GB2469516A - Rotor blade with optical strain sensors covered by erosion shield - Google Patents
Rotor blade with optical strain sensors covered by erosion shield Download PDFInfo
- Publication number
- GB2469516A GB2469516A GB0906625A GB0906625A GB2469516A GB 2469516 A GB2469516 A GB 2469516A GB 0906625 A GB0906625 A GB 0906625A GB 0906625 A GB0906625 A GB 0906625A GB 2469516 A GB2469516 A GB 2469516A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor blade
- optical fibre
- blade
- rotor
- sensor
- 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.)
- Withdrawn
Links
- 230000003628 erosive effect Effects 0.000 title claims abstract description 16
- 230000003287 optical effect Effects 0.000 title claims abstract description 7
- 239000013307 optical fiber Substances 0.000 claims abstract description 28
- 238000004519 manufacturing process Methods 0.000 claims abstract description 6
- 230000010355 oscillation Effects 0.000 claims abstract description 5
- 238000000034 method Methods 0.000 claims description 5
- 239000000835 fiber Substances 0.000 abstract description 9
- 238000005259 measurement Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/006—Safety devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/065—Rotors characterised by their construction elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor
- F03D3/06—Rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor
- F03D3/06—Rotors
- F03D3/062—Rotors characterised by their construction elements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/16—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
-
- 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
-
- 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
- Y02E10/74—Wind turbines with rotation axis perpendicular to the wind direction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Combustion & Propulsion (AREA)
- Life Sciences & Earth Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Length Measuring Devices By Optical Means (AREA)
- Optical Transform (AREA)
Abstract
A method of manufacturing a rotor blade 10 comprising the steps of applying at least one optical fibre strain sensor 14 to the leading edge of the rotor blade body 12 and fitting an erosion shield 16 to the leading edge of the rotor blade body 12, over the optical fibre sensor 14. The optical strain sensors 14 may measure the strain in the axial direction of the blade 10, and may be placed at an angle between 30 and 60 degrees to the rotor blade axis, with 45 degrees being the preferred angle. The sensors may comprise Bragg gratings 18 spaced along the length of the fibre 14, and may be positioned at a location which is not a node of oscillation. The blade 10 may be a helicopter rotor blade.
Description
Improved Rotor Blade
Field of the Invention
This invention relates to rotor blades and is application with particular advantage to helicopter rotor blades.
Background to the Invention
Optical fibre strain sensors are known and patent publication WO 2004/0560 17 discloses a method of interrogating multiple fibre Bragg grating strain sensors along a single fibre.
In the system of WO 2004/056017, Bragg gratings are defined in the optical fibre at spaced locations along the optical fibre. When the optical fibre is put under strain, the relative spacing of the planes of each Bragg grating changes and thus the resonant optical wavelength of the grating changes. By determining the resonant wavelength of each grating, a strain measurement can be derived for the location of each grating along the fibre. Optical strain sensors operating on the principle of back scattering which do not require discrete gratings along the fibre are also known.
It is desirable to monitor the loads on rotor blades, especially helicopter rotor blades, for safety reasons and also to monitor the performance of the blade. Advantageously, the loads on rotor blades due to impacts can be monitored and quantified. However, applying sensors to monitor loads to the outside of the rotor blade may affect the aerodynamic properties of the blade and the sensors themselves are exposed to damage from impacts with foreign bodies. Furthermore, the sensors cannot be contained within the blade, as with hollow wind turbine rotor blades, because helicopter blades are of closed section and getting the sensor out is difficult. Whilst it is possible to embed the sensor within the blade, this may change the structural properties of the blade and a blade with an embedded sensor would significanfly increase the recertification cost for the blade.
Furthermore, should the sensor become damaged, the whole blade would need replacing.
Summary of the Invention
Accordingly, the present invention comprises a method of manufacturing a helicopter rotor blade comprising the steps of; applying at least one optical fibre strain sensor to the leading edge of the rotor blade body; and fitting an erosion shield to the leading edge of the rotor blade body, over the optical fibre sensor.
Helicopter rotor blades have sacrificial erosion shields that are externally bonded around the leading edge. The erosion shields extend the life of the blade and are routinely replaced once they have experienced a significant amount of wear. Positioning an optical fibre strain sensor between the blade body and the erosion shield does not interfere with the structural or aerodynamic properties of the blade and also allows easy access to the sensor for maintenance purposes. Should the optical fibre break in two or more places, a new fibre can be fitted by removing the erosion shield and bonding a new fibre to the blade body. Should the optical fibre strain sensor break in just a single position, this can be catered for by terminating both ends of the fibre.
Advantageously, a plurality of optical fibre strain sensors is applied to the length of the blade body. This allows the detection of impact forces and for profiling of the aerodynamic forces along the blade.
Preferably, optical strain sensors are positioned to measure strains in the axial direction of the blade. By positioning a plurality of sensors around the leading edge at a single cross-section, measurements of the axial strain can be made to determine the lift and drag forces on the rotor blade.
Advantageously, one or more optical fibre strain sensors are positioned at an angle of the order of 45 degrees, for example substantially 45 degrees to the rotor blade axis. By positioning a sensor at this angie, the torsion in the blade caii be measured. Other angles for example, 30 degrees to 60 degrees to the rotor blade axis could also be used.
As the rotor blade is impacted, a variety of the natural nodes of oscillation are excited. In a preferred configuration, the optical fibre strain sensors are positioned at locations other than at the nodes of oscillation. By arranging the optical fibre strain sensors away from the nodes of oscillation, it is possible to identify the impact location from analysis of the signals from the sensors. Furthermore, the magnitude of the impact can be identified from the amplitude of the sensor signals.
The invention includes within its scope a helicopter rotor blade comprising a rotor blade body and an erosion shield, wherein at least one optical fibre strain sensor is provided between the rotor body and the erosion shield.
Brief Description of the Drawings
An embodiment of the invention will now be described, by way of example only, and with reference to the accompanying drawings, in which: Figure 1 is an axial cross-sectional view of a helicopter rotor blade in accordance with the present invention; and Figure 2 is a plan view of the helicopter rotor of Figure 1, wherein the erosion shield has been removed.
Detailed Description of Exemplary Embodiments
Figures 1 and 2 show a helicopter rotor blade 10, comprising a rotor blade body 12 and an optical fibre strain sensor 14 attached to the rotor blade body. An erosion shield 16 is bonded to the leading edge of the rotor blade body 12, which protects the optical fibre strain sensor 14 and rotor blade body 12 from damage from impacts with foreign bodies.
The erosion shield 16 can detached from the rotor blade body 12 replaced if necessary.
As shown in Figure 2, the optical fibre strain sensors comprise Bragg gratings 18 spaced along the length of the fibre 14. The optical fibre 14 extends the length of the rotor blade body 12 and a plurality of optical fibres 14 are positioned longitudinally about the leading edge of the rotor blade body 12 to allow measurements of the life, drag and torsion of the rotor Made 10.
Whilst the present invention has been described in relation to helicopter rotor blades, it may also be used in other applications, such as in aircraft propellers.
In summary, a method of manufacturing a helicopter rotor blade comprising the steps of applying at least one optical fibre strain sensor to the leading edge of the rotor blade body and fitting an erosion shield to the leading edge of the rotor blade body, over the optical fibre sensor.
Claims (10)
- Claims 1. A method of manufacturing a rotor blade comprising the steps of; applying at least one optical fibre strain sensor to the leading edge of the rotor blade body; and fitting an erosion shieki to the leading edge of the rotor Made body, over the optical fibre sensor.
- 2. A method according to claim 1, wherein the, or each, optical strain sensor is positioned to measure strain in the axial direction of the blade.
- 3. A method according to claim 1 or claim 2, wherein one or more of the optical fibre strain sensors is or are positioned at an angle of the order of 45 degrees to the rotor blade axis.
- 4. A method according to any preceding claim, wherein the, or each, optical fibre strain sensor is positioned at a location other than at a node of oscillation.
- 5. A method according to any preceding claim, wherein a plurality of optical fibre strain sensors is applied to the length of the blade body.
- 6. A rotor blade body and an erosion shield, wherein at least one optical fibre strain sensor is provided between the rotor body and the erosion shield.
- 7. A method of manufacturing a rotor blade substantially as described herein with reference to and as illustrated in any appropriate combination of the accompanying text and/or drawings.
- 8. A rotor blade substantially as described herein with reference to and as illustrated in any appropriate combination of the accompanying text and/or drawings.
- 9. A method of manufacturing a rotor blade according to any of claims 1 to 6 or claim 8, wherein the blade is a helicopter rotor blade.
- 10. A rotor blade according to claim 6 or claim 8, wherein the rotor blade is a helicopter rotor blade.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0906625A GB2469516A (en) | 2009-04-17 | 2009-04-17 | Rotor blade with optical strain sensors covered by erosion shield |
PCT/GB2010/050638 WO2010119298A1 (en) | 2009-04-17 | 2010-04-19 | Rotor blade |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0906625A GB2469516A (en) | 2009-04-17 | 2009-04-17 | Rotor blade with optical strain sensors covered by erosion shield |
Publications (2)
Publication Number | Publication Date |
---|---|
GB0906625D0 GB0906625D0 (en) | 2009-05-27 |
GB2469516A true GB2469516A (en) | 2010-10-20 |
Family
ID=40750762
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB0906625A Withdrawn GB2469516A (en) | 2009-04-17 | 2009-04-17 | Rotor blade with optical strain sensors covered by erosion shield |
Country Status (2)
Country | Link |
---|---|
GB (1) | GB2469516A (en) |
WO (1) | WO2010119298A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2505736A (en) * | 2013-03-15 | 2014-03-12 | Epsilon Optics Aerospace Ltd | Method of incorporating a coil of optical fibre into a composite structure |
EP2778059A1 (en) * | 2013-03-14 | 2014-09-17 | Bell Helicopter Textron Inc. | Amorphous metal rotor blade abrasion strip |
EP3068994A4 (en) * | 2013-11-15 | 2017-07-19 | United Technologies Corporation | Component with embedded sensor |
EP3485161A4 (en) * | 2016-07-15 | 2020-04-08 | Sikorsky Aircraft Corporation | Rotor blade deflection sensing system |
WO2021234227A1 (en) * | 2020-05-20 | 2021-11-25 | Teknologian Tutkimuskeskus Vtt Oy | Sensor, arrangement, method of estimating an angle of attack, and computer readable memory |
EP3768969A4 (en) * | 2018-03-18 | 2021-12-08 | Udesen Trade | The present invention relates to a device for remedying erosion problems on wind turbine blades |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014081355A1 (en) * | 2012-11-20 | 2014-05-30 | Saab Ab | An erosion protection strip for a leading edge of an airfoil article |
JP6421078B2 (en) | 2015-05-28 | 2018-11-07 | エムエイチアイ ヴェスタス オフショア ウィンド エー/エス | Wind turbine blade and wind power generator, and method for manufacturing or modifying wind turbine blade |
US11441545B2 (en) * | 2020-02-25 | 2022-09-13 | General Electric Company | Tungsten-based erosion-resistant leading edge protection cap for rotor blades |
CN113404652A (en) * | 2021-06-09 | 2021-09-17 | 东方电气集团科学技术研究院有限公司 | Method for monitoring state of blade of wind generating set in severe environment |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2440953A (en) * | 2006-08-18 | 2008-02-20 | Insensys Ltd | Monitoring wind turbine blades |
WO2009068918A1 (en) * | 2007-11-30 | 2009-06-04 | Bae Systems Plc | Improvements relating to temperature monitoring |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA1270802A (en) * | 1985-02-07 | 1990-06-26 | Edward A. Rothman | Prop-fan with improved stability |
US6447254B1 (en) * | 2001-05-18 | 2002-09-10 | Sikorsky Aircraft Corporation | Low dieletric constant erosion resistant material |
EP1520983B1 (en) * | 2001-07-19 | 2017-04-12 | Vestas Wind Systems A/S | Wind turbine blade |
US20060049302A1 (en) * | 2004-08-31 | 2006-03-09 | Kennedy Dennis K | Apparatus and methods for structurally-integrated conductive conduits for rotor blades |
GB2440954B (en) * | 2006-08-18 | 2008-12-17 | Insensys Ltd | Structural monitoring |
-
2009
- 2009-04-17 GB GB0906625A patent/GB2469516A/en not_active Withdrawn
-
2010
- 2010-04-19 WO PCT/GB2010/050638 patent/WO2010119298A1/en active Application Filing
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2440953A (en) * | 2006-08-18 | 2008-02-20 | Insensys Ltd | Monitoring wind turbine blades |
WO2009068918A1 (en) * | 2007-11-30 | 2009-06-04 | Bae Systems Plc | Improvements relating to temperature monitoring |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2778059A1 (en) * | 2013-03-14 | 2014-09-17 | Bell Helicopter Textron Inc. | Amorphous metal rotor blade abrasion strip |
GB2505736A (en) * | 2013-03-15 | 2014-03-12 | Epsilon Optics Aerospace Ltd | Method of incorporating a coil of optical fibre into a composite structure |
GB2505736B (en) * | 2013-03-15 | 2015-06-10 | Epsilon Optics Aerospace Ltd | A method of incorporating a coil of optical fibre into a composite structure |
EP3068994A4 (en) * | 2013-11-15 | 2017-07-19 | United Technologies Corporation | Component with embedded sensor |
US10006304B2 (en) | 2013-11-15 | 2018-06-26 | United Technologies Corporation | Component with embedded sensor |
EP3485161A4 (en) * | 2016-07-15 | 2020-04-08 | Sikorsky Aircraft Corporation | Rotor blade deflection sensing system |
EP3768969A4 (en) * | 2018-03-18 | 2021-12-08 | Udesen Trade | The present invention relates to a device for remedying erosion problems on wind turbine blades |
WO2021234227A1 (en) * | 2020-05-20 | 2021-11-25 | Teknologian Tutkimuskeskus Vtt Oy | Sensor, arrangement, method of estimating an angle of attack, and computer readable memory |
Also Published As
Publication number | Publication date |
---|---|
GB0906625D0 (en) | 2009-05-27 |
WO2010119298A1 (en) | 2010-10-21 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |