A method for arranging an icing monitoring sensor on a wind turbine blade

Abstract

This invention relates to the field of wind power generation, and more particularly to a method for arranging sensors for monitoring icing on wind turbine blades. First, for a three-dimensional model of the blade, a sampling section is selected for two-dimensional icing simulation calculations, which reduces the workload and simulation time to a certain extent. A functional relationship between the distance from the current section to the reference plane and the fastest time for icing (x mm) on the outer surface of the section is constructed using multiple spline interpolation. Based on this functional relationship, a new section is selected as the sensor installation section. Different sensor arrangement strategies are implemented according to the parity of the section number. This invention's method for arranging sensors for monitoring icing on wind turbine blades can accurately and effectively monitor blade icing in a short time, enabling rapid response of the de-icing system. Simultaneously, it can control the number of icing sensors on the blade, reducing the impact of the sensors themselves on the blade's aerodynamic performance and structure.

Description

Technical Field

[0001] This invention relates to the field of wind power generation, specifically to a method for arranging sensors to monitor icing on wind turbine blades. Background Technology

[0002] In winter, wind farms in southern my country commonly experience blade icing. When widespread extreme cold weather occurs, wind turbines in areas south of the Yangtze River and in the Yunnan-Guizhou region, where humidity is consistently high, are highly susceptible to icing. This icing severely impacts the safe operation of wind turbines. For the blades, icing first alters their aerodynamic shape, reducing the rotor's ability to capture wind energy and lowering the turbine's power generation efficiency. Second, icing increases the overall mass of the blades, causing periodic torque fluctuations of varying frequencies and amplitudes in the rotor, depending on the degree of icing on each blade, leading to a decrease in the lifespan of the rotor shaft and the turbine. Furthermore, large volumes of icing pose a serious threat to surrounding personnel and equipment; the consequences of icing detachment could be disastrous.

[0003] To reduce the impact of icing on wind turbines, icing monitoring sensors and de-icing devices such as air-heating, electric-heating, or vibration-based devices need to be installed on the blades and nacelles. When the icing monitoring sensor detects icing, it promptly sends an early warning signal to the de-icing system inside the turbine. The processor then generates a de-icing signal, driving the de-icing system to operate normally and remove the ice from the outer surface of the blades and around the nacelle through heating, vibration, and other methods. Therefore, the proper placement of icing sensors is crucial for detecting icing conditions and for the subsequent de-icing process. Summary of the Invention

[0004] To address the problems existing in the prior art, this invention provides a method for arranging wind turbine blade icing monitoring sensors. This method can determine the layout and position of the blade icing sensors according to local conditions, which is of great significance for achieving short-term de-icing of blades.

[0005] This invention is achieved through the following technical solution:

[0006] A method for arranging sensors to monitor icing on wind turbine blades includes the following steps:

[0007] S1, Establish a two-dimensional model of the blade element section. A a ;

[0008] S2, Two-dimensional model of leaf element cross section A a The outer surface was simulated for icing scenarios, and then the simulation parameters were tuned to obtain simulation data.

[0009] S3, based on simulation data, simulates the natural icing process of the blades without a de-icing device, and statistically analyzes the cross-sectional models of each blade element. A a The time required for ice to accumulate to X mm at various points on the outer surface was determined, and the curves showing the time required for the maximum ice thickness to reach X mm at each leaf element section were obtained as a function of the distance from the reference surface. L ;

[0010] S4, Take a new set of blade cross-sections C i and in the curve L Based on the blade cross section C i Location to obtain cross section C i Distance to the leaf base L i and cross-section C i The fastest time when ice accumulates in X mm, where, i It is a constant;

[0011] S5, according to the cross section C i Distance to the leaf base L i and cross section C i The arrangement of blade icing detection sensors is determined based on the fastest time when icing reaches X mm.

[0012] Preferably, in S1, the leaf element cross-section two-dimensional model A a The method for obtaining the blade is as follows: First, a three-dimensional outer surface model of the blade is established, and several blade cross-sections are cut out; then, for each blade cross-section, a two-dimensional model of the leaf element cross-section is established. A a .

[0013] Preferably, the method for cutting the blade cross section is as follows: taking the flange connection surface between the blade and the hub as the reference plane, N blade cross sections are cut along the blade extension direction, and the blade cross sections are parallel to the reference plane and perpendicular to the blade twist angle baseline.

[0014] Preferably, in S2, the origin is the intersection of the twist angle baseline and each blade section, and the circumferential rotation direction of the airfoil is taken as the reference point. X The negative axis direction is the direction in which the impeller faces the wind. Y In the negative axial direction, establish a two-dimensional model of the blade cross section. A a .

[0015] Preferably, a two-dimensional model of the blade cross section A a Satisfy the equation:

[0016] ,( a =1,2,...,N)

[0017] In the formula, f a ( x , y ) represents the equation of the outer contour curve of the two-dimensional cross-section of the blade. x , y These are the x and y coordinates of the points that satisfy the outer contour curve. a This indicates the location of the two-dimensional model of the blade cross section.

[0018] Preferably, in S3, the method for obtaining curve L is as follows:

[0019] S301, based on simulation data, simulates the natural icing process of the blades without a de-icing device, and statistically analyzes the cross-sectional models of each blade element. A a The time required for ice to form at various points on the outer surface to reach X mm was calculated, and then the time required for ice to form to X mm was added to the coordinate system of the leaf element section model. Z Plot the space function curves related to each blade cross-section along the axis. T a ;

[0020] S302, take the space function curve T a minimum value on t a As the location where icing first occurs at the current cross-section, i.e., the velocity point, the velocity point of each cross-section is denoted as ( r a , t a );

[0021] S303, the spline interpolation method is used to fit the velocity points of each cross section ( r a , t a The curve L, which shows the time taken for the maximum ice thickness of the cross section to reach X mm, varies with the distance from the reference surface.

[0022] Preferably, in S301, the simulation data is compared with the wind tunnel experimental data. When icing of thickness X mm occurs, if the overlap rate between the actual icing cross-sectional area of ​​the blade and the area calculated by the simulation reaches 80%, the error is considered acceptable, and subsequent steps are performed. If the error is unacceptable, the icing scenario simulation is repeated until simulation data with acceptable error is obtained.

[0023] Preferably, in S301, the space function T a Satisfy the equation:

[0024] ,( a =1,2,...,N)

[0025] In the formula ，T a For a spatial function, its direction XOY The projection of a surface is f a Equation of outer contour curve; t for Z Axial quantity, representing the time (X mm) at which icing first occurs on the blade at the corresponding cross-section; A a For the interface, a two-dimensional model x , y To satisfy the x and y coordinates of the position points on the outer contour curve.

[0026] Preferably, cross-section C i Distance to the leaf base L i The calculation reference expression is:

[0027]

[0028] in, L min for L Minimum value on the curve; L max for L The maximum value on the curve.

[0029] Preferably, when i When the value is odd, an icing sensor is placed at the point of maximum icing velocity (X mm) on that cross section; when... i When the number is even, an icing sensor is placed at a position corresponding to 1.5 to 2 times the fastest icing time (X mm) of the cross section.

[0030] Compared with the prior art, the present invention has the following beneficial effects:

[0031] The present invention provides a method for arranging sensors to monitor icing on wind turbine blades, which can accurately and effectively monitor the icing status of blades in a short time, enabling rapid response of the de-icing system for de-icing blades. At the same time, it can control the number of icing sensors on the blades, reducing the impact of the sensors themselves on the aerodynamic performance and structure of the blades.

[0032] This invention discloses a sensor arrangement method for monitoring icing on wind turbine blades. This method enables gradient monitoring of icing conditions at locations prone to icing on the blades. The staggered sensor layout used also reduces sensor installation costs without compromising monitoring accuracy. Furthermore, the limited number of sensors helps maintain good aerodynamic performance of the blades to some extent.

[0033] This invention enables the icing monitoring sensor to accurately and effectively monitor the icing status of blades in a short time, achieving a rapid response of the de-icing system for de-icing blades. At the same time, it can control the number of icing sensors on the blades, reducing the impact of the sensors themselves on the aerodynamic performance and structure of the blades.

[0034] First, for the three-dimensional model of the blade, a fixed sampling section is selected for two-dimensional icing simulation calculation, which reduces the simulation workload and time to a certain extent. The time taken for icing in X mm, obtained from the simulation, represents the fastest icing rate of the current section. A functional relationship between the distance from the current section to the reference plane and the fastest time for icing in X mm on the outer surface of the section is constructed using multiple spline interpolation. Based on this functional relationship, a new section is selected as the sensor installation section. For the newly selected section, different sensor placement strategies are implemented according to the parity of the section number: for sections with odd numbers, icing sensors are placed at the location of the fastest icing in X mm; for sections with even numbers, icing sensors are placed at locations corresponding to 1.5 to 2 times the fastest time for icing in X mm.

[0035] This invention enables gradient monitoring of blade icing at locations prone to icing. The staggered sensor layout reduces sensor installation costs without compromising monitoring accuracy. Furthermore, the limited number of sensors helps maintain good aerodynamic performance of the blades. Attached Figure Description

[0036] Figure 1 A flowchart illustrating the overall process of setting up an icing sensor.

[0037] Figure 2 This is a schematic diagram showing the location of the cross-section taken for the blade.

[0038] Figure 3 This is a two-dimensional leaf element cross-sectional model diagram.

[0039] Figure 4 The curve showing the time required for X mm of icing to form on the outer surface of the blade as a function of the distance from the cross section to the reference plane.

[0040] Figure 5 This is the arrangement of the icing sensor according to the present invention.

[0041] In the diagram, 1. Flange connection surface between blade and hub; 2. Blade twist angle baseline; 3. 0.1R blade section; 4. 0.2R blade section; 5. 0.3R blade section; 6. 0.4R blade section; 7. 0.5R blade section; 8. 0.6R blade section; 9. 0.7R blade section; 10. 0.8R blade section; 11. 0.9R blade section; 12. 0.95R blade section; 13. Sensor arrangement section C1; 14. Sensor arrangement section C2; 15. Sensor arrangement section C3; 16. Sensor arrangement section C4; 17. Sensor arrangement section C5; 18. Sensor arrangement section C6; 19. Sensor arrangement section C7; 20. Sensor placement point for maximum speed with icing in mm; 21. Sensor placement point for maximum speed with icing in mm on the leeward side (1.5~2 times the maximum time); 22. Sensor placement point for maximum speed with icing in mm on the windward side (1.5~2 times the maximum time). Detailed Implementation

[0042] The present invention will be further described in detail below with reference to specific embodiments. These descriptions are for explanation purposes only and are not intended to limit the scope of the invention.

[0043] This invention discloses a method for arranging sensors to monitor icing on wind turbine blades, referring to... Figure 1 This includes the following steps:

[0044] S1, Establish a three-dimensional outer surface model of the blade and cut out several blade sections;

[0045] The method for selecting the blade cross-section is as follows: taking the flange connection surface 1 between the blade and the hub as the reference plane, N blade cross-sections are selected along the blade extension direction. The blade cross-sections are parallel to the reference plane and perpendicular to the blade twist baseline 2. Among them, the N blade cross-sections include N-1 equidistant cross-sections and 1 detail cross-section. The distance between two adjacent equidistant cross-sections is d, and the distance between the detail cross-section and the equidistant cross-section is d / 2.

[0046] For each blade cross section, a two-dimensional model of the blade element cross section is established. A a Taking the intersection of the torsion baseline 2 and each blade section as the origin, and the circumferential rotation direction of the airfoil as the reference point... X The negative axis direction is the direction in which the impeller faces the wind. Y In the negative axial direction, establish a two-dimensional model of the blade cross section. A a , refer to Figure 3 Satisfies the equation:

[0047] (a=1,2,...,10)

[0048] In the formula, f a (x , y ) represents the equation of the outer contour curve of the two-dimensional cross-section of the blade. x , y These are the x and y coordinates of the points that satisfy the outer contour curve. a This indicates the location of the two-dimensional model of the blade cross section.

[0049] S3, based on simulation data, simulates the natural icing process of the blades without a de-icing device, and statistically analyzes the cross-sectional models of each blade element. A a The time required for ice to accumulate to X mm at various points on the outer surface was determined, and the curves showing the time required for the maximum ice thickness to reach X mm at each leaf element section were obtained as a function of the distance from the reference surface. L The specific steps are as follows:

[0050] S301, based on the characteristics of the wind turbine's location, simulation software was used to simulate icing scenarios on a two-dimensional model of the blade. Then, based on wind tunnel experimental data, the simulation software's scenario parameters were tuned until the experimental data and software simulation data were within the allowable error range. (This refers to the two-dimensional model of the blade element section.) A a The outer surface of the blade is simulated for icing scenarios. Then, the simulation parameters are tuned and simulation data is obtained. The simulation data is compared with the wind tunnel experimental data. When icing of X mm thickness occurs, if the overlap rate between the actual icing cross-sectional area of ​​the blade and the area calculated by the simulation reaches 80%, the error is considered acceptable and subsequent steps are performed. If the error is unacceptable, the icing scenario simulation is repeated until simulation data with acceptable error is obtained.

[0051] S302, based on simulation data, simulates the natural icing process of the blades without a de-icing device, and statistically analyzes the cross-sectional models of each blade element. A a The time required for ice to accumulate to 2 mm at various points on the outer surface was calculated, and then the time required for ice to accumulate to X mm was added to the coordinate system of the leaf element section model. Z Plot the space function curves related to each blade cross-section along the axis. T a Satisfies the equation:

[0052] (a=1,2,...,10)

[0053] In the formula, T a For a spatial function, its direction XOY The projection of a surface is f a Equation of outer contour curve; t for ZAxial quantity, representing the time (X mm) at which icing first occurs on the blade at the corresponding cross-section; A a For the interface, a two-dimensional model x , y To satisfy the x and y coordinates of the position points on the outer contour curve.

[0054] S303, take the space function curve T a minimum value on t a As the location where icing first occurs at the current cross-section, i.e., the velocity point, the velocity point of each cross-section is denoted as ( r a , t a The spline interpolation method was used to fit the velocity points of each cross section. r a , t a The curve showing the time taken for the maximum ice thickness of the cross section to reach X mm as a function of the distance from the reference surface was obtained. L ,curve L It can visually reflect the rate of ice formation on leaves; that is, with (r a ,t a Using the boundary conditions for cubic spline interpolation, construct a cubic spline curve L;

[0055] S4, see reference Figure 4 Take a new set of blade cross-sections C i and in the curve L Based on the blade cross section C i Location to obtain cross section C i Distance to the leaf base L i and cross-section C i The fastest time when ice accumulates in X mm, where, i It is a constant;

[0056] Among them, the blade cross section C i Distance to the leaf base L i The calculation reference expression is:

[0057]

[0058] in, L min for L Minimum value on the curve; Lmax for L The maximum value on the curve.

[0059] S5, according to the cross section C i Distance to the leaf base L i The arrangement of sensors for detecting blade icing at the fastest possible time. i When it is an odd number, in this C i An icing sensor is placed at the point of maximum icing velocity (X mm) on the cross-section; when i When the number is even, an icing sensor is placed at a position corresponding to 1.5 to 2 times the fastest icing time (X mm) of the cross section.

[0060] in, C i The location of the highest icing velocity (X mm) at the cross section was determined by the aforementioned two-dimensional simulation, and the simulation environment parameters were based on... A a The simulation parameters were obtained by linearizing them.

[0061] Example

[0062] First, a three-dimensional outer surface model of the blade is created using software. Then, based on the positional relationships defined in the invention, a set of sampling surfaces consisting of 10 cross-sections is selected (e.g., ...). Figure 2 ), Figure 2 In the diagram, 1 represents the flange connection surface between the blade and the hub, 2 represents the blade torsion baseline, 3 represents the 0.1R blade section, 4 represents the 0.2R blade section, 5 represents the 0.3R blade section, 6 represents the 0.4R blade section, 7 represents the 0.5R blade section, 8 represents the 0.6R blade section, 9 represents the 0.7R blade section, 10 represents the 0.8R blade section, 11 represents the 0.9R blade section, and 12 represents the 0.95R blade section. The distance from the reference plane to the blade tip is defined as... R The distance from the 10 blade sections to the reference plane is... r a The values ​​are 0.1R, 0.2R, 0.3R, 0.4R, 0.5R, 0.6R, 0.7R, 0.8R, 0.9R, and 0.95R, respectively.

[0063] A two-dimensional model of the blade element cross-section was created for the sampling surface. Then, simulation software was used to simulate the icing scenario on the two-dimensional model. The simulation data was compared with actual wind tunnel experimental data, and the model simulation parameters were adjusted until the error was within acceptable limits. The time for icing to 2mm at each point on the outer surface of the blade element cross-section was used as the Z-axis variable to construct a spatial function curve T. a Take the minimum time t of the curve. a , as the fastest time for icing to reach 2 mm at the current cross-section. (r) a,t a Using cubic spline interpolation boundary conditions, construct a cubic spline curve L, and then select 7 points on the L curve according to the following formula:

[0064]

[0065] These 7 points redefine a set of blade cross sections, i.e., the abscissas of L1~L7 are recalculated to form a new set of cross sections C1~C7 (13-19). The corresponding positions of cross sections C1~C7 (13-19) on the L curve are as follows: Figure 4 As shown. Figure 4 In the diagram, 13 is the sensor arrangement section C1, 14 is the sensor arrangement section C2, 15 is the sensor arrangement section C3, 16 is the sensor arrangement section C4, 17 is the sensor arrangement section C5, 18 is the sensor arrangement section C6, and 19 is the sensor arrangement section C7.

[0066] Reference Figure 5 Then, based on the selected section number i The parity of the sensors determines the choice of different sensor arrangement methods. Specifically, when... i When the number is odd, install an icing sensor at the point where icing reaches its fastest speed of 2 mm on that cross section; when... i When the number is even, install an icing sensor at the position corresponding to 1.5 to 2 times the fastest time for icing to reach 2 mm on that cross-section. Figure 5 Point 20 is the sensor placement point for the fastest icing time of 2 mm on the leeward side, point 21 is the sensor placement point for the fastest icing time of 2 mm on the leeward side, and point 22 is the sensor placement point for the fastest icing time of 2 mm on the windward side, which is 1.5 to 2 times the sensor placement point for the fastest icing time of 2 mm on the windward side.

[0067] The above description is merely a preferred embodiment of the present invention and is not intended to limit the technical solution of the present invention in any way. Those skilled in the art should understand that, without departing from the spirit and principles of the present invention, the technical solution can be modified and replaced in several simple ways, and these modifications and replacements are all within the scope of protection covered by the claims.

Claims

1. A method for arranging sensors to monitor icing on wind turbine blades, characterized in that, Includes the following steps: S1, Establish a two-dimensional model of the blade element section. A a ; S2, Two-dimensional model of leaf element cross section A a The outer surface was simulated for icing scenarios, and then the simulation parameters were tuned to obtain simulation data. S3, based on simulation data, simulates the natural icing process of the blades without a de-icing device, and statistically analyzes the cross-sectional models of each blade element. A a The time required for ice to accumulate to X mm at various points on the outer surface was determined, and the curves showing the time required for the maximum ice thickness to reach X mm at each leaf element section were obtained as a function of the distance from the reference surface. L ; The method for obtaining curve L is as follows: S301, based on simulation data, simulates the natural icing process of the blades without a de-icing device, and statistically analyzes the cross-sectional models of each blade element. A a The time required for ice to form at various points on the outer surface to reach X mm was calculated, and then the time required for ice to form to X mm was added to the coordinate system of the leaf element section model. Z Plot the space function curves related to each blade cross-section along the axis. T a ; S302, take the space function curve T a minimum value on t a As the location where icing first occurs at the current cross-section, i.e., the velocity point, the velocity point of each cross-section is denoted as ( r a , t a ); S303, the spline interpolation method is used to fit the velocity points of each cross section ( r a , t a The curve L showing the time taken for the maximum ice thickness of the cross section to reach X mm as a function of the distance from the reference surface was obtained. S4, Take a new set of blade cross-sections C i and in the curve L Based on the blade cross section C i Location to obtain cross section C i Distance to the leaf base L i and cross-section C i The fastest time when ice accumulates in X mm, where, i It is a constant; S5, according to the cross section C i Distance to the leaf base L i and cross section C i The arrangement of blade icing detection sensors is determined based on the fastest time when icing reaches X mm.

2. The method for arranging wind turbine blade icing monitoring sensors according to claim 1, characterized in that, In S1, the two-dimensional model of the leaf element section. A a The method for obtaining the blade is as follows: First, a three-dimensional outer surface model of the blade is established, and several blade cross-sections are cut out; then, for each blade cross-section, a two-dimensional model of the leaf element cross-section is established. A a .

3. The method for arranging wind turbine blade icing monitoring sensors according to claim 2, characterized in that, The method for cutting the blade section is as follows: taking the flange connection surface between the blade and the hub as the reference plane, N blade sections are cut along the blade extension direction. The blade sections are parallel to the reference plane and perpendicular to the blade twist angle baseline.

4. The method for arranging wind turbine blade icing monitoring sensors according to claim 3, characterized in that, In S2, the origin is the intersection of the twist baseline and each blade section, and the circumferential rotation direction of the airfoil is taken as the reference point. X The negative axis direction is the direction in which the impeller faces the wind. Y In the negative axial direction, establish a two-dimensional model of the blade cross section. A a .

5. The method for arranging wind turbine blade icing monitoring sensors according to claim 4, characterized in that, Two-dimensional model of blade cross section A a Satisfy the equation: ,( a =1,2,...,N) In the formula, f a ( x , y ) represents the equation of the outer contour curve of the two-dimensional cross-section of the blade. x , y These are the x and y coordinates of the points that satisfy the outer contour curve. a This indicates the location of the two-dimensional model of the blade cross section.

6. The method for arranging wind turbine blade icing monitoring sensors according to claim 5, characterized in that, In S301, the simulation data is compared with the wind tunnel test data. When icing of thickness X mm occurs, if the actual icing cross-sectional area of ​​the blade coincides with the area calculated by the simulation by 80%, the error is considered acceptable and subsequent steps are performed. If the error is unacceptable, the icing scenario simulation is repeated until simulation data with acceptable error is obtained.

7. The method for arranging wind turbine blade icing monitoring sensors according to claim 5, characterized in that, In S301, space function T a Satisfy the equation: ,( a =1,2,...,N) In the formula ，T a For a spatial function, its direction XOY The projection of a surface is f a Equation of outer contour curve; t for Z Axial quantity, representing the time (X mm) at which icing first occurs on the blade at the corresponding cross-section; A a For the interface, a two-dimensional model x , y To satisfy the x and y coordinates of the position points on the outer contour curve.

8. The method for arranging wind turbine blade icing monitoring sensors according to claim 5, characterized in that, section C i Distance to the leaf base L i The calculation reference expression is: in, L min for L Minimum value on the curve; L max for L The maximum value on the curve.

9. The method for arranging wind turbine blade icing monitoring sensors according to claim 8, characterized in that, when i When the value is odd, an icing sensor is placed at the point of maximum icing velocity (X mm) on that cross section; when... i When the number is even, an icing sensor is placed at a position corresponding to 1.5 to 2 times the fastest icing time (X mm) of the cross section.

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