The scope of the application is limited only by the appended claims.
Claims (9)
1. A stall condition monitoring method, the method comprising:
acquiring each monitoring point of the target blade according to the stall separation monitoring coordinates; the stall separation monitoring coordinates comprise blade spanwise coordinates and chord wise coordinates;
stall separation signals of all monitoring points are respectively collected through piezoelectric sensors; the stall separation signal comprises at least one of a speed signal and a pressure signal;
Based on stall separation signals of the monitoring points, stall separation states of section wing profiles at different unfolding positions of the target blade are obtained;
acquiring a stall state and a stall degree of the target blade based on stall separation states of the wing profiles with different spreading positions;
the method for acquiring each monitoring point of the target blade according to the stall separation monitoring coordinates comprises the following steps:
acquiring a relation curve of a power loss coefficient of the target blade and a coverage duty ratio of a stall separation area on the surface of the blade based on aerodynamic profile information of the target blade;
and acquiring each monitoring point of the stall separation of the three-dimensional surface of the target blade based on the relation curve.
2. The method of claim 1, wherein the obtaining a power loss coefficient of the target blade versus blade surface stall separation area coverage ratio based on aerodynamic profile information of the target blade comprises:
and determining a reference wind speed, and establishing a relation curve of the power loss coefficient of the target blade and the coverage ratio of the stall separation area on the surface of the blade at the reference wind speed based on the aerodynamic profile information of the target blade.
3. The method of claim 1, wherein the obtaining each monitoring point of the three-dimensional surface stall separation of the target blade based on the relationship curve comprises:
and based on the relation curve, acquiring blade spanwise coordinates of the coverage points of the separation areas corresponding to the power loss thresholds of the target blade under different stall degrees, and determining the coverage points of the separation areas as monitoring points.
4. A method according to any one of claims 1 to 3, wherein prior to said obtaining each monitoring point of a target blade from stall separation monitoring coordinates, the method comprises:
acquiring the vane spanwise coordinates of each monitoring point of the target vane;
acquiring section wing profiles of each monitoring point at the spreading positions based on the vane spreading coordinates of each monitoring point;
acquiring pressure distribution curves of section wing profiles of all the monitoring points under stall attack angles;
and acquiring chord coordinates of the stall separation area covered to the section airfoil corresponding to each monitoring point according to each pressure distribution curve.
5. The method of claim 4, wherein the obtaining, from each pressure distribution curve, chordwise coordinates of stall separation area coverage to cross-section airfoil for each monitoring point comprises:
According to each pressure distribution curve, the approximate separation starting point position of the leeward surface of the blade corresponding to the section airfoil of each monitoring point and the pressure reference position of the section airfoil are obtained;
and acquiring chord coordinates corresponding to each monitoring point according to the approximate separation starting point position of each monitoring point and the pressure reference position of the section airfoil.
6. The method of claim 5, wherein the obtaining stall separation status for each section airfoil of the target blade based on the stall separation signal for each monitoring point comprises:
obtaining stall condition criterion parameters of the section wing profile of the target blade according to the pressure distribution characteristics of the section wing profile corresponding to each monitoring point;
and obtaining stall separation states of the section wing profiles of the monitoring points of the target blade according to comparison results of the stall separation signals corresponding to the chord direction coordinates of the section wing profiles and the stall state criterion parameters.
7. A method according to any one of claims 1-3, wherein said obtaining a stall condition and a stall degree of said target blade based on stall separation conditions of said respective differently spanned position cross-sectional airfoils comprises:
Acquiring the coverage range of a surface stall separation area of the target blade based on stall separation states of each section airfoil;
and obtaining the stall state and the stall degree of the target blade according to the coverage range of the surface stall separation area of the target blade.
8. A method according to any one of claims 1-3, wherein the method further comprises:
selecting abnormal stall monitoring points from the monitoring points; the abnormal stall monitoring point is a monitoring point close to the tip position of the target blade;
and when the section airfoil profile of the abnormal stall monitoring point is subjected to stall separation, carrying out protection control operation on the target blade.
9. A stall condition monitoring system, the system comprising: a piezoelectric sensor and a data acquisition processing unit; the piezoelectric sensors are arranged at all monitoring points;
the data acquisition processing unit is used for:
acquiring each monitoring point of the target blade according to the stall separation monitoring coordinates; the stall separation monitoring coordinates comprise blade spanwise coordinates and chord wise coordinates;
stall separation signals of all monitoring points are respectively collected through piezoelectric sensors; the stall separation signal comprises at least one of a speed signal and a pressure signal;
Based on stall separation signals of the monitoring points, stall separation states of section wing profiles at different unfolding positions of the target blade are obtained;
acquiring a stall state and a stall degree of the target blade based on stall separation states of the wing profiles with different spreading positions;
the data acquisition processing unit is specifically configured to:
acquiring a relation curve of a power loss coefficient of the target blade and a coverage duty ratio of a stall separation area on the surface of the blade based on aerodynamic profile information of the target blade;
and acquiring each monitoring point of the stall separation of the three-dimensional surface of the target blade based on the relation curve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211548114.0A CN115962101B (en) | 2022-12-05 | 2022-12-05 | Stall state monitoring method and system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211548114.0A CN115962101B (en) | 2022-12-05 | 2022-12-05 | Stall state monitoring method and system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115962101A CN115962101A (en) | 2023-04-14 |
| CN115962101B true CN115962101B (en) | 2024-03-22 |
Family
ID=87354142
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211548114.0A Active CN115962101B (en) | 2022-12-05 | 2022-12-05 | Stall state monitoring method and system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115962101B (en) |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02151599A (en) * | 1988-12-02 | 1990-06-11 | Mitsubishi Heavy Ind Ltd | Stall alarm device using semiconductor pressure sensor |
| JP2001041192A (en) * | 1999-07-26 | 2001-02-13 | Ebara Corp | Stall controller |
| CN101672247A (en) * | 2008-07-22 | 2010-03-17 | 西门子公司 | Method and arrangement to adjust the pitch of wind turbine blades |
| CN101787954A (en) * | 2008-08-26 | 2010-07-28 | 通用电气公司 | Resistive contact sensors for large blade and airfoil pressure and flow separation measurements |
| DE102009050577A1 (en) * | 2009-06-08 | 2010-12-09 | Volker Osterlitz | Numeric control for vertical rotor of wind power plant utilized during aircraft installation, has computer software adjusting slats, flaps, blade angle, pressure point position and devices for influencing profile rotation |
| WO2013097852A1 (en) * | 2011-12-29 | 2013-07-04 | Vestas Wind Systems A/S | Optimisation of power production in a wind turbine at below rated power |
| KR101541738B1 (en) * | 2014-08-29 | 2015-08-05 | 연세대학교 원주산학협력단 | Predection method for aerodynamic characteristics of turbine blade using a post-stall model |
| DE102018127804A1 (en) * | 2018-11-07 | 2020-05-07 | fos4X GmbH | Improvement or optimization of the yield of a wind turbine by detecting a stall |
| CN112283051A (en) * | 2020-12-25 | 2021-01-29 | 浙江中自庆安新能源技术有限公司 | Vibration signal characteristic optimization method and system based on lift line model |
| CN112746929A (en) * | 2019-10-31 | 2021-05-04 | 江苏金风科技有限公司 | Blade stall monitoring method, device, equipment and storage medium |
| CN113464376A (en) * | 2020-03-31 | 2021-10-01 | 北京金风科创风电设备有限公司 | Wind turbine stall identification method and device |
| CN114645824A (en) * | 2020-12-18 | 2022-06-21 | 北京金风科创风电设备有限公司 | Blade stall identification method and device for wind generating set |
| JP2022176821A (en) * | 2021-05-17 | 2022-11-30 | 株式会社日立パワーソリューションズ | Monitoring system and monitoring method |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7896614B2 (en) * | 2009-04-30 | 2011-03-01 | General Electric Company | Wind turbine blade with integrated stall sensor and associated method of detecting stall of a wind turbine blade |
| GB2573513A (en) * | 2018-05-02 | 2019-11-13 | Anakata Wind Power Resources Ltd | Aerofoil tip structure, particularly for a HAWT rotor blade |
-
2022
- 2022-12-05 CN CN202211548114.0A patent/CN115962101B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02151599A (en) * | 1988-12-02 | 1990-06-11 | Mitsubishi Heavy Ind Ltd | Stall alarm device using semiconductor pressure sensor |
| JP2001041192A (en) * | 1999-07-26 | 2001-02-13 | Ebara Corp | Stall controller |
| CN101672247A (en) * | 2008-07-22 | 2010-03-17 | 西门子公司 | Method and arrangement to adjust the pitch of wind turbine blades |
| CN101787954A (en) * | 2008-08-26 | 2010-07-28 | 通用电气公司 | Resistive contact sensors for large blade and airfoil pressure and flow separation measurements |
| DE102009050577A1 (en) * | 2009-06-08 | 2010-12-09 | Volker Osterlitz | Numeric control for vertical rotor of wind power plant utilized during aircraft installation, has computer software adjusting slats, flaps, blade angle, pressure point position and devices for influencing profile rotation |
| WO2013097852A1 (en) * | 2011-12-29 | 2013-07-04 | Vestas Wind Systems A/S | Optimisation of power production in a wind turbine at below rated power |
| KR101541738B1 (en) * | 2014-08-29 | 2015-08-05 | 연세대학교 원주산학협력단 | Predection method for aerodynamic characteristics of turbine blade using a post-stall model |
| DE102018127804A1 (en) * | 2018-11-07 | 2020-05-07 | fos4X GmbH | Improvement or optimization of the yield of a wind turbine by detecting a stall |
| CN112746929A (en) * | 2019-10-31 | 2021-05-04 | 江苏金风科技有限公司 | Blade stall monitoring method, device, equipment and storage medium |
| CN113464376A (en) * | 2020-03-31 | 2021-10-01 | 北京金风科创风电设备有限公司 | Wind turbine stall identification method and device |
| CN114645824A (en) * | 2020-12-18 | 2022-06-21 | 北京金风科创风电设备有限公司 | Blade stall identification method and device for wind generating set |
| CN112283051A (en) * | 2020-12-25 | 2021-01-29 | 浙江中自庆安新能源技术有限公司 | Vibration signal characteristic optimization method and system based on lift line model |
| JP2022176821A (en) * | 2021-05-17 | 2022-11-30 | 株式会社日立パワーソリューションズ | Monitoring system and monitoring method |
Non-Patent Citations (1)
| Title |
|---|
| 水平轴风力机静态失速数值模拟;李佳;胡丹梅;张建平;;华东电力(第07期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115962101A (en) | 2023-04-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10371124B2 (en) | System and method for determining wind farm wake loss | |
| CN105508149B (en) | Fault detection method and device for wind generating set | |
| US20170022974A1 (en) | Operating wind turbines | |
| CN110067708B (en) | Method for identifying yaw wind disharmony by using power curve | |
| CN105134510A (en) | State monitoring and failure diagnosis method for wind generating set variable pitch system | |
| EP1505299A1 (en) | Method for yawing horizontal axis wind turbine | |
| CN108431404B (en) | Method and system for controlling a plurality of wind turbines | |
| Kragh et al. | Rotor speed dependent yaw control of wind turbines based on empirical data | |
| CN107947228B (en) | Stochastic stability analysis method for power system containing wind power based on Markov theory | |
| WO2022048228A1 (en) | Load control method and apparatus for wind turbine generator system | |
| CN111091298B (en) | Wind power plant flow field coupling characteristic evaluation and intelligent grouping method and system | |
| EP3642481B1 (en) | A method for determining wind turbine blade edgewise load recurrence | |
| CN115962101B (en) | Stall state monitoring method and system | |
| CN110023621B (en) | Determining load on wind turbine | |
| CN112610412B (en) | Wind turbine generator blade clearance control method based on load detection | |
| Melani et al. | An experimental and numerical analysis of the dynamic variation of the angle of attack in a vertical-axis wind turbine | |
| CN108204342A (en) | Blade icing identification method and device of wind driven generator | |
| CN109798226B (en) | Wind turbine generator tower load prediction method and system | |
| JP2004060477A (en) | Operation control device for windmill | |
| CN114542402A (en) | Wind power blade fault type online diagnosis method and system based on multi-parameter analysis | |
| EP3406897B1 (en) | System and method for determining wind farm wake loss | |
| CN115807739A (en) | Blade stall determination method and device for wind generating set | |
| Bao et al. | A data-driven approach for identification and compensation of wind turbine inherent yaw misalignment | |
| DK201670502A1 (en) | Wind turbine and a method of operating a wind turbine | |
| CN112283051A (en) | Vibration signal characteristic optimization method and system based on lift line model |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |