• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Esillä olevan keksinnön erään esimerkkinäkökulman mukaisesti esitellään anturi (1) käsittäen vähintään yhden tuen (2) konfiguroituna kytkettäväksi kappaleen (3) pintaan (9) tuen (2) ensimmäisestä päästä (4), rakenteen (5) yhdistettynä mainitun vähintään yhden tuen (2) toiseen päähän (6), joukon koloja (7) sijoitettuna pitkin rakennetta (5) sekä joukon kuituoptisia paineantureita (8), missä yksi kuituoptinen paineanturi (8) on järjestetty kunkin kolon (7) sisään ja missä anturi (1) on konfiguroitu siten, että ainakin osa kuituoptisista paineantureista (8) on järjestetty eri etäisyyksille kappaleen (3) pinnasta (9).
    公开号:FI20205516A1
    申请号:FI20205516
    申请日:2020-05-20
    公开日:2021-06-15
    发明作者:Spencer Jennifer Carreiro；Raul Prieto
    申请人:Teknologian Tutkimuskeskus Vtt Oy；
    IPC主号:
    专利说明:

    [0001] [0001] The present invention relates to a sensor. In particular, certain embodiments of the present invention relate to a flow sensor.
    [0002] [0002] Further, the present invention relates to an arrangement comprising at least a first sensor and a second sensor and a blade, for example a wind turbine blade.
    [0003] [0003] Yet further, the present invention relates to a use of a sensor.
    [0004] [0004] Furthermore, the present invention relates to a method of estimating an angle of attack.
    [0005] [0005] Additionally, the present invention relates to a computer readable memory.BACKGROUND
    [0006] [0006] In the operation of wind turbine blades, it is advantageous to reduce the fluctuation of the load generated by the wind acting on the wind turbine blades. In order to reduce said fluctuation, known applications include measurement of blade root strains in o the structure, and subseguently adjust the incidence of the blades in order to control said
    [0008] [0008] In view of the foregoing, it would be beneficial to provide a sensor for estimating an angle of attack of a wind turbine blade at a specific radial position in real time. The sensor should not be susceptible to lightning strike. The sensor should be capable of being manufactured on an industrial scale.
    [0011] [0011] Various embodiments of the first aspect may comprise at least one feature from the following bulleted list: e the structure is configured such that at least some of the cavities are arranged at different distances from the surface of the object e the sensor is configured to measure a stagnation pressure of an incident air flow at different distances from the surface of the object e the structure is V-shaped, U-shaped, curved or arched e at least a section of the structure is in the form of an aerodynamic profile, an airfoil or a NACA airfoil e at least some of the cavities extend through a leading edge of the structure in the form of an aerodynamic profile, an airfoil or a NACA airfoil e at least a section of the at least one strut is in the form of an aerodynamic profile, an airfoil or a NACA airfoil e the structure is shaped symmetrically e the second end of the at least one strut is connected to a centre of the structure e the sensor further comprises a microprocessor e the sensor comprises a transmitter configured to wirelessly transmit data to a node e the cavity comprises at least one separating wall e the number of cavities on a first side of the at least one strut is different than the number of cavities on a second side of the at least one strut e the sensor comprises two or more struts o [0012] According to a second aspect of the present invention, there is provided an O arrangement comprising at least a first sensor and a second sensor according to any one of ro 25 — claims 1-9, at least one blade, wherein the first sensor is coupled to a pressure side of the S at least one blade and the second sensor is coupled to a suction side of the at least one z blade. a © [0013] Various embodiments of the second aspect may comprise at least one feature 3 from the following bulleted list:
    [0015] [0015] According to a fourth aspect of the present invention, there is provided a method for estimating an angle of attack of at least one blade, the method comprising — providing a first sensor according to any one of claims 1 — 9 on a pressure side surface of a blade, providing a second sensor according to any one of claims 1 — 9 on a suction side surface of the blade, and estimating an angle of attack of the blade based on an angle of N attack estimator.
    [0018] [0018] Various embodiments of the fifth aspect may comprise at least one feature — from the following bulleted list: e calculate a first height HPS above the pressure side surface of the wind turbine blade and a second height HSS above the suction side surface of the wind turbine blade, where the total pressure is below a threshold value e estimate an angle of attack of the wind turbine blade based on a ratio HSS / (HSS+HPS) o e estimate an angle of attack based on pattern recognition applied to pressure O readings of the first sensor and the second sensor
    [0019] [0019] Considerable advantages are obtained by means of certain embodiments of the present invention. A sensor system and a method for estimating an angle of attack are provided. According to certain embodiments of the present invention, an angle of attack of a wind turbine blade at a specific radial station can be estimated. Estimation of the angle of attack takes place in real time. Having reliable information on the aerodynamics affecting the rotor enables the deployment of more advanced wind turbine control, reducing fatigue loads and noise, reducing weight and material costs, and increasing efficiency and energy yield. The sensor system, which measures the wind aerodynamic flow condition, which generates the aerodynamic load directly at blade outboard locations, represents a significant improvement over a blade root measurement. Knowing the angle of attack and sensing the flow affecting the blade in the outer part of the blade has the advantage of allowing faster reaction to wind variation, as compared to current state of the art blade root measurement sensors. Thus, the angle of attack sensor allows improved control of a wind turbine. Advantageously, the angle of attack is estimated without the need of knowing the upstream wind speed relative to the airfoil to within an accuracy of better than +/- 0.5 degrees.
    [0020] [0020] Advantageously, the magnitude of surface contamination due to roughness, erosion, bugs, debris or icing can be further found from the total pressure readings using the ratio HSS / (HSS+HPS) and the magnitude HSS+HPS. Alternatively, pattern recognition with neural networks may also be used for estimating the magnitude of surface contamination.
    [0021] [0021] The system further relies on a reliable and robust fibre-optic sensor system. Fibre-optic based sensors are not affected by lightning strike, which is common on wind turbines.O
    [0024] [0024] FIGURE 3 illustrates a schematic front view of a detail of a sensor in accordance with at least some embodiments of the present invention,
    [0025] [0025] FIGURE 4 illustrates a schematic front view of another detail of a sensor in accordance with at least some embodiments of the present invention,
    [0026] [0026] FIGURE 5 illustrates a schematic perspective view of an arrangement in accordance with at least some embodiments of the present invention, and
    [0027] [0027] FIGURE 6 illustrates a schematic front view of another arrangement in accordance with at least some embodiments of the present invention.EMBODIMENTS
    [0028] [0028] In FIGURE 1, a schematic perspective view of a sensor 1 in accordance with — at least some embodiments of the present invention is illustrated. The sensor 1 comprises a strut 2 configured to be coupled to a surface 9 of an object 3 at a first end 4 of the strut 2. The strut 2 may be in the form of a profile or in the form of a NACA airfoil, for instance. The object 3 may be, for example, a blade of a wind turbine.
    [0029] [0029] Further, the sensor 1 comprises a structure 5 connected to a second end 6 of — the strut 2. The structure 5 is typically V-shaped, U shaped, curved or arched. Typically, at least a section of the structure 5 is in the form of a profile or in the form of a NACA airfoil. The structure 5 may be, for example, shaped symmetrically and the strut 2 may be connected at its second end 6 to a centre of the structure 5. A plurality of cavities 7 are positioned along the structure 5. Typically, at least some of the cavities 7 extend through a leading edge 10 of the structure 5 in the form of an aerodynamic profile, airfoil or a NACA airfoil. Of course, also two or more struts 2 may be provided, wherein each strut 2 is N connected at its second end 6 to the structure 5. NACA airfoils are commonly known and 3 have been widely studied by the National Advisory Committee for Aeronautics. N [0030] In other words, the structure 5 typically has a curved or arched wing profile E 25 and an aerodynamically faired strut 2 to reduce the drag. Said form further prevents the O possibility of accidental damage from maintenance crew, ropes, or icing as compared to a 3 protruding pole.
    [0032] [0032] In FIGURE 2, a schematic front view of a sensor 1 in accordance with at least some embodiments of the present invention is illustrated. It can be seen that the strut 2 is connected to the centre of the structure 5 at the second end 6 of the strut 2. The first end 4 of the strut is coupled to a surface 9 of an object. The structure 5 is curved or arched. The structure 5 is further symmetric. The ends of the structure 5 may be, for example, — coupled to the surface 9. A plurality of cavities 7 is provided along a leading edge 10 of the structure 5. Each cavity 7 is arranged at a different distance from the surface 9. The number of cavities can be, but not necessarily, different on both sides of the strut 2.
    [0033] [0033] In FIGURE 3, a schematic front view of a detail of a sensor in accordance with at least some embodiments of the present invention is illustrated. A particular shape of a cavity 7 or chamber is shown. The cavity has been designed using CFD (computer aided fluid design) simulation tools. A fibre-optic pressure transducer 8 is arranged within the cavity 7. Advantageously, the fibre-optic pressure transducer may be placed in the cavity in a wall substantially aligned with the incident flow to minimize any damage from direct impact of particles. The geometry of the cavity 7 is designed taking into account the noise emittance to avoid audible acoustic resonance of the cavity. Advantageously, the cavity 7 may contain one or more separating wall(s) 16 to divide the chamber into two or more volumes such as to create a stable flow structure, and conseguently, provide a stable pressure reading.
    [0039] [0039] The microprocessor is capable of analysing in real time or substantially in real time, i.e. within a delay of less than 0.1 s, the measured signals from the array of fibre- optic pressure transducers 8 in order to map the measured magnitudes to an estimated angle of attack. The height HSS and HPS above the surface of respectively the suction side and the pressure side of the blade 11, where the total pressure falls below a certain threshold, are computed. Without loss of generality the threshold may be set to 99% of the free stream total pressure.
    [0040] [0040] The free stream total pressure is defined as the value of total pressure in a region at a large enough distance from the blade surface so as to not be disturbed by the boundary layer viscous effects.
    [0045] [0045] In FIGURE 6, a schematic front view of another arrangement in accordance with at least some embodiments of the present invention is illustrated. A first sensor 1a and a second sensor (not shown) are coupled to a trailing edge aerodynamic add-on 15, such as a serrated trailing edge, which is connected to a trailing edge 12 of a wind turbine blade 11. According to this document, the blade 11 may incorporate a trailing edge aerodynamic add-on 15. The sensors are arranged such that they are able of measuring a stagnation pressure of an incident air flow at different distances from the pressure side surface 13 and the suction side surface (not shown) of the blade, respectively. The stagnation pressure is measured directly behind the trailing edge 12 of the blade 11.
    [0048] [0048] As used herein, a plurality of items, structural elements, compositional o elements, and/or materials may be presented in a common list for convenience. However, O these lists should be construed as though each member of the list is individually identified ro 25 as a separate and unique member. Thus, no individual member of such list should be S construed as a de facto eguivalent of any other member of the same list solely based on I their presentation in a common group without indications to the contrary. In addition, o various embodiments and example of the present invention may be referred to herein along io with alternatives for the various components thereof. It is understood that such N 30 embodiments, examples, and alternatives are not to be construed as de facto equivalents of N one another, but are to be considered as separate and autonomous representations of the present invention.
    [0049] [0049] Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the description, numerous specific details are provided, such as examples of lengths, widths, shapes, etc., to provide a thorough understanding of embodiments of the invention. One skilled in the relevant art will recognize, however, that the invention can be practiced without one or more of the specific details, or with other methods, components, materials, etc. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention.
    [0050] [0050] While the forgoing examples are illustrative of the principles of the present invention in one or more particular applications, it will be apparent to those of ordinary skill in the art that numerous modifications in form, usage and details of implementation can be made without the exercise of inventive faculty, and without departing from the principles and concepts of the invention. Accordingly, it is not intended that the invention be limited, except as by the claims set forth below.
    — [0051] The verbs “to comprise” and “to include” are used in this document as open limitations that neither exclude nor reguire the existence of also un-recited features. The features recited in depending claims are mutually freely combinable unless otherwise explicitly stated. Furthermore, it is to be understood that the use of "a" or "an", that is, a singular form, throughout this document does not exclude a plurality.
    INDUSTRIAL APPLICABILITY o [0052] At least some embodiments of the present invention find industrial
    N S application in estimating an angle of attack of a wind turbine blade.
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    REFERENCE SIGNS LIST 1, 1a, 1b sensor 2 strut 3 object 4 first end 5 structure 6 second end 7 cavity 8 fibre-optic pressure transducer 9 surface 10 leading edge of structure 11 blade 12 trailing edge of blade 13 pressure side surface 14 suction side surface 15 trailing edge aerodynamic add-on N 16 separating wallN
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    CITATION LIST Patent Literature WO 2019/129337 Al US 2018/0335015 Al US 7445431 B2 US 2014/0356165 Al US 2010/0021296 A1 US 8397564 B2 US 8712703 B3 US 9753050 B2 US 8915709 B2 Non Patent LiteratureO
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    权利要求:
    Claims (15)
    [1] 1. A sensor (1) comprising: — at least one strut (2) configured to be coupled to a surface (9) of an object (3) at a first end (4) of the strut (2), — a structure (5) connected to a second end (6) of the at least one strut (2), — a plurality of cavities (7) positioned along the structure (5), and — a plurality of fibre-optic pressure transducers (8), wherein a single fibre-optic pressure transducer (8) is arranged within each of the cavities (7), — and wherein the sensor (1) is configured such that at least some of the fibre-optic pressure transducers (8) are arranged at different distances from the surface (9) of the object (3).
    [2] 2. The sensor (1) according to claim 1, wherein the structure (5) is configured such that at least some of the cavities (7) are arranged at different distances from the surface (9) of the object (3).
    [3] 3. The sensor (1) according to claim 1 or 2, wherein the sensor (1) is configured to measure — a stagnation pressure of an incident air flow at different distances from the surface (9) of the object (3).
    [4] 4. The sensor (1) according to any one of claims 1-3, wherein the structure (5) is V- o shaped, U shaped, curved or arched. o 25 3
    [5] 5. The sensor (1) according to any one of claims 1-4, wherein at least a section of the S structure (5) is in the form of an aerodynamic profile, an airfoil or a NACA airfoil. x a ©
    [6] 6. The sensor (1) according to claim 5, wherein at least some of the cavities (7) extend 2 30 — through a leading edge (10) of the structure (5) in the form of the aerodynamic profile, the O airfoil or the NACA airfoil.
    [7] 7. The sensor (1) according to any one of claims 1-6, wherein at least a section of the at least one strut (2) is in the form of an aerodynamic profile, an airfoil or a NACA airfoil.
    [8] 8. The sensor (1) according to any one of claims 1-7, wherein the sensor (1) further comprises a microprocessor.
    [9] 9. The sensor (1) according to any one of claims 1-8, wherein the second end (6) of the at least one strut (2) is connected to a centre of the structure.
    [10] 10. An arrangement comprising: — at least a first sensor (1a) and a second sensor (1b) according to any one of claims 1-9, and — at least one blade (11), wherein the first sensor (1a) is coupled to a pressure side of the at least one blade (11) and the second sensor (1b) is coupled to a suction side of the at least one blade (11).
    [11] 11. The arrangement according to claim 10, further comprising a microprocessor configured to calculate an angle of attack of the at least one blade (11) based on an angle of attack estimator.
    [12] 12. The arrangement according to claim 11 or 12, wherein the microprocessor is configured to calculate a first height HPS above a pressure side surface (13) of the at least one blade (11) and a second height HSS above a suction side surface (14) of the at least o one blade (11), where the total pressure is below a threshold value, and to estimate an O 25 angle of attack of the at least one blade (11) based on a ratio HSS / (HSS+HPS).
    [13] S o 13. Use of a sensor (1) according to any one of claims 1-9 in connection with a wind z turbine blade (11), an aircraft wing, a wing, a blade or an object. a © O 30 14. A method for estimating an angle of attack of at least one blade, the method ä comprising: — providing a first sensor according to any one of claims 1-9 on a pressure side surface (13) of a blade (11),
    [14] — providing a second sensor according to any one of claims 1-9 on a suction side surface (14) of the blade (11), and — estimating an angle of attack of the blade (11) based on an angle of attack estimator.
    [15] 15. A non-transitory computer readable memory having stored thereon a set of computer implementable instructions capable of causing a computing device, in connection with a wind turbine, at least to: — receive from a first sensor (la) information about a stagnation pressure of an incident air flow at different distances from a pressure side surface (13) of a wind turbine blade (11), — receive from a second sensor (1b) information about a stagnation pressure of an incident air flow at different distances from a suction side surface (14) of the wind turbine blade (11), — estimate an angle of attack of the wind turbine blade (11) based on an angle of attack estimator, and — control a pitch angle of the wind turbine blade (11) based on the estimated angle of attack.
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    同族专利:
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    FI129067B|2021-06-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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