Determining loads using various sensor locations
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F03B-015/06
F03D-007/00
F03D-007/02
F03D-007/04
F03D-001/06
출원번호
US-0837262
(2013-03-15)
등록번호
US-9316205
(2016-04-19)
발명자
/ 주소
Baker, Jonathon P.
Mayda, Edward A.
출원인 / 주소
Frontier Wind, LLC
대리인 / 주소
Banner & Witcoff, Ltd.
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A system and method for pressure based load measurement are provided. The system and method measure at least one pressure differential on an airfoil and determine at least one aerodynamic load associated with the at least one pressure differential. The determined at least one load is used to modify
A system and method for pressure based load measurement are provided. The system and method measure at least one pressure differential on an airfoil and determine at least one aerodynamic load associated with the at least one pressure differential. The determined at least one load is used to modify characteristics of the airfoil to increase efficiency and/or avoid damage. The determined at least one aerodynamic load may be further utilized to balance and/or optimize loads at the airfoil, estimate a load distribution along the airfoil used to derive other metrics about the airfoil, and/or used in a distributed control system to increase efficiency and/or reduce damage to, e.g., one or more wind turbines.
대표청구항▼
1. A method for determining an aerodynamic force associated with an airfoil of an aerodynamic blade, the method comprising: detecting, by an airfoil control device using a pressure sensor, a first pressure at a first pressure location and a second pressure at a second pressure location on the airfoi
1. A method for determining an aerodynamic force associated with an airfoil of an aerodynamic blade, the method comprising: detecting, by an airfoil control device using a pressure sensor, a first pressure at a first pressure location and a second pressure at a second pressure location on the airfoil;determining, by the airfoil control device, a pressure differential between a first pressure location and a second pressure location on an airfoil;determining, by the airfoil control device, at least two of: a rotation speed of the airfoil, an ambient air pressure, an ambient air temperature, and a pitch angle of the airfoil;determining, by the airfoil control device, an aerodynamic force associated with the airfoil based on the pressure differential, and the at least two of: the rotation speed of the airfoil, the ambient air pressure, the ambient air temperature, and the pitch angle of the airfoil; andcontrolling, by the airfoil control device, at least one physical characteristic of the aerodynamic blade based on the determined aerodynamic force. 2. The method of claim 1, wherein the determining the aerodynamic force associated with the airfoil comprises estimating a local dynamic pressure at the airfoil based on the at least two of: the rotation speed of the airfoil, the ambient air pressure, the ambient air temperature, and the pitch angle of the airfoil. 3. The method of claim 2, wherein the estimating the local dynamic pressure at the airfoil comprises estimating a local air speed at the airfoil. 4. The method of claim 3, wherein the estimating the local air speed of the airfoil comprises estimating a wind speed at the airfoil. 5. The method of claim 4, wherein the estimating the wind speed at the airfoil comprises determining whether the pitch angle of the airfoil is greater than a minimum pitch angle. 6. The method of claim 5, wherein, when the pitch angle of the airfoil is not greater than a minimum pitch angle, the estimating the wind speed at the airfoil is performed based on the rotation speed of a rotor. 7. The method of claim 5, wherein, in response to determining the pitch angle of the airfoil is greater than a minimum pitch angle, the estimating the wind speed at the airfoil is based on the pitch angle of the airfoil. 8. The method of claim 1, wherein the modifying the at least one characteristic of the airfoil comprises at least one of: changing the pitch angle of the blade; changing a yaw angle of the blade; deploying at least one air deflector; retracting the at least one air deflector; extending a tip portion of the airfoil; and retracting the tip portion of the airfoil. 9. A wind turbine comprising: a hub;a controller; anda plurality of wind turbine blades connected to and arranged about the hub, wherein at least one wind turbine blade of the plurality of wind turbine blades comprises: a first pressure sensing orifice arranged on a bottom surface of the at least one wind turbine blade; anda second pressure sensing orifice arranged on a top surface of the at least one wind turbine blade, wherein the first pressure sensing orifice and the second pressure sensing orifice are configured to enable the controller to determine an aerodynamic load generated by the at least one wind turbine blade based on a difference in pressure between a location of the first pressure sensing orifice and a location of the second pressure sensing orifice, a rotation speed of the hub, an ambient air pressure, an ambient air temperature, and a pitch angle of the at least one wind turbine blade. 10. The wind turbine of claim 9, wherein the determination of the aerodynamic load of the at least one wind turbine bade includes determining a local dynamic pressure at the at least one wind turbine blade based on the rotation speed of the hub, the ambient air pressure, the ambient air temperature, and the pitch angle of the at least one wind turbine blade. 11. The wind turbine of claim 10, wherein the controller is configured to determine the local dynamic pressure by estimating a wind speed and a local air speed at the at least one wind turbine blade. 12. The wind turbine of claim 11, wherein the controller is configured to determine whether the pitch angle of the at least one wind turbine blade is greater than a minimum pitch angle, and, in response to determining the pitch angle of the at least one wind turbine blade is not greater than the minimum pitch angle, estimate the wind speed of the at least one wind turbine blade using the rotation speed of the hub. 13. The wind turbine of claim 11, wherein the controller determines whether the pitch angle of the at least one wind turbine blade is greater than a minimum pitch angle, and, in response to determining the pitch angle of the at least one wind turbine blade is greater than the minimum pitch angle, estimate the wind speed of the at least one wind turbine blade using the pitch angle of the at least one wind turbine blade. 14. A method for relating a pressure differential to an aerodynamic force at an airfoil of a turbine blade, the method comprising: determining, by a wind turbine blade controller using at least one pressure sensor, a local air pressure at a surface of the airfoil of the turbine blade;determining, by the wind turbine blade controller, an ambient air pressure away from the airfoil's surface;determining, by the wind turbine blade controller, a pressure differential, wherein the pressure differential is a difference between the determined local air pressure and the determined ambient air pressure;determining, by the wind turbine blade controller using at least one sensor other than the pressure sensor, an aerodynamic force associated with the airfoil; andgenerating and storing, by the wind turbine blade controller, a relationship between the aerodynamic force and the pressure differential. 15. The method of claim 14, wherein the determining the relationship between the aerodynamic force and the pressure differential comprises: determining a pressure differential coefficient;determining an aerodynamic force coefficient; andderiving a relationship between the pressure differential coefficient and the aerodynamic force coefficient. 16. The method of claim 15, wherein the deriving the relationship between the pressure differential coefficient and the aerodynamic force coefficient comprises determining a linear relationship between the pressure differential coefficient and the aerodynamic force coefficient. 17. The method of claim 15, wherein the deriving the relationship between the pressure differential coefficient and the aerodynamic force coefficient comprises determining a quadratic relationship between the pressure differential coefficient and the aerodynamic force coefficient. 18. The method of claim 15, wherein the determining the pressure differential coefficient and the determining the aerodynamic force coefficient comprises determining a dynamic pressure at the airfoil. 19. The method of claim 18, wherein the pressure differential coefficient is the difference of the local air pressure and the ambient air pressure divided by the dynamic pressure, and wherein the aerodynamic force coefficient is the aerodynamic force divided by the product of the dynamic pressure and the nominal area on which the aerodynamic force is acting.
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이 특허에 인용된 특허 (4)
Frantz, James B., Apparatus and method for determining information for aircraft.
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