CN116498505A - Method for arranging icing monitoring sensors of fan blades - Google Patents

Method for arranging icing monitoring sensors of fan blades Download PDF

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Publication number
CN116498505A
CN116498505A CN202310517748.8A CN202310517748A CN116498505A CN 116498505 A CN116498505 A CN 116498505A CN 202310517748 A CN202310517748 A CN 202310517748A CN 116498505 A CN116498505 A CN 116498505A
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China
Prior art keywords
blade
section
icing
curve
distance
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Pending
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CN202310517748.8A
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Chinese (zh)
Inventor
邬烔
唐烂芳
吴忠伟
孟秀俊
汪德军
詹彪
付荣方
周世银
朱玉瑞
胡辉
吴孝伟
刘勇
蔡安民
王传玺
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Huaneng Weining Wind Power Co ltd
Huaneng Clean Energy Research Institute
China Huaneng Group Co Ltd
Original Assignee
Huaneng Weining Wind Power Co ltd
Huaneng Clean Energy Research Institute
China Huaneng Group Co Ltd
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Application filed by Huaneng Weining Wind Power Co ltd, Huaneng Clean Energy Research Institute, China Huaneng Group Co Ltd filed Critical Huaneng Weining Wind Power Co ltd
Priority to CN202310517748.8A priority Critical patent/CN116498505A/en
Publication of CN116498505A publication Critical patent/CN116498505A/en
Pending legal-status Critical Current

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    • 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
    • F03D80/00—Details, components or accessories not provided for in groups F03D1/00 - F03D17/00
    • F03D80/40—Ice detection; De-icing means
    • 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
    • F03D1/0675—Rotors characterised by their construction elements of the blades
    • 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

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  • Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Wind Motors (AREA)

Abstract

The invention relates to the field of wind power generation, in particular to a method for arranging an icing monitoring sensor of a fan blade. And constructing a functional relation between the distance from the current section to the reference surface and the maximum speed time of icing x mm on the outer surface of the section by a multi-spline interpolation method. And re-selecting the section as the sensor mounting section by the function relation of the distance from the current section to the reference surface and the maximum speed of icing x mm on the outer surface of the section. Different sensor placement strategies are implemented depending on the parity of the section labels. The method for arranging the icing monitoring sensors of the fan blades can accurately and effectively monitor the icing condition of the blades in a short time, realize the quick response of a deicing system of the deicing blades, simultaneously control the number of the icing sensors on the blades, and reduce the influence of the sensors on the aerodynamic performance of the blades and the structure of the blades.

Description

Method for arranging icing monitoring sensors of fan blades
Technical Field
The invention relates to the field of wind power generation, in particular to a method for arranging an icing monitoring sensor of a fan blade.
Background
The problem of blade icing generally exists in the south wind field in China in winter. When the extremely cold condition occurs in a large range in China, ice coating is extremely easy to occur in regions with higher annual humidity such as regions in the south of Yangtze river and cloud precious regions. Such icing phenomenon may seriously affect the safe operation of the wind generating set. For the blade, the icing on the blade firstly changes the aerodynamic shape of the blade, reduces the capturing capacity of the impeller to wind energy to a certain extent, and reduces the power generation efficiency of the wind turbine. And secondly, the overall mass of the blades is increased when the blades are coated with ice, and according to different ice coating conditions of each blade, the impeller can generate periodic torque fluctuation with different frequencies and different amplitudes, so that the service lives of the impeller main shaft and the generator set are attenuated. In addition, the large volume of ice coating can pose a serious threat to surrounding personnel and equipment, and once the ice-throwing phenomenon occurs, the consequences are not envisaged.
In order to reduce the influence of icing on the wind generating set, icing monitoring sensors and deicing devices such as air heating, electric heating or vibration are required to be arranged on the blades and the engine room. When the icing monitoring sensor detects the icing, an early warning signal is sent to the deicing processing system in the fan in time, then the processor generates a deicing signal to drive the deicing system to work normally, and the icing on the outer surfaces of the blades and around the engine room is removed through means such as heating and vibration. The reasonable arrangement of the icing sensor is particularly important for detecting the icing condition and the subsequent deicing process.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a fan blade icing monitoring sensor arrangement method, which can determine the layout and the position of a blade icing sensor according to local conditions and has important significance for realizing short-time deicing of the blade.
The invention is realized by the following technical scheme:
an arrangement method of an icing monitoring sensor of a fan blade comprises the following steps:
s1, establishing a phyllanthus section two-dimensional model A of a blade section a ；
S2, a two-dimensional model A of a folin section a Carrying out ice-covered scene simulation on the outer surface of the steel plate, and then setting simulation parameters to obtain simulation data;
s3, simulating a natural icing process of the blade when the deicing device is not additionally arranged on the blade according to simulation data, and counting a sectional model A of each phyllin a The time required for icing each point on the outer surface of the blade element to x mm is obtained, and a curve L of the time required for the maximum value of the icing thickness of each blade element section to reach x mm is obtained along with the change of the distance of the reference surface;
s4, re-taking a group of blade sections C i And according to the blade section C on the curve L i Position acquisition section C of (2) i Distance L to blade root i Section C i The maximum speed time when ice is coated by x mm, wherein i is a constant;
s5, according to section C i Distance L to blade root i And section C i The blade icing detection sensor is arranged at the maximum speed of icing x mm.
Preferably, in S1, a two-dimensional model A of the phyllanthus cross-section a The acquisition method of (1) comprises the following steps: firstly, establishing a three-dimensional outer surface model of a blade, and cutting a plurality of blade sections; and then establishing a phyllanthin section two-dimensional model Aa for each blade section.
Preferably, the method for cutting the section of the blade comprises the following steps: taking a flange connection surface of the blade and the hub as a reference surface, and intercepting N blade sections in the aspect of extending to the blade, wherein the blade sections are parallel to the reference surface and perpendicular to a blade torsion angle base line; the N blade sections comprise N-1 equidistant sections and 1 detail section, the distance between two adjacent equidistant sections is d, and the distance between the detail section and the equidistant section is d/2.
Preferably, in S2, a two-dimensional model a of the blade section is built with the intersection point of the torsion angle baseline and each blade section as the origin, the circumferential rotation direction of the blade element airfoil as the negative X-axis direction, and the windward direction of the impeller as the negative Y-axis direction a 。
Preferably, the blade section two-dimensional model A a The equation is satisfied:
f a (x,y)＝0,(a＝1,2,...,N)
wherein f a (x, y) represents the outer contour curve equation of the two-dimensional section of the blade, and x and y are respectively the parameters satisfying the outer contourThe abscissa of the points of the curve, a, represents the position of the two-dimensional model of the blade section.
Preferably, in S3, the method for obtaining the curve L is as follows:
s301, simulating a natural icing process of the blade when the deicing device is not additionally arranged on the blade according to simulation data, and counting a sectional model A of each phyllin a The time required for icing each point on the outer surface of the blade to x mm is added on the basis of the phyllanthin section model coordinate system to be taken as the Z axis, and a space function curve T related to each blade section is formed a ；
S302, taking a space function curve T a Minimum value t a As the first appearance position point of the ice coating of the current section, i.e., the fastest position point of each section is denoted as (r a ，t a )；
S303, fitting the fastest position point (r) of each section by adopting a spline interpolation method a ，t a ) And obtaining a curve L of the time for the maximum value of the ice thickness of the section to reach x mm along with the change of the distance of the reference surface.
Preferably, in S301, the simulation data is compared with the wind tunnel experimental data, when icing with a thickness of x mm occurs, and when the superposition ratio of the area of the icing section of the actual blade and the area obtained by simulation calculation reaches 80%, the error is considered to be qualified, and the subsequent steps are performed; and when the error is unqualified, re-performing ice-covering scene simulation until simulation data with qualified error are obtained.
Preferably, in S301, the spatial function T a The equation is satisfied:
wherein T is a As a spatial function, its projection onto the XOY plane is f a An outer contour curve square city; t is Z-axis quantity and represents the time of x mm when blade icing first occurs at the corresponding section position; a is that a The two-dimensional model is an interface two-dimensional model, and x and y are the abscissas and the ordinates of position points on the outer contour curves.
Preferably, section C i Distance L to blade root i The calculated reference expression of (2) is:
wherein L is min Is the minimum on the L curve; l (L) max Is the maximum on the L curve.
Preferably, when i is an odd number, an icing sensor is arranged at the icing x mm fastest position point of the section; and when i is even, arranging an icing sensor at a position point corresponding to 1.5-2 times of the maximum speed time of icing x mm of the section.
Compared with the prior art, the invention has the following beneficial effects:
the method for arranging the icing monitoring sensors of the fan blades can accurately and effectively monitor the icing condition of the blades in a short time, realize the quick response of a deicing system of the deicing blades, simultaneously control the number of the icing sensors on the blades, and reduce the influence of the sensors on the aerodynamic performance of the blades and the structure of the blades.
According to the fan blade icing monitoring sensor arrangement method, gradient monitoring of blade icing conditions is achieved at the position points where the blades are easy to cover ice, and the used staggered sensor layout can reduce the installation cost of the sensor on the basis that the monitoring accuracy is not reduced. Meanwhile, a small amount of sensors are installed to a certain extent, so that good aerodynamic performance of the blade is maintained.
The invention enables the icing monitoring sensor to accurately and effectively monitor the icing condition of the blade in a short time, realizes the quick response of the deicing system for deicing the blade, can control the number of the icing sensors on the blade, and reduces the influence of the sensors on the aerodynamic performance and the blade structure of the blade.
Firstly, a sampling section is selected for a three-dimensional model of the blade to perform two-dimensional icing simulation calculation, so that the simulation workload and simulation time are reduced to a certain extent. The fastest icing rate of the current section is represented by the time taken for icing x mm obtained through simulation. And constructing a functional relation between the distance from the current section to the reference surface and the maximum speed time of icing x mm on the outer surface of the section by a multi-spline interpolation method. And re-selecting the section as the sensor mounting section by the function relation of the distance from the current section to the reference surface and the maximum speed of icing x mm on the outer surface of the section. For the re-selected section, implementing different sensor arrangement strategies according to the parity of section marks, wherein the sections marked with odd numbers are provided with icing sensors at the icing x mm fastest position points of the sections; and the sections with even numbers are provided with icing sensors at corresponding positions 1.5-2 times of the maximum speed time of icing x mm of the sections.
According to the invention, gradient monitoring of the icing condition of the blade is realized at the position points of the blade where the blade is easy to cover ice, and the installation cost of the sensor can be reduced on the basis of not reducing the monitoring accuracy by using the staggered sensor layout. Meanwhile, a small amount of sensors are installed to a certain extent, so that good aerodynamic performance of the blade is maintained.
Drawings
Fig. 1 is an overall flow diagram of an ice coating sensor arrangement.
FIG. 2 is a schematic view of a cross-sectional position taken through a blade.
FIG. 3 is a two-dimensional phyllanthin section model view.
FIG. 4 is a plot of time required to form x mm icing on the outer surface of a blade as a function of cross-section to datum plane distance.
Fig. 5 is an ice coating sensor arrangement of the present invention.
In the figure, 1, a hub and a blade are connected with a flange surface; 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 C 1 The method comprises the steps of carrying out a first treatment on the surface of the 14. Sensor arrangement section C 2 The method comprises the steps of carrying out a first treatment on the surface of the 15. Sensor arrangement section C 3 The method comprises the steps of carrying out a first treatment on the surface of the 16. Sensor arrangement section C 4 The method comprises the steps of carrying out a first treatment on the surface of the 17. Sensor arrangement section C 5 The method comprises the steps of carrying out a first treatment on the surface of the 18. Sensor arrangement section C 6 The method comprises the steps of carrying out a first treatment on the surface of the 19. Sensor arrangement section C 7 The method comprises the steps of carrying out a first treatment on the surface of the 20. Ice coating x mm mostA speed sensor arrangement point; 21. the sensor arrangement point is coated with ice on the lee side for x mm of maximum speed time of 1.5-2 times; 22. the maximum speed of icing x mm at the windward side is 1.5-2 times of the sensor arrangement point.
Detailed Description
The invention will now be described in further detail with reference to specific examples, which are intended to illustrate, but not to limit, the invention.
The invention discloses a fan blade icing monitoring sensor arrangement method, which comprises the following steps with reference to fig. 1:
s1, establishing a three-dimensional outer surface model of a blade, and cutting a plurality of blade sections;
the method for cutting the section of the blade comprises the following steps: taking a flange connection surface of a blade and a hub as a reference surface 1, and intercepting N blade sections in the aspect of extending to the blade, wherein the blade sections are parallel to the reference surface and perpendicular to a blade torsion angle base line 2; the N blade sections comprise N-1 equidistant sections and 1 detail section, the distance between two adjacent equidistant sections is d, and the distance between the detail section and the equidistant section is d/2.
For each blade section, establishing a phyllanthus section two-dimensional model A a The method comprises the steps of carrying out a first treatment on the surface of the Taking the intersection point of the torsion angle baseline 2 and each blade section as an origin, taking the circumferential rotation direction of a blade plain airfoil profile as an X-axis negative direction, and taking the windward direction of an impeller as a Y-axis negative direction, and establishing a blade section two-dimensional model A a Referring to fig. 3, the equation is satisfied:
f a (x,y)＝0,(a＝1,2,...,10)
wherein f a (x, y) represents an outer contour curve equation of the two-dimensional section of the blade, x and y are respectively the abscissa of points meeting the outer contour curve, and a represents the position of the two-dimensional model of the section of the blade.
S3, simulating a natural icing process of the blade when the deicing device is not additionally arranged on the blade according to simulation data, and counting a sectional model A of each phyllin a The time required for icing each point on the outer surface of the blade element to x mm is obtained, and a curve L of the time required for the maximum value of the icing thickness of each blade element section to reach x mm is obtained along with the change of the distance of the reference surface; the method comprises the following specific steps:
s301, according to the regional characteristics of the wind turbine generator, using simulation software to simulate the ice-covering scene of the two-dimensional model of the blade, and then setting scene parameters of the simulation software based on wind tunnel experimental data until the experimental data and the software simulation data are within allowable errors. Two-dimensional model A of folacin section a Carrying out ice-covered scene simulation on the outer surface of the steel plate, and then setting simulation parameters to obtain simulation data; comparing the simulation data with wind tunnel experimental data, and when icing with the thickness of x mm occurs, considering that the error is qualified and carrying out the subsequent steps when the superposition rate of the area of the icing section of the actual blade and the area obtained by simulation calculation reaches 80%; and when the error is unqualified, re-performing ice-covering scene simulation until simulation data with qualified error are obtained.
S302, simulating a natural icing process of the blade when the deicing device is not additionally arranged on the blade according to simulation data, and counting a sectional model A of each phyllin a The time required for icing each point on the outer surface of the blade to 2mm is added on the basis of the phyllanthin section model coordinate system to be taken as the Z axis, and a space function curve T related to each blade section is formed a The equation is satisfied:
wherein T is a As a spatial function, its projection onto the XOY plane is f a An outer contour curve square city; t is Z-axis quantity and represents the time of x mm when blade icing first occurs at the corresponding section position; a is that a The two-dimensional model is an interface two-dimensional model, and x and y are the abscissas and the ordinates of position points on the outer contour curves.
S303, taking a space function curve T a Minimum value t a As the first appearance position point of the ice coating of the current section, i.e., the fastest position point of each section is denoted as (r a ，t a ) The method comprises the steps of carrying out a first treatment on the surface of the Fitting the fastest position point (r) of each section by spline interpolation method a ，t a ) Obtaining a curve L of the change of the time for the maximum value of the ice thickness of the section to reach x mm along with the distance of a reference surface, wherein the curve L can be visualizedReflecting the rate of ice formation on the blade;
s4, referring to FIG. 4, a set of blade sections C is taken again i And according to the blade section C on the curve L i Position acquisition section C of (2) i Distance L to blade root i Section C i The maximum speed time when ice is coated with xmm, wherein i is a constant;
wherein the blade section C i Distance L to blade root i The calculated reference expression is:
wherein L is min Is the minimum on the L curve; l (L) max Is the maximum on the L curve.
S5, according to section C i Distance L to blade root i And the arrangement of the blade icing detection sensor is performed at the maximum speed. When i is odd, at C i An icing sensor is arranged at the position point of the maximum speed of the icing x mm of the section; and when i is even, arranging an icing sensor at a position point corresponding to 1.5-2 times of the maximum speed time of icing x mm of the section.
Wherein C is i The icing x mm fastest position of the section is determined by the two-dimensional simulation, and the simulation environment parameters are determined according to A a And carrying out linearization treatment on the simulated parameters to obtain the simulation parameters.
Examples
Firstly, a three-dimensional outer surface model of a blade is established by software, then, according to the position relation determined in the invention content, a group of sampling surfaces (shown in figure 2) consisting of 10 sections are selected, in figure 2, 1 is a hub and blade connecting flange surface, 2 is a blade torsion angle baseline, 3 is a 0.1R blade section, 4 is a 0.2R blade section, 5 is a 0.3R blade section, 6 is a 0.4R blade section, 7 is a 0.5R blade section, 8 is a 0.6R blade section, 9 is a 0.7R blade section, 10 is a 0.8R blade section, 11 is a 0.9R blade section, and 12 is a 0.95R blade section. Defining the distance from the reference surface to the blade tip as R, and then defining the distance R from the reference surface of 10 blade sections a 0.1R, 0.2R, 0.3R respectively,0.4R, 0.5R, 0.6R, 0.7R, 0.8R, 0.9R and 0.95R.
And carrying out two-dimensional modeling on the phyllanthus cross section of the sampling surface. And then carrying out ice-covering scene simulation on the two-dimensional model by using simulation software, comparing simulation data with actual wind tunnel experimental data, and then adjusting model simulation parameters until errors are allowed. Taking icing time of 2mm at each point on the outer surface of the phyllanthin section as Z-axis variable to construct a space function curve T a . Taking the minimum time t of the curve a As the current section, 2mm of maximum speed time was covered with ice. With (r) a ,t a ) For cubic spline interpolation boundary conditions, a cubic spline curve L is constructed, then according to formula 3, 7 points on the L curves are selected, and the 7 points redetermine a group of blade sections, namely L 1 ～L 7 Is taken again a set of sections C 1 ～C 7 (13-19), section C 1 ～C 7 (13-19) the corresponding positions on the L-curve are shown in FIG. 4. FIG. 4 shows a sensor arrangement section C at 13 1 Section C of the sensor arrangement at 14 2 Section C of the sensor arrangement at 15 3 Section C of the sensor arrangement is 16 4 The method comprises the steps of carrying out a first treatment on the surface of the 17 is the sensor arrangement section C 5 The method comprises the steps of carrying out a first treatment on the surface of the 18 is a sensor arrangement section C 6 The method comprises the steps of carrying out a first treatment on the surface of the 19 is the sensor arrangement section C 7 。
Referring to fig. 5, a different sensor arrangement is then selected based on the parity of the selection of section index i. When i is an odd number, mounting an icing sensor at the position point of the 2mm fastest speed of icing on the section; when i is even, an icing sensor is installed at a position corresponding to 1.5-2 times of the 2mm maximum speed time of icing on the section, 20 is the 2mm maximum speed sensor arrangement point of icing in fig. 5, 21 is the 1.5-2 times of the 2mm maximum speed time of icing on the leeward side, and 22 is the 1.5-2 times of the 2mm maximum speed time of icing on the windward side.
The foregoing description of the preferred embodiment of the present invention is not intended to limit the technical solution of the present invention in any way, and it should be understood that the technical solution can be modified and replaced in several ways without departing from the spirit and principle of the present invention, and these modifications and substitutions are also included in the protection scope of the claims.

Claims (10)

1. The method for arranging the fan blade icing monitoring sensor is characterized by comprising the following steps of:
s1, establishing a phyllanthus section two-dimensional model A of a blade section a ；
S2, a two-dimensional model A of a folin section a Carrying out ice-covered scene simulation on the outer surface of the steel plate, and then setting simulation parameters to obtain simulation data;
s3, simulating a natural icing process of the blade when the deicing device is not additionally arranged on the blade according to simulation data, and counting a sectional model A of each phyllin a The time required for icing each point on the outer surface of the blade element to x mm is obtained, and a curve L of the time required for the maximum value of the icing thickness of each blade element section to reach x mm is obtained along with the change of the distance of the reference surface;
s4, re-taking a group of blade sections C i And according to the blade section C on the curve L i Position acquisition section C of (2) i Distance L to blade root i Section C i The maximum speed time when ice is coated by x mm, wherein i is a constant;
s5, according to section C i Distance L to blade root i And section C i The blade icing detection sensor is arranged at the maximum speed of icing x mm.
2. The fan blade icing monitoring sensor arrangement method according to claim 1, characterized in that in S1, a two-dimensional model a of the phyllanthin cross section a The acquisition method of (1) comprises the following steps: firstly, establishing a three-dimensional outer surface model of a blade, and cutting a plurality of blade sections; and then establishing a phyllanthin section two-dimensional model Aa for each blade section.
3. The fan blade icing monitoring sensor arrangement method according to claim 2, wherein the blade section intercepting method comprises the following steps: taking a flange connection surface of the blade and the hub as a reference surface, and intercepting N blade sections in the aspect of extending to the blade, wherein the blade sections are parallel to the reference surface and perpendicular to a blade torsion angle base line; the N blade sections comprise N-1 equidistant sections and 1 detail section, the distance between two adjacent equidistant sections is d, and the distance between the detail section and the equidistant section is d/2.
4. The method for arranging ice coating monitoring sensors of fan blades according to claim 3, wherein in S2, a two-dimensional model A of the blade sections is built by taking an intersection point of a torsion angle baseline and each blade section as an origin, taking a circumferential rotation direction of a blade element airfoil profile as an X-axis negative direction and taking a windward direction of an impeller as a Y-axis negative direction a 。
5. The fan blade icing monitoring sensor arrangement method according to claim 4, wherein the blade section two-dimensional model a a The equation is satisfied:
f a (,y)＝0,(a＝1,2,...,N)
wherein f a (x, y) represents an outer contour curve equation of the two-dimensional section of the blade, x and y are respectively the abscissa of points meeting the outer contour curve, and a represents the position of the two-dimensional model of the section of the blade.
6. The fan blade icing monitoring sensor arrangement method according to claim 4, characterized in that in S3, the method for obtaining the curve L is:
s301, simulating a natural icing process of the blade when the deicing device is not additionally arranged on the blade according to simulation data, and counting a sectional model A of each phyllin a The time required for icing each point on the outer surface of the blade to x mm is added on the basis of the phyllanthin section model coordinate system to be taken as the Z axis, and a space function curve T related to each blade section is formed a ；
S302, taking a space function curve T a Minimum value t a As the first appearance position point of the ice coating of the current section, i.e., the fastest position point of each section is denoted as (r a ，t a )；
S303, fitting the fastest position point (r) of each section by adopting a spline interpolation method a ，t a ) And obtaining a curve L of the time for the maximum value of the ice thickness of the section to reach x mm along with the change of the distance of the reference surface.
7. The fan blade icing monitoring sensor arrangement method according to claim 6, wherein in S301, simulation data are compared with wind tunnel experimental data, when icing with the thickness of x mm occurs, when the superposition rate of the area of the icing section of the actual blade and the area obtained by simulation calculation reaches 80%, errors are considered to be qualified, and the subsequent steps are performed; and when the error is unqualified, re-performing ice-covering scene simulation until simulation data with qualified error are obtained.
8. The fan blade icing monitoring sensor arrangement method according to claim 6, characterized in that in S301 the spatial function T a The equation is satisfied:
wherein T is a As a spatial function, its projection onto the XOY plane is f a An outer contour curve square city; t is Z-axis quantity and represents the time of x mm when blade icing first occurs at the corresponding section position; a is that a The two-dimensional model is an interface two-dimensional model, and x and y are the abscissas and the ordinates of position points on the outer contour curves.
9. The fan blade icing monitoring sensor arrangement method of claim 6 wherein section C i Distance L to blade root i The calculated reference expression of (2) is:
wherein L is min Is the minimum on the L curve; l (L) max Is the maximum on the L curve.
10. The fan blade icing monitoring sensor arrangement method according to claim 9, characterized in that when i is an odd number, an icing sensor is arranged at the icing x mm maximum speed position point of the section; and when i is even, arranging an icing sensor at a position point corresponding to 1.5-2 times of the maximum speed time of icing x mm of the section.
CN202310517748.8A 2023-05-09 2023-05-09 Method for arranging icing monitoring sensors of fan blades Pending CN116498505A (en)

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* Cited by examiner, † Cited by third party
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CN117436322A (en) * 2023-12-21 2024-01-23 浙江远算科技有限公司 Wind turbine blade aeroelastic simulation method and medium based on phyllin theory

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117436322A (en) * 2023-12-21 2024-01-23 浙江远算科技有限公司 Wind turbine blade aeroelastic simulation method and medium based on phyllin theory
CN117436322B (en) * 2023-12-21 2024-04-19 浙江远算科技有限公司 Wind turbine blade aeroelastic simulation method and medium based on phyllin theory

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