WO2023040417A1 - New moving blade modeling method for energy-saving transformation of axial flow fan with adjustable moving blades of power station - Google Patents

New moving blade modeling method for energy-saving transformation of axial flow fan with adjustable moving blades of power station Download PDF

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WO2023040417A1
WO2023040417A1 PCT/CN2022/102929 CN2022102929W WO2023040417A1 WO 2023040417 A1 WO2023040417 A1 WO 2023040417A1 CN 2022102929 W CN2022102929 W CN 2022102929W WO 2023040417 A1 WO2023040417 A1 WO 2023040417A1
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blade
fan
airfoil
new
profile
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PCT/CN2022/102929
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French (fr)
Chinese (zh)
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陈得胜
郑金
孙大伟
闫宏
石清鑫
马翔
李昊燃
王伯平
朱红伟
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西安热工研究院有限公司
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
    • 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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  • the application relates to an axial flow fan with adjustable movable blades used in the flue gas system of a coal-fired power plant, in particular to a new type of modeling method for the movable blades of an axial flow fan with adjustable movable blades for energy-saving transformation.
  • axial flow fans with adjustable rotor blades are the most widely used in all kinds of thermal power units in China.
  • due to factors such as unreasonable selection of fans, large changes in coal quality, and frequent deep peak regulation of units there are some problems in the actual operation of fans.
  • Various problems such as insufficient fan output, low stall margin, and poor matching with the pipe network system lead to poor economics and safety in actual operation of axial flow fans with adjustable rotor blades, resulting in high energy consumption of thermal power generating units.
  • the energy-saving transformation of axial flow fans with adjustable movable blades usually involves replacing the whole fan. This not only requires huge investment costs, but also has a long payback period, and because the fan manufacturers have fewer blade shapes, the matching between the fan and the system after transformation Difficult to achieve the best. Therefore, when implementing energy-saving transformation of axial flow fans with adjustable movable blades, it is necessary to propose a new type of moving blade modeling method for energy-saving transformation of fans, so as to achieve multiple purposes such as saving investment costs, shortening the investment recovery period, realizing deep energy saving of fans, and ensuring safe and reliable operation of fans.
  • this application proposes a new type of moving blade modeling method for energy-saving transformation of axial flow fans with adjustable moving blades in power stations.
  • a new type of energy-saving blade shape is carried out for the fan moving blades. After the shape is completed, all the original moving blades of the fan are replaced with new moving blades, so as to save investment costs, shorten the investment recovery period, realize deep energy saving of the fan, and ensure the safe and reliable operation of the fan, etc. Purpose.
  • a new type of rotor blade modeling method for energy-saving retrofit of an axial flow fan with adjustable rotor blades in a power station comprising: firstly, determining the fan modification method according to the technical parameters of the fan before and after the energy-saving modification of the axial fan with adjustable rotor blades; secondly, for different fan modification methods , to determine the corresponding new rotor blade modeling method; finally, according to the fan transformation plan and the new rotor blade modeling method determined above, implement the fan energy-saving transformation.
  • the further improvement of the present application lies in that, for the energy-saving transformation of the single-stage movable blade adjustable axial flow fan with a new type of movable blade shape, the specific implementation method is as follows:
  • Step 1 Determine the technical plan for fan transformation, according to the flow coefficient corresponding to the fan TB point selection parameters before the transformation of the adjustable blade axial flow fan Pressure coefficient ⁇ 1 , flow coefficient corresponding to TB point selection parameters after fan energy-saving transformation
  • the pressure coefficient ⁇ 2 determines the technical scheme of fan transformation
  • Step 2 Determine the modeling method of the new rotor blade of the fan.
  • the technical plan for fan renovation is divided into two methods: fan blade replacement and fan partial modification.
  • the fan blade replacement method when the ratio of the flow coefficient before and after the fan modification satisfies , only need to replace all the moving blades of the fan, while the dimensions of other structures such as the hub and casing of the fan remain unchanged;
  • H 1 is the height of the fan blade before modification
  • H′ 1 is the height of the fan blade after modification
  • the unit is mm
  • R′ shroud R shroud + H′ 1 -H 1 , where R shroud is the inner diameter of the fan casing before transformation , R′ shroud is the inner diameter of the casing after the transformation of the fan, and the unit is mm.
  • the blade profile lines BS′ i of the M airfoil sections of the new type of moving blade are stacked along the blade height direction to generate a three-dimensional model of the new type of moving blade.
  • the blade profile line BS'i of the profile section is accumulated along the blade height direction through the Bezier curve C2 , and the three-dimensional modeling of the new type of moving blade is completed.
  • n-order Bezier curves to perform curve fitting on the pressure surface PS i and suction surface SS i of the i-th airfoil section of the original blade.
  • the n-order Bezier curve formula is as follows:
  • the positions of the blade leading edge point A i and the blade trailing edge point B i are kept unchanged, and the same blade thickness distribution is applied to both sides of the mid-arc line C 1,i of the i-th airfoil section.
  • the middle arc C 1,i of the i-th airfoil section of the original blade and the Bezier fitting curve of the airfoil thickness distribution are obtained, and the following parameters are obtained: the leading edge of the i-th airfoil section of the original blade Inlet geometric angle ⁇ i , trailing edge outlet geometric angle ⁇ i , airfoil chord length c i , blade maximum thickness position to airfoil leading edge position a i , blade maximum thickness b max,i parameter;
  • the arc Bezier fitting curve parameters of the new-type moving blade airfoil cross - section are determined by the following formula :
  • k 1 is the adjustment coefficient of the inlet geometric angle of the airfoil leading edge
  • k 2 is the adjustment coefficient of the geometric angle of the airfoil trailing edge outlet
  • k 3 is the adjustment coefficient of the airfoil chord length
  • the profile line of the arc C′ 1,i in the profile section of the new rotor blade is uniquely determined.
  • step (3) the specific implementation method is as follows:
  • the leading edge arc curve and the trailing edge arc curve are respectively constructed on the leading edge and the trailing edge of the airfoil section.
  • the leading edge arc curve and the trailing edge arc curve are both arcs, which are respectively related to the pressure surface curve and suction generated above.
  • the surface curves are tangent, and in the section of the airfoil, the arc radius R′ 1,i of the leading edge arc curve of the new type of moving blade satisfies: 0 ⁇ R′ 1,i ⁇ 3% c′ i ; the trailing edge of the new type of moving blade
  • the arc radius R′ 2,i of the arc curve satisfies: 0 ⁇ R′ 2,i ⁇ 2% c′ i , thus, the pressure surface profile line PS′ i of the i-th airfoil section of the new moving blade is determined and the suction surface profile line SS′ i , combining the pressure surface profile line PS′ i and the suction surface profile line SS′ i to complete the blade profile line BS′ i of the i-th profile section of the new rotor blade structure.
  • the further improvement of this application is that, for the energy-saving transformation of the new type of rotor blade shape of the double-stage movable blade adjustable axial flow fan, the first-stage and second-stage new type of movable blade modeling methods are the same, and they are all in accordance with the single-stage movable blade adjustable axial flow fan.
  • Modeling with the method of energy-saving transformation of the new type of moving blade the first stage follows the method of energy-saving transformation of the single-stage adjustable axial flow fan to complete the shape of the new type of moving blade of the single-stage fan, and the second stage repeats the above process , the shape of the first-stage and second-stage wind turbine blades is exactly the same.
  • This application provides a new type of moving blade modeling method for energy-saving transformation of axial flow fans with adjustable moving blades in power stations.
  • the fan transformation method is determined, and then, for different fan transformations Methods Determine the corresponding new rotor blade modeling method.
  • the energy-saving transformation of the axial flow fan with adjustable moving blades and the new shape of the moving blades can be implemented according to the method determined above.
  • the new type of blade modeling method for the adjustable blade axial fan can be customized according to the actual needs of users, and the new type of blade for energy-saving transformation of the axial fan with adjustable blade can be customized.
  • the new type of blade developed is applied to the shaft with adjustable blade After the flow fan, on the basis of reducing the output of the fan, the deep energy saving of the fan can be realized, and at the same time, the adjustment performance of the fan can be effectively improved, the operating range of the fan can be expanded, and the energy-saving transformation effect of the fan is remarkable.
  • Fig. 1 is the schematic diagram of the airfoil section modeling of the patent of the present application.
  • Fig. 2 is a schematic diagram of the thickness distribution of the airfoil section of the patent application.
  • M is the total number of airfoil sections of the blade shape
  • i is the serial number of the airfoil section
  • ⁇ 1 is the pressure coefficient corresponding to the fan TB point selection parameter before transformation
  • ⁇ 2 is the pressure coefficient corresponding to the type selection parameter of the modified fan point TB.
  • H 1 is the height of the moving blade before the fan modification
  • H′ 1 is the height of the moving blade after the fan modification
  • R shroud is the inner diameter of the fan casing before the fan modification
  • R′ shroud is the inner diameter of the fan casing after the fan modification
  • n is the order of the Bezier curve
  • P i is the control point of the Bezier curve
  • Figure 1 shows the parameters of the i-th airfoil section of the original blade, where A i is the leading edge point of the airfoil, B i is the trailing edge point of the airfoil, C 1,i is the arc shape line of the airfoil, and PS i is the shape line of the pressure surface of the airfoil, and SS i is the shape line of the suction surface of the airfoil.
  • ⁇ i is the inlet geometric angle of the leading edge of the airfoil
  • ⁇ i is the geometric angle of the airfoil trailing edge outlet
  • a i is the distance between the position of the maximum thickness of the airfoil and the leading edge of the airfoil
  • b max,i is the maximum thickness of the airfoil
  • c i is the chord length of the airfoil
  • R 1,i is the arc radius of the original blade leading edge arc curve
  • R 2, i is the arc radius of the original blade trailing edge arc curve
  • the above units are mm.
  • Figure 2 is the parameters of the i-th airfoil section of the original blade, where the leading edge point A i of the blade is the coordinate origin 0, x is the arc line C′ 1 in the airfoil shape, and a point on i is far from the coordinate origin 0 in the x direction b(x) is the blade thickness distribution corresponding to the x-coordinate position.
  • the following parameters are the parameters of the i-th airfoil section of the new type of moving blade:
  • C′ 1,i is the profile line of the airfoil center arc
  • PS′ i is the profile line of the pressure surface of the blade profile
  • SS′ i is the profile line of the suction surface of the blade profile.
  • ⁇ ′ i is the inlet geometric angle of the airfoil leading edge
  • ⁇ ′ i is the geometric angle of the airfoil trailing edge outlet
  • k 1 is the adjustment coefficient of the airfoil leading edge inlet geometric angle
  • k 2 is the airfoil trailing edge Export geometry angle adjustment factor.
  • a' i is the distance from the position of the maximum thickness of the airfoil to the leading edge of the airfoil
  • b' max,i is the maximum thickness of the airfoil
  • c' i is the chord length of the airfoil
  • R' 1,i is the arc curve of the leading edge of the airfoil Arc radius
  • R′ 2, i is the arc radius of the arc curve of the trailing edge of the blade profile, and the above units are mm
  • k 3 is the adjustment coefficient of the blade profile chord length.
  • x' is the distance from a point on the arc C' 1, i in the blade shape to the coordinate origin 0 in the x direction, and b(x') is the thickness distribution of the blade shape corresponding to the position of the abscissa x'.
  • O′ i is the center of gravity of the blade shape
  • C 2 is the Bezier curve stacked along the blade height direction of the blade shape.
  • a new type of rotor blade modeling method for energy-saving transformation of an axial flow fan with adjustable rotor blades in a power station including:
  • H 1 is the height of the fan blade before modification
  • H′ 1 is the height of the fan blade after modification
  • the unit is mm.
  • R shroud is the inner diameter of the casing of the fan before modification
  • R′ shroud is the inner diameter of the casing of the fan after modification
  • the unit is mm.
  • n-order Bezier curves curve fitting is carried out on the pressure surface PS i and the suction surface SS i of the i-th airfoil section of the original blade.
  • the n-order Bezier curve formula is as follows:
  • the positions of the blade leading edge point A i and the blade trailing edge point B i are kept unchanged, and the same blade thickness distribution is applied to both sides of the mid-arc line C 1,i of the i-th airfoil section.
  • the pressure surface profile PS i and the suction surface profile line SS i are used for curve fitting; the least square method is used to solve the Bessel
  • the middle arc C 1,i of the i-th airfoil section of the original blade and the Bezier fitting curve of the airfoil thickness distribution are obtained, and the following parameters are obtained: the leading edge of the i-th airfoil section of the original blade Inlet geometric angle ⁇ i , trailing edge outlet geometric angle ⁇ i , airfoil chord length c i , blade maximum thickness position from airfoil leading edge position a i , blade maximum thickness b max,i parameters.
  • the arc Bezier fitting curve parameters of the new-type moving blade airfoil cross - section are determined by the following formula :
  • k 1 is the adjustment coefficient of the inlet geometric angle of the airfoil leading edge
  • k 2 is the adjustment coefficient of the geometric angle of the airfoil trailing edge outlet
  • k 3 is the adjustment coefficient of the airfoil chord length
  • the profile line of the arc C′ 1,i in the profile section of the new rotor blade is uniquely determined.
  • the arc radius R′ 1,i of the arc curve at the leading edge of the new type of moving blade satisfies: 0 ⁇ R′ 1,i ⁇ 3% c′ i ; the new type of moving blade
  • the arc radius R′ 2,i of the arc curve of the trailing edge satisfies: 0 ⁇ R′ 2,i ⁇ 2% ⁇ c′ i .
  • the pressure surface profile PS′ i and the suction surface profile SS′ i of the i-th airfoil section of the new rotor blade are determined, and the pressure surface profile PS′ i and the suction surface profile SS′ i are combined , will complete the construction of the profile line BS′ i of the i-th profile section of the new rotor blade.
  • the profile line BS'i of the i-th profile section of the new rotor blade is stacked along the blade height direction through the Bezier curve C2 , and the three-dimensional modeling of the new rotor blade
  • the modeling method of the new rotor blade of the first stage and the second stage is the same, and the modeling method is carried out according to the method of the first step: the first stage After completing the shape of the new moving blades of the single-stage fan according to the method of the first step, repeat the above process for the second stage, and the shapes of the moving blades of the first and second stages are exactly the same. In this way, the shape of the new type of movable blade for energy-saving transformation of the two-stage movable blade adjustable axial flow fan is completed.
  • the gas density is 1.146kg/m 3 .
  • the flow coefficient corresponding to the fan TB point selection parameters before transformation is obtained
  • the pressure coefficient ⁇ 1 0.421 corresponding to the fan TB point selection parameter before transformation, and the flow coefficient corresponding to the fan TB point selection parameter after transformation
  • the pressure coefficient ⁇ 2 corresponding to the type selection parameter of fan TB point after transformation is 0.321.
  • the new type of moving blade shape of the energy-saving transformation of the axial flow fan with adjustable moving blades is completed.
  • the fan can not only meet the output requirements of the new model selection point after the energy-saving transformation, but also reduce the comprehensive energy consumption of the fan by more than 15%.
  • the scope has been increased by more than 10%, the operation economy of the fan and the applicability of the equipment have been significantly improved, and the energy-saving transformation of the fan has achieved remarkable results.

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Abstract

Disclosed in the present application is a new moving blade modeling method for the energy-saving transformation of an axial flow fan with adjustable moving blades of a power station. The method comprises: first, determining a fan transformation method according to fan technical parameters before and after the energy-saving transformation of an axial flow fan with adjustable moving blades; second, for different fan transformation methods, determining corresponding new moving blade modeling methods; and finally, implementing energy-saving transformation of the fan according to the determined fan transformation method and new moving blade modeling method. In the present application, when most parts of an axial flow fan with adjustable moving blades remain unchanged, new energy-saving blade modeling is performed on moving blades of the fan, and the original moving blades of the fan are completely replaced with new moving blades after transformation is completed, thereby achieving multiple goals in terms of saving on investment costs, shortening the investment recovery period, realizing deep energy saving of the fan, guaranteeing the safe and reliable operation of the fan, etc.

Description

一种电站动叶可调式轴流风机节能改造新型动叶造型方法A new type of rotor blade modeling method for energy-saving retrofit of an axial flow fan with adjustable rotor blades in a power station
相关申请的交叉引用Cross References to Related Applications
本申请要求在2021年9月18日提交中国专利局、申请号为202111112596.0、发明名称为“一种电动站叶可调式轴流风机节能改造新型动叶造型方法”的中国专利申请的优先权，其全部内容通过引用结合在本申请中。This application claims the priority of the Chinese patent application submitted to the China Patent Office on September 18, 2021, with the application number 202111112596.0, and the title of the invention is "A new type of moving blade modeling method for energy-saving transformation of an electric station blade adjustable axial flow fan", The entire contents of which are incorporated by reference in this application.
技术领域technical field
本申请涉及燃煤电厂烟气系统所使用的动叶可调式轴流风机，具体涉及一种电站动叶可调式轴流风机节能改造新型动叶造型方法。The application relates to an axial flow fan with adjustable movable blades used in the flue gas system of a coal-fired power plant, in particular to a new type of modeling method for the movable blades of an axial flow fan with adjustable movable blades for energy-saving transformation.
背景技术Background technique
目前全国各类火电机组动叶可调轴流式风机的应用最为广泛，然而，由于风机选型不合理、煤质变化太大、机组频繁深度调峰等因素，使得风机在实际运行过程中存在着风机出力不足、失速裕量低以及与管网系统匹配性差等各种问题，导致动叶可调式轴流风机实际运行经济性和安全性往往较差，造成火力发电机组能耗较高。At present, axial flow fans with adjustable rotor blades are the most widely used in all kinds of thermal power units in China. However, due to factors such as unreasonable selection of fans, large changes in coal quality, and frequent deep peak regulation of units, there are some problems in the actual operation of fans. Various problems such as insufficient fan output, low stall margin, and poor matching with the pipe network system lead to poor economics and safety in actual operation of axial flow fans with adjustable rotor blades, resulting in high energy consumption of thermal power generating units.
动叶可调式轴流风机实施节能改造，采用的改造方案往往都是将风机整机更换，这样不仅投资费用巨大，回收周期长，而且由于风机厂家叶型较少使得改造后风机与系统匹配性难以达到最佳。因此，动叶可调式轴流风机实施节能改造时，有必要提出风机节能改造新型动叶片造型方法，达到节省投资费用、缩短投资回收年限，实现风机深度节能，保证风机安全可靠运行等多重目的。The energy-saving transformation of axial flow fans with adjustable movable blades usually involves replacing the whole fan. This not only requires huge investment costs, but also has a long payback period, and because the fan manufacturers have fewer blade shapes, the matching between the fan and the system after transformation Difficult to achieve the best. Therefore, when implementing energy-saving transformation of axial flow fans with adjustable movable blades, it is necessary to propose a new type of moving blade modeling method for energy-saving transformation of fans, so as to achieve multiple purposes such as saving investment costs, shortening the investment recovery period, realizing deep energy saving of fans, and ensuring safe and reliable operation of fans.
发明内容Contents of the invention
为解决现有技术存在的问题，本申请提出一种电站动叶可调式轴流风机节能改造新型动叶造型方法，其目的是在保持动叶可调式轴流风机大部分零部件不变的前提下，对风机动叶片进行新型节能叶片造型，造型完成后将风机原有动叶片全部更换为新型动叶片，达到节省投资费用、缩短投资回收年限，实现风机深度节能，保证风机安全可靠运行等多重目的。In order to solve the problems existing in the existing technology, this application proposes a new type of moving blade modeling method for energy-saving transformation of axial flow fans with adjustable moving blades in power stations. Next, a new type of energy-saving blade shape is carried out for the fan moving blades. After the shape is completed, all the original moving blades of the fan are replaced with new moving blades, so as to save investment costs, shorten the investment recovery period, realize deep energy saving of the fan, and ensure the safe and reliable operation of the fan, etc. Purpose.
本申请采用如下技术方案来实现的：This application adopts following technical scheme to realize:
一种电站动叶可调式轴流风机节能改造新型动叶造型方法，包括：首先，根据动叶可调式轴流风机节能改造前、后风机技术参数确定风机改造方法；其次，针对不同风机改造方法，确定相应的新型动叶造型方法；最后，根据上面确定的风机改造方案和新型动叶造型方法，实施风机节能改造。A new type of rotor blade modeling method for energy-saving retrofit of an axial flow fan with adjustable rotor blades in a power station, comprising: firstly, determining the fan modification method according to the technical parameters of the fan before and after the energy-saving modification of the axial fan with adjustable rotor blades; secondly, for different fan modification methods , to determine the corresponding new rotor blade modeling method; finally, according to the fan transformation plan and the new rotor blade modeling method determined above, implement the fan energy-saving transformation.
本申请进一步的改进在于，对于单级动叶可调式轴流风机节能改造新型动叶造型，具体实现方法如下：The further improvement of the present application lies in that, for the energy-saving transformation of the single-stage movable blade adjustable axial flow fan with a new type of movable blade shape, the specific implementation method is as follows:
步骤1、确定风机改造技术方案，根据动叶可调式轴流风机改造前风机TB点选型参数对应的流量系数
Figure PCTCN2022102929-appb-000001
压力系数φ 1，风机节能改造后TB点选型参数对应的流量系数
Figure PCTCN2022102929-appb-000002
压力系数φ 2确定风机改造技术方案； Step 1. Determine the technical plan for fan transformation, according to the flow coefficient corresponding to the fan TB point selection parameters before the transformation of the adjustable blade axial flow fan
Figure PCTCN2022102929-appb-000001
Pressure coefficient φ 1 , flow coefficient corresponding to TB point selection parameters after fan energy-saving transformation
Figure PCTCN2022102929-appb-000002
The pressure coefficient φ 2 determines the technical scheme of fan transformation;
步骤2、确定风机新型动叶造型方法，风机改造技术方案分为风机叶片更换和风机局部改造两种方法。Step 2. Determine the modeling method of the new rotor blade of the fan. The technical plan for fan renovation is divided into two methods: fan blade replacement and fan partial modification.
本申请进一步的改进在于，风机改造技术方案分为风机叶片更换和风机局部改造两种方法，两种方法分别陈述如下：The further improvement of the present application is that the technical scheme of fan transformation is divided into two methods: fan blade replacement and fan partial modification, and the two methods are respectively stated as follows:
(1)风机叶片更换方法，当风机改造前、后流量系数比满足
Figure PCTCN2022102929-appb-000003
时，仅需更换风机全部动叶片，而风机轮毂和机壳等其它结构的尺寸均保持不变； (1) The fan blade replacement method, when the ratio of the flow coefficient before and after the fan modification satisfies
Figure PCTCN2022102929-appb-000003
, only need to replace all the moving blades of the fan, while the dimensions of other structures such as the hub and casing of the fan remain unchanged;
(2)风机局部改造方法，当风机改造前、后流量系数比满足
Figure PCTCN2022102929-appb-000004
时，在风机叶片更换的同时，还需进行如下改动： (2) Partial transformation method of the fan, when the ratio of the flow coefficient before and after the transformation of the fan satisfies
Figure PCTCN2022102929-appb-000004
When the fan blades are replaced, the following changes are also required:
①风机动叶片高度H′ 1调整，缩短改造后风机动叶片高度H′ 1，使其满足
Figure PCTCN2022102929-appb-000005
式中，H 1为风机改造前叶片高度，H′ 1为风机改造后叶片高度，单位均为mm； ①Adjust the height H′ 1 of the wind turbine blades, and shorten the height H′ 1 of the wind turbine blades after the transformation to meet the
Figure PCTCN2022102929-appb-000005
In the formula, H 1 is the height of the fan blade before modification, H′ 1 is the height of the fan blade after modification, and the unit is mm;
②风机机壳内径R′ shroud调整，缩短改造后风机机壳内径R′ shroud，使其满足R′ shroud＝R shroud+H′ 1-H 1，式中，R shroud为风机改造前机壳内径，R′ shroud为风机改造后机壳内径，单位均为mm，同时，改造前后风机叶顶间隙保持不变。 ②Adjust the inner diameter R′ shroud of the fan casing, shorten the inner diameter R′ shroud of the fan casing after the transformation, so that it meets R′ shroud = R shroud + H′ 1 -H 1 , where R shroud is the inner diameter of the fan casing before transformation , R′ shroud is the inner diameter of the casing after the transformation of the fan, and the unit is mm.
本申请进一步的改进在于，对于风机叶片更换方法，风机新型动叶具体造型方法如下：The further improvement of the present application is that, for the fan blade replacement method, the specific modeling method of the new fan blade is as follows:
(1)沿叶高方向将叶片在圆柱坐标系下等分为M个叶型截面，M取3～8之间的整数，并将M个叶型截面的叶型型线坐标展开到平面坐标系；(1) Divide the blade into M airfoil sections equally in the cylindrical coordinate system along the blade height direction, M takes an integer between 3 and 8, and expand the airfoil line coordinates of the M airfoil sections to plane coordinates Tie;
(2)确定M个叶型截面的造型方法，对于M个叶型截面，每个叶型截面的造型方法相同；(2) determine the modeling method of M airfoil sections, for M airfoil sections, the modeling method of each airfoil section is the same;
(3)确定新型动叶片第i个叶型截面的压力面型线PS′ i和吸力面型线SS′ i，构造新型动叶片第i个叶型截面的叶型型线BS′ i，根据上一步确定的新型动叶叶型截面中弧线C′ 1,i的型线，通过在中弧线C′ 1,i型线两侧叠加叶型厚度分布，并叶型截面前缘和尾缘完成前缘圆弧曲线和尾缘圆弧曲线的造型，就确定了新型动叶片第i个叶型截面的压力面型线PS′ i和吸力面型线SS′ i； (3) Determine the pressure surface profile PS′ i and the suction surface profile SS′ i of the i-th profile section of the new type of moving blade, and construct the profile line BS′ i of the i-th profile section of the new type of rotor blade, according to The profile line of the arc line C′ 1,i determined in the previous step is to superimpose the profile thickness distribution on both sides of the profile line of the center arc line C′ 1,i , and align the leading edge and trailing edge of the profile section. Complete the molding of the leading edge arc curve and the trailing edge arc curve, the pressure surface profile PS′ i and the suction surface profile SS′ i of the i-th airfoil section of the novel rotor blade are determined;
(4)将新型动叶片M个叶型截面的叶型型线BS′ i沿叶高方向积叠，生成新型动叶片三维造型，根据新型动叶片第i个叶型截面的叶型型线BS′ i，求解得到第i个叶型截面的叶型重心O′ i，将新型动叶片M个叶型截面的叶型重心O′ i作为n 阶贝塞尔曲线的控制点，i＝1,···,M，n＝M-1，O′ 1点为起点，O′ M点为终点，生成(M-1)阶贝塞尔曲线C 2，然后，将新型动叶片第i个叶型截面的叶型型线BS′ i通过贝塞尔曲线C 2沿叶高方向积叠，就完成了新型动叶片的三维造型。 (4) The blade profile lines BS′ i of the M airfoil sections of the new type of moving blade are stacked along the blade height direction to generate a three-dimensional model of the new type of moving blade. ′ i , the airfoil center of gravity O′ i of the i-th airfoil section is obtained by solving, and the airfoil center of gravity O′ i of the M airfoil sections of the new moving blade is used as the control point of the n-order Bezier curve, i=1, ···, M, n=M-1, O′ 1 point is the starting point, O′ M point is the end point, generate (M-1) order Bezier curve C 2 , and then, the i-th blade of the new rotor blade The blade profile line BS'i of the profile section is accumulated along the blade height direction through the Bezier curve C2 , and the three-dimensional modeling of the new type of moving blade is completed.
本申请进一步的改进在于，步骤(2)中，对于以第i个叶型截面，i＝1,···,M，陈述新型动叶叶型截面造型方法如下：The further improvement of the present application is that, in step (2), for the i-th airfoil section, i=1,...,M, the method of modeling the new moving blade section is stated as follows:
①采用n阶贝塞尔曲线，对原始叶片第i个叶型截面的压力面型线PS i、吸力面型线SS i进行曲线拟合，n阶贝塞尔曲线公式如下： ① Use n-order Bezier curves to perform curve fitting on the pressure surface PS i and suction surface SS i of the i-th airfoil section of the original blade. The n-order Bezier curve formula is as follows:
Figure PCTCN2022102929-appb-000006
Figure PCTCN2022102929-appb-000006
拟合过程中，保持叶片前缘点A i、叶片尾缘点B i位置不变，采用对第i个叶型截面的中弧线C 1,i两侧施加相同叶型厚度分布的方式对压力面型线PS i、吸力面型线SS i进行曲线拟合；采用最小二乘法，根据贝塞尔拟合曲线与中弧线C 1,i离散点之间误差平方和最小原则，求解贝塞尔曲线控制点P i，i＝0,1,...,n，并得到贝塞尔曲线阶数n，n≥3； During the fitting process, the positions of the blade leading edge point A i and the blade trailing edge point B i are kept unchanged, and the same blade thickness distribution is applied to both sides of the mid-arc line C 1,i of the i-th airfoil section. The pressure surface profile PS i and the suction surface profile line SS i are used for curve fitting; the least square method is used to solve the Bessel Bezier curve control point P i , i=0,1,...,n, and obtain Bezier curve order n, n≥3;
拟合完成后得到原始叶片第i个叶型截面的中弧线C 1,i和叶型厚度分布的贝塞尔拟合曲线，获取了如下参数：原始叶片第i个叶型截面的前缘进口几何角α i，尾缘出口几何角β i，叶型弦长c i，叶片最大厚度位置距叶型前缘位置a i，叶片最大厚度b max,i参数； After the fitting is completed, the middle arc C 1,i of the i-th airfoil section of the original blade and the Bezier fitting curve of the airfoil thickness distribution are obtained, and the following parameters are obtained: the leading edge of the i-th airfoil section of the original blade Inlet geometric angle α i , trailing edge outlet geometric angle β i , airfoil chord length c i , blade maximum thickness position to airfoil leading edge position a i , blade maximum thickness b max,i parameter;
②调整原始叶片第i个叶型截面中弧线C 1,i的贝塞尔拟合曲线参数，得到新型动叶片第i个叶型截面中弧线的贝塞尔拟合曲线，完成新型动叶片第i个叶型截面中弧线C′ 1,i的造型； ②Adjust the Bezier fitting curve parameters of the arc C 1,i in the i-th profile section of the original blade to obtain the Bezier fitting curve of the arc in the i-th profile section of the new moving blade, and complete the new dynamic The shape of the arc C′ 1,i in the i-th airfoil section of the blade;
新型动叶片叶型截面中弧线贝塞尔拟合曲线参数前缘进口几何角为α′ i，尾 缘出口几何角为β′ i和叶型弦长c′ i按如下公式确定： The arc Bezier fitting curve parameters of the new-type moving blade airfoil cross - section are determined by the following formula :
Figure PCTCN2022102929-appb-000007
Figure PCTCN2022102929-appb-000007
式中，k 1为叶型前缘进口几何角调整系数，k 2为叶型尾缘出口几何角调整系数，k 3为叶型弦长调整系数； In the formula, k 1 is the adjustment coefficient of the inlet geometric angle of the airfoil leading edge, k 2 is the adjustment coefficient of the geometric angle of the airfoil trailing edge outlet, and k 3 is the adjustment coefficient of the airfoil chord length;
确定了上述参数，就唯一确定了新型动叶叶型截面中弧线C′ 1,i的型线。 After the above parameters are determined, the profile line of the arc C′ 1,i in the profile section of the new rotor blade is uniquely determined.
本申请进一步的改进在于，步骤(3)中，具体实施方法如下：The further improvement of the present application is that in step (3), the specific implementation method is as follows:
①以叶片前缘点A i为坐标原点0，叶片前缘点A i到叶片尾缘点B i为x轴正方向建立坐标系，以叶型中弧线C′ 1,i上某一点在x方向距离坐标原点0的距离为x，以该点处的叶型厚度分布为b(x)，根据第二步得到的原始叶片第i个叶型截面叶型厚度分布的贝塞尔拟合曲线，得到该截面叶型厚度分布函数b(x)＝f 1(x),0≤x≤c i，令
Figure PCTCN2022102929-appb-000008
将叶型厚度分布函数无量纲化处理，整理得到函数b(j)＝f 2(j),0≤j≤1； ① Take the blade leading edge point A i as the coordinate origin 0, the blade leading edge point A i to the blade trailing edge point B i as the positive direction of the x-axis to establish a coordinate system, and take a certain point on the arc C′ 1,i of the blade shape at The distance from the coordinate origin 0 in the x direction is x, and the profile thickness distribution at this point is b(x), according to the Bessel fitting of the profile thickness distribution of the i-th profile section of the original blade obtained in the second step Curve, get the profile thickness distribution function b(x)=f 1 (x), 0≤x≤c i , let
Figure PCTCN2022102929-appb-000008
The blade thickness distribution function is dimensionless, and the function b(j)=f 2 (j), 0≤j≤1 is obtained;
②保持新型动叶片与原始叶片在第i个叶型截面相同相对弦长位置叶型的厚度分布相同，即假设新型动叶片第i个叶型截面横坐标为x′，而叶型截面弦长为c′ i，则
Figure PCTCN2022102929-appb-000009
将其整理为新型动叶片第i个叶型截面叶型厚度分布函数b(x′)＝f 3(x′),0≤x′≤c′ i，这样，就确定了新型动叶片第i个叶型截面的叶型厚度分布规律； ②Keep the thickness distribution of the blade profile at the same relative chord length position of the new rotor blade and the original blade at the i-th blade profile section, that is, assume that the abscissa of the i-th profile section of the new rotor blade is x′, and the blade profile chord length is c′ i , then
Figure PCTCN2022102929-appb-000009
It is sorted into the profile thickness distribution function b(x′)=f 3 (x′), 0≤x′≤c′ i of the i-th airfoil section of the new type of moving blade, so that the i-th blade of the new type of moving blade Airfoil thickness distribution law of each airfoil section;
③将上面步骤确定新型动叶片第i个叶型截面的叶型厚度分布规律叠加于该叶型截面的中弧线C′ 1,i型线上，生成压力面曲线和吸力面曲线，然后，在叶型截面前缘和尾缘分别构造前缘圆弧曲线和尾缘圆弧曲线，前缘圆弧曲线和尾缘圆弧曲线均为一段圆弧，分别与上面生成的压力面曲线和吸力面曲线相切，且 在该叶型截面，新型动叶片前缘圆弧曲线圆弧半径R′ 1,i满足：0＜R′ 1,i≤3％·c′ i；新型动叶片尾缘圆弧曲线圆弧半径R′ 2,i满足：0＜R′ 2,i≤2％·c′ i，这样，就确定了新型动叶片第i个叶型截面的压力面型线PS′ i和吸力面型线SS′ i，将压力面型线PS′ i和吸力面型线SS′ i组合在一起，将完成了新型动叶片第i个叶型截面的叶型型线BS′ i的构造。 ③ superimpose the profile thickness distribution law of the i-th profile section of the new moving blade determined by the above steps on the mid-arc line C' 1, i -shaped line of the profile section to generate a pressure surface curve and a suction surface curve, and then, The leading edge arc curve and the trailing edge arc curve are respectively constructed on the leading edge and the trailing edge of the airfoil section. The leading edge arc curve and the trailing edge arc curve are both arcs, which are respectively related to the pressure surface curve and suction generated above. The surface curves are tangent, and in the section of the airfoil, the arc radius R′ 1,i of the leading edge arc curve of the new type of moving blade satisfies: 0<R′ 1,i ≤ 3% c′ i ; the trailing edge of the new type of moving blade The arc radius R′ 2,i of the arc curve satisfies: 0<R′ 2,i ≤ 2% c′ i , thus, the pressure surface profile line PS′ i of the i-th airfoil section of the new moving blade is determined and the suction surface profile line SS′ i , combining the pressure surface profile line PS′ i and the suction surface profile line SS′ i to complete the blade profile line BS′ i of the i-th profile section of the new rotor blade structure.
本申请进一步的改进在于，对于风机局部改造方法，风机新型动叶具体造型方法如下：The further improvement of the present application is that, for the local modification method of the fan, the specific modeling method of the new rotor blade of the fan is as follows:
(1)按照风机叶片更换方法中(1)～(4)部分的内容完成新型动叶片的三维造型，新型动叶片原始叶高H 2与原始叶片叶高H 1保持一致，即H 2＝H 1； (1) Complete the three-dimensional modeling of the new moving blade according to the contents of parts (1) to (4) in the fan blade replacement method. The original blade height H 2 of the new moving blade is consistent with the original blade height H 1 , that is, H 2 =H 1 ;
(2)将新型动叶片叶顶处进行切割，缩短叶片高度，由第1步骤可知，风机局部改造后，风机叶片高度要缩短至H′ 1，
Figure PCTCN2022102929-appb-000010
所以对叶片顶部进行切割，将叶片固定安装于轮毂后，采用圆柱坐标系，以轮毂中心线为回转轴，将叶片顶部切掉(H 2-H′ 1)高度，H 2-H′ 1＝H 1-H′ 1，新型动叶片高度就缩短至H′ 1，叶片其它部分保持不变。 (2) Cut the top of the new moving blade to shorten the height of the blade. From the first step, it can be known that after the partial modification of the fan, the height of the fan blade should be shortened to H′ 1 ,
Figure PCTCN2022102929-appb-000010
So cut the top of the blade, fix the blade on the hub, use the cylindrical coordinate system, take the hub centerline as the axis of rotation, cut off the top of the blade to a height of (H 2 -H′ 1 ), H 2 -H′ 1 = H 1 -H′ 1 , the height of the new moving blade is shortened to H′ 1 , and the other parts of the blade remain unchanged.
本申请进一步的改进在于，对于双级动叶可调式轴流风机节能改造新型动叶造型，第一级和第二级的新型动叶造型方法相同，均按照单级动叶可调式轴流风机节能改造新型动叶造型的方法进行造型：第一级按照单级动叶可调式轴流风机节能改造新型动叶造型的方法完成单级风机新型动叶片的造型后，第二级再重复上述过程，第一级和第二级的风机动叶片造型完全相同。The further improvement of this application is that, for the energy-saving transformation of the new type of rotor blade shape of the double-stage movable blade adjustable axial flow fan, the first-stage and second-stage new type of movable blade modeling methods are the same, and they are all in accordance with the single-stage movable blade adjustable axial flow fan. Modeling with the method of energy-saving transformation of the new type of moving blade: the first stage follows the method of energy-saving transformation of the single-stage adjustable axial flow fan to complete the shape of the new type of moving blade of the single-stage fan, and the second stage repeats the above process , the shape of the first-stage and second-stage wind turbine blades is exactly the same.
本申请至少具有如下有益的技术效果：The application has at least the following beneficial technical effects:
本申请提供的一种电站动叶可调式轴流风机节能改造新型动叶造型方法，根据动叶可调式轴流风机节能改造前、后风机技术参数确定风机改造方法，然后，针对不同的风机改造方法确定相应的新型动叶造型方法。上述工作完成后， 依据上面确定的方法就可以实施动叶可调式轴流风机节能改造及新型动叶片造型。This application provides a new type of moving blade modeling method for energy-saving transformation of axial flow fans with adjustable moving blades in power stations. According to the technical parameters of the fans before and after the energy-saving transformation of axial flow fans with adjustable moving blades, the fan transformation method is determined, and then, for different fan transformations Methods Determine the corresponding new rotor blade modeling method. After the above work is completed, the energy-saving transformation of the axial flow fan with adjustable moving blades and the new shape of the moving blades can be implemented according to the method determined above.
该动叶可调式轴流风机新型动叶造型方法，可以根据用户实际需求，个性化开发定制动叶可调式轴流风机节能改造新型动叶片，所开发的新型动叶片应用于动叶可调式轴流风机后，在降低风机出力的基础上，可以实现风机深度节能，同时可以有效改善风机调节性能，扩大风机运行范围，风机节能改造效果显著。The new type of blade modeling method for the adjustable blade axial fan can be customized according to the actual needs of users, and the new type of blade for energy-saving transformation of the axial fan with adjustable blade can be customized. The new type of blade developed is applied to the shaft with adjustable blade After the flow fan, on the basis of reducing the output of the fan, the deep energy saving of the fan can be realized, and at the same time, the adjustment performance of the fan can be effectively improved, the operating range of the fan can be expanded, and the energy-saving transformation effect of the fan is remarkable.
附图说明Description of drawings
图1为本申请专利的叶型截面造型示意图；Fig. 1 is the schematic diagram of the airfoil section modeling of the patent of the present application;
图2为本申请专利的叶型截面叶型厚度分布示意图。Fig. 2 is a schematic diagram of the thickness distribution of the airfoil section of the patent application.
其中，M为叶片造型的叶型截面总数目，i为叶型截面序号，
Figure PCTCN2022102929-appb-000011
为改造前风机TB点选型参数对应的流量系数，φ 1为改造前风机TB点选型参数对应的压力系数，
Figure PCTCN2022102929-appb-000012
为改造后风机TB点选型参数对应的流量系数，φ 2为改造后风机TB点选型参数对应的压力系数。 Among them, M is the total number of airfoil sections of the blade shape, i is the serial number of the airfoil section,
Figure PCTCN2022102929-appb-000011
is the flow coefficient corresponding to the fan TB point selection parameter before transformation, φ 1 is the pressure coefficient corresponding to the fan TB point selection parameter before transformation,
Figure PCTCN2022102929-appb-000012
is the flow coefficient corresponding to the type selection parameter of the TB point of the modified fan, and φ 2 is the pressure coefficient corresponding to the type selection parameter of the modified fan point TB.
H 1为风机改造前动叶片高度，H′ 1为风机改造后动叶片高度，R shroud为风机改造前机壳内径，R′ shroud为风机改造后机壳内径，以上单位均为mm。 H 1 is the height of the moving blade before the fan modification, H′ 1 is the height of the moving blade after the fan modification, R shroud is the inner diameter of the fan casing before the fan modification, and R′ shroud is the inner diameter of the fan casing after the fan modification, and the above units are mm.
n为贝塞尔曲线阶数，P i为贝塞尔曲线控制点，b(x)＝f 1(x)为原始叶片第i叶型截面的叶型厚度分布函数，b(x)＝f 2(x)为原始叶片第i叶型截面的无量纲化叶型厚度分布函数，b(x)＝f 3(x)为新型动叶片第i叶型截面的厚度分布函数。 n is the order of the Bezier curve, P i is the control point of the Bezier curve, b(x)=f 1 (x) is the profile thickness distribution function of the i-th profile section of the original blade, b(x)=f 2 (x) is the dimensionless profile thickness distribution function of the i-th profile section of the original blade, and b(x)=f 3 (x) is the thickness distribution function of the i-th profile profile section of the new rotor blade.
图1中均为原始叶片第i叶型截面的参数，其中，A i为叶型前缘点，B i为叶型尾缘点，C 1,i为叶型中弧线型线，PS i为叶型压力面型线，SS i为叶型吸力面型线。 Figure 1 shows the parameters of the i-th airfoil section of the original blade, where A i is the leading edge point of the airfoil, B i is the trailing edge point of the airfoil, C 1,i is the arc shape line of the airfoil, and PS i is the shape line of the pressure surface of the airfoil, and SS i is the shape line of the suction surface of the airfoil.
α i为叶型前缘进口几何角，β i为叶型尾缘出口几何角，以上单位均为°。 α i is the inlet geometric angle of the leading edge of the airfoil, and β i is the geometric angle of the airfoil trailing edge outlet, and the units above are °.
a i为叶型最大厚度位置距叶型前缘距离，b max,i为叶型最大厚度，c i为叶型弦长，R 1,i为原始叶片前缘圆弧曲线圆弧半径，R 2,i为原始叶片尾缘圆弧曲线圆弧半径，以上单位均为mm。 a i is the distance between the position of the maximum thickness of the airfoil and the leading edge of the airfoil, b max,i is the maximum thickness of the airfoil, c i is the chord length of the airfoil, R 1,i is the arc radius of the original blade leading edge arc curve, R 2, i is the arc radius of the original blade trailing edge arc curve, and the above units are mm.
图2中均为原始叶片第i叶型截面的参数，其中，叶片前缘点A i为坐标原点0，x为叶型中弧线C′ 1,i上某一点在x方向距离坐标原点0的距离，b(x)为横坐标x位置对应的叶型厚度分布。 Figure 2 is the parameters of the i-th airfoil section of the original blade, where the leading edge point A i of the blade is the coordinate origin 0, x is the arc line C′ 1 in the airfoil shape, and a point on i is far from the coordinate origin 0 in the x direction b(x) is the blade thickness distribution corresponding to the x-coordinate position.
以下参数均为新型动叶片第i叶型截面的参数：The following parameters are the parameters of the i-th airfoil section of the new type of moving blade:
C′ 1,i为叶型中弧线型线，PS′ i为叶型压力面型线，SS′ i为叶型吸力面型线。 C′ 1,i is the profile line of the airfoil center arc, PS′ i is the profile line of the pressure surface of the blade profile, and SS′ i is the profile line of the suction surface of the blade profile.
α′ i为叶型前缘进口几何角，β′ i为叶型尾缘出口几何角，以上单位均为°；k 1为叶型前缘进口几何角调整系数，k 2为叶型尾缘出口几何角调整系数。 α′ i is the inlet geometric angle of the airfoil leading edge, β′ i is the geometric angle of the airfoil trailing edge outlet, and the units above are °; k 1 is the adjustment coefficient of the airfoil leading edge inlet geometric angle, and k 2 is the airfoil trailing edge Export geometry angle adjustment factor.
a′ i为叶型最大厚度位置距叶型前缘距离，b′ max,i为叶型最大厚度，c′ i为叶型弦长，R′ 1,i为叶型前缘圆弧曲线圆弧半径，R′ 2,i为叶型尾缘圆弧曲线圆弧半径，以上单位均为mm；k 3为叶型弦长调整系数。 a' i is the distance from the position of the maximum thickness of the airfoil to the leading edge of the airfoil, b' max,i is the maximum thickness of the airfoil, c' i is the chord length of the airfoil, R' 1,i is the arc curve of the leading edge of the airfoil Arc radius, R′ 2, i is the arc radius of the arc curve of the trailing edge of the blade profile, and the above units are mm; k 3 is the adjustment coefficient of the blade profile chord length.
x′为叶型中弧线C′ 1,i上某一点在x方向距离坐标原点0的距离，b(x′)为横坐标x′位置对应的叶型厚度分布。 x' is the distance from a point on the arc C' 1, i in the blade shape to the coordinate origin 0 in the x direction, and b(x') is the thickness distribution of the blade shape corresponding to the position of the abscissa x'.
O′ i为叶型重心，C 2为叶型沿叶高方向积叠贝塞尔曲线。 O′ i is the center of gravity of the blade shape, and C 2 is the Bezier curve stacked along the blade height direction of the blade shape.
具体实施方式Detailed ways
下面将参照附图更详细地描述本公开的示例性实施例。虽然附图中显示了本公开的示例性实施例，然而应当理解，可以以各种形式实现本公开而不应被这里阐述的实施例所限制。相反，提供这些实施例是为了能够更透彻地理解本公开，并且能够将本公开的范围完整的传达给本领域的技术人员。需要说明的 是，在不冲突的情况下，本申请中的实施例及实施例中的特征可以相互组合。下面将参考附图并结合实施例来详细说明本申请。Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.
一种电站动叶可调式轴流风机节能改造新型动叶造型方法，包括：A new type of rotor blade modeling method for energy-saving transformation of an axial flow fan with adjustable rotor blades in a power station, including:
首先，根据动叶可调式轴流风机节能改造前、后风机技术参数确定风机改造方法；其次，针对不同风机改造方法，确定相应的新型动叶造型方法；最后，根据上面确定的风机改造方案和新型动叶造型方法，实施风机节能改造。First, according to the fan technical parameters before and after the energy-saving transformation of the axial flow fan with adjustable movable blades, determine the fan transformation method; secondly, according to different fan transformation methods, determine the corresponding new dynamic blade modeling method; finally, according to the fan transformation plan determined above and A new type of moving blade modeling method is used to implement energy-saving renovation of fans.
(一)对于单级动叶可调式轴流风机节能改造新型动叶造型，具体实施方法如下：(1) For the energy-saving transformation of the single-stage movable blade adjustable axial flow fan with a new type of movable blade shape, the specific implementation method is as follows:
1、确定风机改造技术方案。根据动叶可调式轴流风机改造前风机TB点选型参数对应的流量系数
Figure PCTCN2022102929-appb-000013
压力系数φ 1，风机节能改造后TB点选型参数对应的流量系数
Figure PCTCN2022102929-appb-000014
压力系数φ 2确定风机改造技术方案。风机改造技术方案分为风机叶片更换和风机局部改造两种方法，两种方法分别陈述如下： 1. Determine the technical plan for fan transformation. According to the flow coefficient corresponding to the fan TB point selection parameters before the transformation of the movable blade adjustable axial flow fan
Figure PCTCN2022102929-appb-000013
Pressure coefficient φ 1 , flow coefficient corresponding to TB point selection parameters after fan energy-saving transformation
Figure PCTCN2022102929-appb-000014
The pressure coefficient φ 2 determines the technical scheme of fan transformation. The technical plan for fan transformation is divided into two methods: fan blade replacement and partial fan modification. The two methods are respectively stated as follows:
(1)风机叶片更换方法。当风机改造前、后流量系数比满足
Figure PCTCN2022102929-appb-000015
时，仅需更换风机全部动叶片，而风机轮毂和机壳等其它结构的尺寸均保持不变。 (1) How to replace fan blades. When the ratio of flow coefficient before and after fan modification satisfies
Figure PCTCN2022102929-appb-000015
At this time, only all the moving blades of the fan need to be replaced, while the dimensions of other structures such as the hub and casing of the fan remain unchanged.
(2)风机局部改造方法。当风机改造前、后流量系数比满足
Figure PCTCN2022102929-appb-000016
时，在风机叶片更换的同时，还需要进行如下改动： (2) Partial transformation method of fan. When the ratio of flow coefficient before and after fan modification satisfies
Figure PCTCN2022102929-appb-000016
When the fan blades are replaced, the following changes are also required:
①风机动叶片高度H′ 1调整。缩短改造后风机动叶片高度H′ 1，使其满足
Figure PCTCN2022102929-appb-000017
式中，H 1为风机改造前叶片高度，H′ 1为风机改造后叶片高度，单位均为mm。 ①Adjustment of the height H′ 1 of the fan blades. Shorten the height H′ 1 of the wind turbine blades after transformation to meet
Figure PCTCN2022102929-appb-000017
In the formula, H 1 is the height of the fan blade before modification, H′ 1 is the height of the fan blade after modification, and the unit is mm.
②风机机壳内径R′ shroud调整。缩短改造后风机机壳内径R′ shroud，使其满足R′ shroud＝R shroud+H′ 1-H 1。式中，R shroud为风机改造前机壳内径，R′ shroud为风机改造后机 壳内径，单位均为mm。同时，改造前后风机叶顶间隙保持不变。 ②Adjust the inner diameter R′ shroud of the fan casing. Shorten the inner diameter R′ shroud of the modified fan casing to satisfy R′ shroud =R shroud +H′ 1 −H 1 . In the formula, R shroud is the inner diameter of the casing of the fan before modification, and R′ shroud is the inner diameter of the casing of the fan after modification, and the unit is mm. At the same time, the fan blade top clearance remains unchanged before and after the transformation.
2、确定风机新型动叶造型方法。如上所述，风机改造技术方案分为风机叶片更换和风机局部改造两种方法，两种方法的新型动叶片造型方法有所不同，下面分别进行论述。2. Determine the new type of fan blade modeling method. As mentioned above, the technical scheme of fan transformation is divided into two methods: fan blade replacement and fan partial transformation. The new moving blade modeling methods of the two methods are different, which will be discussed separately below.
I.对于风机叶片更换方法，风机新型动叶具体造型方法如下：I. Regarding the replacement method of fan blades, the specific modeling method of the new rotor blades of the fan is as follows:
(1)沿叶高方向将叶片在圆柱坐标系下等分为M个叶型截面，M取3～8之间的整数，并将M个叶型截面的叶型型线坐标展开到平面坐标系。(1) Divide the blade into M airfoil sections equally in the cylindrical coordinate system along the blade height direction, M takes an integer between 3 and 8, and expand the airfoil line coordinates of the M airfoil sections to plane coordinates Tie.
(2)确定M个叶型截面的造型方法。对于M个叶型截面，每个叶型截面的造型方法相同，下面以第i个(i＝1,···,M)叶型截面为例，陈述新型动叶叶型截面造型方法如下：(2) Determine the modeling method of M airfoil sections. For M airfoil sections, the modeling method of each airfoil section is the same, and the i-th (i=1,..., M) airfoil section is taken as an example below to state the modeling method of the new moving blade airfoil section as follows:
①采用n阶贝塞尔曲线，对原始叶片第i个叶型截面的压力面型线PS i、吸力面型线SS i进行曲线拟合。n阶贝塞尔曲线公式如下： ① Using n-order Bezier curves, curve fitting is carried out on the pressure surface PS i and the suction surface SS i of the i-th airfoil section of the original blade. The n-order Bezier curve formula is as follows:
Figure PCTCN2022102929-appb-000018
Figure PCTCN2022102929-appb-000018
拟合过程中，保持叶片前缘点A i、叶片尾缘点B i位置不变，采用对第i个叶型截面的中弧线C 1,i两侧施加相同叶型厚度分布的方式对压力面型线PS i、吸力面型线SS i进行曲线拟合；采用最小二乘法，根据贝塞尔拟合曲线与中弧线C 1,i离散点之间误差平方和最小原则，求解贝塞尔曲线控制点P i，i＝0,1,...,n，并得到贝塞尔曲线阶数n(通常情况下，n≥3)。 During the fitting process, the positions of the blade leading edge point A i and the blade trailing edge point B i are kept unchanged, and the same blade thickness distribution is applied to both sides of the mid-arc line C 1,i of the i-th airfoil section. The pressure surface profile PS i and the suction surface profile line SS i are used for curve fitting; the least square method is used to solve the Bessel The Bezier curve control point P i , i=0, 1,...,n, and the Bezier curve order n (usually, n≥3) is obtained.
拟合完成后得到原始叶片第i个叶型截面的中弧线C 1,i和叶型厚度分布的贝塞尔拟合曲线，获取了如下参数：原始叶片第i个叶型截面的前缘进口几何角α i，尾缘出口几何角β i，叶型弦长c i，叶片最大厚度位置距叶型前缘位置a i，叶片最 大厚度b max,i参数。 After the fitting is completed, the middle arc C 1,i of the i-th airfoil section of the original blade and the Bezier fitting curve of the airfoil thickness distribution are obtained, and the following parameters are obtained: the leading edge of the i-th airfoil section of the original blade Inlet geometric angle α i , trailing edge outlet geometric angle β i , airfoil chord length c i , blade maximum thickness position from airfoil leading edge position a i , blade maximum thickness b max,i parameters.
②调整原始叶片第i个叶型截面中弧线C 1,i的贝塞尔拟合曲线参数，得到新型动叶片第i个叶型截面中弧线的贝塞尔拟合曲线，完成新型动叶片第i个叶型截面中弧线C′ 1,i的造型。 ②Adjust the Bezier fitting curve parameters of the arc C 1,i in the i-th profile section of the original blade to obtain the Bezier fitting curve of the arc in the i-th profile section of the new moving blade, and complete the new dynamic The shape of the arc C′ 1,i in the i-th airfoil section of the blade.
新型动叶片叶型截面中弧线贝塞尔拟合曲线参数前缘进口几何角为α′ i，尾缘出口几何角为β′ i和叶型弦长c′ i按如下公式确定： The arc Bezier fitting curve parameters of the new-type moving blade airfoil cross - section are determined by the following formula :
Figure PCTCN2022102929-appb-000019
Figure PCTCN2022102929-appb-000019
式中，k 1为叶型前缘进口几何角调整系数，k 2为叶型尾缘出口几何角调整系数，k 3为叶型弦长调整系数。 In the formula, k 1 is the adjustment coefficient of the inlet geometric angle of the airfoil leading edge, k 2 is the adjustment coefficient of the geometric angle of the airfoil trailing edge outlet, and k 3 is the adjustment coefficient of the airfoil chord length.
确定了上述参数，就唯一确定了新型动叶叶型截面中弧线C′ 1,i的型线。 After the above parameters are determined, the profile line of the arc C′ 1,i in the profile section of the new rotor blade is uniquely determined.
(3)确定新型动叶片第i个叶型截面的压力面型线PS′ i和吸力面型线SS′ i，构造新型动叶片第i个叶型截面的叶型型线BS′ i。根据上一步确定的新型动叶叶型截面中弧线C′ 1,i的型线，通过在中弧线C′ 1,i型线两侧叠加叶型厚度分布，并叶型截面前缘和尾缘完成前缘圆弧曲线和尾缘圆弧曲线的造型，就确定了新型动叶片第i个叶型截面的压力面型线PS′ i和吸力面型线SS′ i。具体实施方法如下： (3) Determine the pressure surface profile PS′ i and the suction surface profile SS′ i of the i-th profile section of the new rotor blade, and construct the profile line BS′ i of the i-th profile section of the new rotor blade. According to the profile line of the mid-arc line C′ 1,i determined in the previous step, by superimposing the profile thickness distribution on both sides of the mid-arc line C′ 1,i , and combining the leading edge and After the trailing edge completes the shape of the leading edge arc curve and the trailing edge arc curve, the pressure surface profile line PS′ i and the suction surface profile line SS′ i of the i-th airfoil section of the new rotor blade are determined. The specific implementation method is as follows:
①以叶片前缘点A i为坐标原点0，叶片前缘点A i到叶片尾缘点B i为x轴正方向建立坐标系，以叶型中弧线C′ 1,i上某一点在x方向距离坐标原点0的距离为x，以该点处的叶型厚度分布为b(x)。根据第二步得到的原始叶片第i个叶型截面叶型厚度分布的贝塞尔拟合曲线，可以得到该截面叶型厚度分布函数b(x)＝f 1(x),0≤x≤c i，令
Figure PCTCN2022102929-appb-000020
将叶型厚度分布函数无量纲化处理，整理得到函数 b(j)＝f 2(j),0≤j≤1。 ① Take the blade leading edge point A i as the coordinate origin 0, the blade leading edge point A i to the blade trailing edge point B i as the positive direction of the x-axis to establish a coordinate system, and take a certain point on the arc C′ 1,i of the blade shape at The distance from the coordinate origin 0 in the x direction is x, and the blade thickness distribution at this point is b(x). According to the Bezier fitting curve of the profile thickness distribution of the i-th profile of the original blade obtained in the second step, the profile thickness distribution function b(x)=f 1 (x), 0≤x≤ c i , let
Figure PCTCN2022102929-appb-000020
The airfoil thickness distribution function is non-dimensionalized, and the function b(j)=f 2 (j), 0≤j≤1 is obtained.
②本申请保持新型动叶片与原始叶片在第i个叶型截面相同相对弦长位置叶型的厚度分布相同，即假设新型动叶片第i个叶型截面横坐标为x′，而叶型截面弦长为c′ i，则
Figure PCTCN2022102929-appb-000021
将其整理为新型动叶片第i个叶型截面叶型厚度分布函数b(x′)＝f 3(x′),0≤x′≤c′ i。这样，就确定了新型动叶片第i个叶型截面的叶型厚度分布规律。 ② This application maintains that the thickness distribution of the blade profile at the same relative chord length position of the new rotor blade and the original blade at the i-th blade profile section is the same, that is, it is assumed that the abscissa of the i-th profile section of the new rotor blade is x′, and the blade profile section The length of the chord is c′ i , then
Figure PCTCN2022102929-appb-000021
It is sorted into the profile thickness distribution function b(x′)=f 3 (x′), 0≤x′≤c′ i of the i-th profile section of the new rotor blade. In this way, the profile thickness distribution law of the i-th profile section of the new rotor blade is determined.
③将上面步骤确定新型动叶片第i个叶型截面的叶型厚度分布规律叠加于该叶型截面的中弧线C′ 1,i型线上，生成压力面曲线和吸力面曲线。然后，在叶型截面前缘和尾缘分别构造前缘圆弧曲线和尾缘圆弧曲线，前缘圆弧曲线和尾缘圆弧曲线均为一段圆弧，分别与上面生成的压力面曲线和吸力面曲线相切，且在该叶型截面，新型动叶片前缘圆弧曲线圆弧半径R′ 1,i满足：0＜R′ 1,i≤3％·c′ i；新型动叶片尾缘圆弧曲线圆弧半径R′ 2,i满足：0＜R′ 2,i≤2％·c′ i。这样，就确定了新型动叶片第i个叶型截面的压力面型线PS′ i和吸力面型线SS′ i，将压力面型线PS′ i和吸力面型线SS′ i组合在一起，将完成了新型动叶片第i个叶型截面的叶型型线BS′ i的构造。 ③ Superimpose the profile thickness distribution law of the i-th airfoil section of the new rotor blade determined by the above steps on the mid-arc C′ 1, i -line of the airfoil section to generate a pressure surface curve and a suction surface curve. Then, the leading edge arc curve and the trailing edge arc curve are respectively constructed on the leading edge and the trailing edge of the airfoil section. It is tangent to the suction surface curve, and in the profile section, the arc radius R′ 1,i of the arc curve at the leading edge of the new type of moving blade satisfies: 0<R′ 1,i ≤ 3% c′ i ; the new type of moving blade The arc radius R′ 2,i of the arc curve of the trailing edge satisfies: 0<R′ 2,i ≤2%·c′ i . In this way, the pressure surface profile PS′ i and the suction surface profile SS′ i of the i-th airfoil section of the new rotor blade are determined, and the pressure surface profile PS′ i and the suction surface profile SS′ i are combined , will complete the construction of the profile line BS′ i of the i-th profile section of the new rotor blade.
(4)将新型动叶片M个叶型截面的叶型型线BS′ i(i＝1,···,M)沿叶高方向积叠，生成新型动叶片三维造型。根据新型动叶片第i个叶型截面的叶型型线BS′ i，求解得到第i个叶型截面的叶型重心O′ i，将新型动叶片M个叶型截面的叶型重心O′ i(i＝1,···,M)作为n阶(n＝M-1)贝塞尔曲线的控制点，O′ 1点为起点，O′ M点为终点，生成(M-1)阶贝塞尔曲线C 2。然后，将新型动叶片第i个叶型截面的叶型型线BS′ i通过贝塞尔曲线C 2沿叶高方向积叠，就完成了新型动叶片的三维造型。 (4) The profile lines BS′ i (i=1,···,M) of the M profile sections of the new rotor blade are stacked along the blade height direction to generate a three-dimensional model of the new rotor blade. According to the airfoil line BS′ i of the i-th airfoil section of the new moving blade, the airfoil center of gravity O′ i of the i-th airfoil section is obtained by solving, and the airfoil center of gravity O′ of the new moving blade’s M airfoil sections i (i=1,...,M) is used as the control point of n-order (n=M-1) Bezier curve, O' 1 point is the starting point, O' M point is the end point, and (M-1) is generated order Bezier curve C 2 . Then, the profile line BS'i of the i-th profile section of the new rotor blade is stacked along the blade height direction through the Bezier curve C2 , and the three-dimensional modeling of the new rotor blade is completed.
II.对于风机局部改造方法，风机新型动叶具体造型方法如下：II. For the local modification method of the fan, the specific modeling method of the new rotor blade of the fan is as follows:
(1)按照第I步骤中(1)～(4)部分的内容完成新型动叶片的三维造型， 新型动叶片原始叶高H 2与原始叶片叶高H 1保持一致，即H 2＝H 1。 (1) Complete the three-dimensional modeling of the new moving blade according to the contents of (1) to (4) in the first step. The original blade height H 2 of the new moving blade is consistent with the original blade height H 1 , that is, H 2 =H 1 .
(2)将新型动叶片叶顶处进行切割，缩短叶片高度。由第1步骤可知，风机局部改造后，风机叶片高度要缩短至
Figure PCTCN2022102929-appb-000022
所以需要对叶片顶部进行切割，将叶片固定安装于轮毂后，采用圆柱坐标系，以轮毂中心线为回转轴，将叶片顶部切掉(H 2-H′ 1)高度(H 2-H′ 1＝H 1-H′ 1)，新型动叶片高度就缩短至H′ 1，叶片其它部分保持不变。这样，就完成了新型动叶片的三维造型。 (2) Cut the top of the new moving blade to shorten the height of the blade. From the first step, it can be known that after the partial modification of the fan, the height of the fan blades should be shortened to
Figure PCTCN2022102929-appb-000022
Therefore, it is necessary to cut the top of the blade. After the blade is fixedly installed on the hub, use the cylindrical coordinate system and take the hub centerline as the axis of rotation to cut off the top of the blade (H 2 -H′ 1 ) to a height (H 2 -H′ 1 =H 1 -H′ 1 ), the height of the new moving blade is shortened to H′ 1 , and the other parts of the blade remain unchanged. In this way, the three-dimensional modeling of the new moving blade is completed.
(二)对于双级动叶可调式轴流风机节能改造新型动叶造型，第一级和第二级的新型动叶造型方法相同，均按照第(一)步骤的方法进行造型：第一级按照第(一)步骤的方法完成单级风机新型动叶片的造型后，第二级再重复上述过程，第一级和第二级的风机动叶片造型完全相同。这样，就完成了双级动叶可调式轴流风机节能改造新型动叶片的造型。(2) For the new rotor blade shape of the energy-saving retrofit of the double-stage movable blade adjustable axial flow fan, the modeling method of the new rotor blade of the first stage and the second stage is the same, and the modeling method is carried out according to the method of the first step: the first stage After completing the shape of the new moving blades of the single-stage fan according to the method of the first step, repeat the above process for the second stage, and the shapes of the moving blades of the first and second stages are exactly the same. In this way, the shape of the new type of movable blade for energy-saving transformation of the two-stage movable blade adjustable axial flow fan is completed.
实施例Example
国内某600MW机组送风机为单级动叶可调式轴流风机，风机动叶数量为22片，叶轮直径为2660mm，风机机壳内径R shroud＝1330mm，叶片高度H 1＝630mm，电机额定转速为990r/min，风机TB点流量为232m 3/s，TB点压力为4730Pa，进气密度为1.183kg/m 3，节能改造后，风机TB点流量为220m 3/s，TB点压力为3500Pa，进气密度为1.146kg/m 3。经过计算，得到改造前风机TB点选型参数对应的流量系数
Figure PCTCN2022102929-appb-000023
改造前风机TB点选型参数对应的压力系数φ 1＝0.421，改造后风机TB点选型参数对应的流量系数
Figure PCTCN2022102929-appb-000024
改造后风机TB点选型参数对应的压力系数φ 2＝0.321。依次按照下面的步骤实施动叶可调式轴流风机新型动叶造型： The blower of a domestic 600MW unit is a single-stage movable blade adjustable axial flow fan, the number of fan blades is 22, the diameter of the impeller is 2660mm, the inner diameter of the fan casing R shroud = 1330mm, the blade height H 1 = 630mm, and the rated speed of the motor is 990r /min, the flow rate at point TB of the fan is 232m 3 /s, the pressure at point TB is 4730Pa , and the intake air density is 1.183kg/m 3 . The gas density is 1.146kg/m 3 . After calculation, the flow coefficient corresponding to the fan TB point selection parameters before transformation is obtained
Figure PCTCN2022102929-appb-000023
The pressure coefficient φ 1 = 0.421 corresponding to the fan TB point selection parameter before transformation, and the flow coefficient corresponding to the fan TB point selection parameter after transformation
Figure PCTCN2022102929-appb-000024
The pressure coefficient φ 2 corresponding to the type selection parameter of fan TB point after transformation is 0.321. Follow the steps below to implement the new rotor blade shape of the axial flow fan with adjustable rotor blades:
1、风机改造前、后流量系数比
Figure PCTCN2022102929-appb-000025
满足
Figure PCTCN2022102929-appb-000026
条件。因此， 采用风机叶片更换方法实施风机节能改造。 1. Ratio of flow coefficient before and after fan transformation
Figure PCTCN2022102929-appb-000025
satisfy
Figure PCTCN2022102929-appb-000026
condition. Therefore, fan blade replacement method is adopted to carry out fan energy-saving renovation.
2、选取M＝6，即沿叶高方向将叶片在圆柱坐标系下等分为6个叶型截面。2. Select M=6, that is, divide the blade into 6 blade sections equally in the cylindrical coordinate system along the blade height direction.
3、以第1个叶型截面(即叶根截面)为例，实施单个叶型截面的造型：3. Taking the first airfoil section (that is, the blade root section) as an example, implement the modeling of a single airfoil section:
(1)采用n阶贝塞尔曲线对第1个叶型截面的压力面型线PS 1、吸力面型线SS 1进行曲线拟合，求解得到贝塞尔曲线阶数n＝8，并得到贝塞尔曲线控制点P i，i＝0,1,...,8；拟合完成后，得到原始叶片第1个叶型截面的中弧线C 1,1和叶型厚度分布的贝塞尔拟合曲线，并得到第1个叶型截面的下列参数：前缘进口几何角α i＝31°，尾缘出口几何角β i＝37°，叶型弦长c i＝348.3mm，叶片最大厚度位置距叶型前缘位置a i＝111.5mm，叶片最大厚度b max,i＝36.6mm。 (1) Use the n-order Bezier curve to fit the pressure surface profile line PS 1 and the suction surface profile line SS 1 of the first airfoil section, and obtain the Bezier curve order n=8, and get Bezier curve control point P i , i=0,1,...,8; after the fitting is completed, the middle arc C 1,1 of the first profile section of the original blade and the Bezier profile of the profile thickness distribution are obtained Searle fit the curve, and obtained the following parameters of the first airfoil section: leading edge inlet geometric angle α i =31°, trailing edge outlet geometric angle β i =37°, airfoil chord length c i =348.3mm, The position of the maximum thickness of the blade is a i =111.5 mm from the position of the leading edge of the blade profile, and the maximum thickness of the blade b max,i =36.6 mm.
(2)调整原始叶片第1个叶型截面中弧线C 1,1的贝塞尔拟合曲线参数，选择叶型前缘进口几何角调整系数k 1＝0.95，叶型尾缘出口几何角调整系数k 2＝0.88，叶型弦长调整系数k 3＝0.95，得到新型动叶片第1个叶型截面的前缘进口几何角为α′ i＝29.5°，尾缘出口几何角为β′ i＝32.6°和叶型弦长c′ i＝330.9mm。这样，就完成了新型动叶片第1个叶型截面中弧线C′ 1,1的造型。 (2) Adjust the Bezier fitting curve parameters of the arc C 1,1 in the first airfoil section of the original blade, select the adjustment coefficient k 1 =0.95 for the inlet geometric angle of the airfoil leading edge, and select the geometric angle of the airfoil trailing edge outlet geometric angle The adjustment coefficient k 2 =0.88, the blade profile chord length adjustment coefficient k 3 =0.95, the leading edge inlet geometric angle of the first airfoil section of the new rotor blade is α′ i =29.5°, and the trailing edge outlet geometric angle is β′ i =32.6° and airfoil chord length c′ i =330.9mm. In this way, the shape of the arc C′ 1,1 in the first airfoil section of the new type of moving blade is completed.
(3)根据第I部分第(3)步骤第③步的方法，在新型动叶片第1个叶型截面中弧线C′ 1,1叠加叶型厚度分布；然后，构造前缘圆弧曲线(前缘圆弧曲线圆弧半径R′ 1,1＝3.6mm)和尾缘圆弧曲线(尾缘圆弧曲线圆弧半径R′ 2,1＝2mm)。这样，就完成了新型动叶片第1个叶型截面的叶型型线BS′ 1的构造。 (3) According to the method of step ③ in step (3) of Part I, the arc C′ 1,1 in the first airfoil section of the new rotor blade is superimposed on the thickness distribution of the airfoil; then, construct the arc curve of the leading edge (Arc radius R′ 1,1 = 3.6mm for leading edge arc curve) and trailing edge arc curve (arc radius R′ 2,1 = 2mm for trailing edge arc curve). In this way, the construction of the profile line BS'1 of the first profile section of the new rotor blade is completed.
4、按照上面步骤的方法，完成新型动叶片其它几个叶型截面的叶型型线BS′ i(i＝2,...,6)的构造。 4. According to the method in the above steps, complete the construction of the profile lines BS' i (i=2,...,6) of several other profile sections of the new rotor blade.
5、根据第I部分第(4)步骤的方法，将新型动叶片6个叶型截面的叶型型线BS′ i(i＝1,···,6)沿叶高方向积叠，生成新型动叶片三维造型。 5. According to the method of step (4) of part I, the profile lines BS′ i (i=1, , 6) of the 6 profile sections of the novel rotor blade are stacked along the blade height direction to generate Three-dimensional modeling of new moving blades.
经过上面的步骤，就完成了动叶可调式轴流风机节能改造新型动叶片造型。 所开发的新型动叶片应用于动叶可调式轴流风机后，风机不仅可以满足节能改造后新选型工况点的出力要求，而且风机综合能耗降低了15％以上，风机动叶角度调节范围提高了10％以上，风机运行经济性和设备适用性得到了显著提升，本次风机节能改造效果显著。After the above steps, the new type of moving blade shape of the energy-saving transformation of the axial flow fan with adjustable moving blades is completed. After the developed new type of moving blade is applied to the axial flow fan with adjustable moving blade, the fan can not only meet the output requirements of the new model selection point after the energy-saving transformation, but also reduce the comprehensive energy consumption of the fan by more than 15%. The scope has been increased by more than 10%, the operation economy of the fan and the applicability of the equipment have been significantly improved, and the energy-saving transformation of the fan has achieved remarkable results.
虽然，上文中已经用一般性说明及具体实施方案对本申请作了详尽的描述，但在本申请基础上，可以对之作一些修改或改进，这对本领域技术人员而言是显而易见的。因此，在不偏离本申请精神的基础上所做的这些修改或改进，均属于本申请要求保护的范围。Although the present application has been described in detail with general descriptions and specific implementations above, it is obvious to those skilled in the art that some modifications or improvements can be made on the basis of the present application. Therefore, the modifications or improvements made on the basis of not departing from the spirit of the present application all belong to the protection scope of the present application.

Claims (8)

  1. 一种电站动叶可调式轴流风机节能改造新型动叶造型方法，其特征在于，包括：首先，根据动叶可调式轴流风机节能改造前、后风机技术参数确定风机改造方法；其次，针对不同风机改造方法，确定相应的新型动叶造型方法；最后，根据上面确定的风机改造方案和新型动叶造型方法，实施风机节能改造。A new type of rotor blade modeling method for energy-saving renovation of an axial flow fan with adjustable rotor blades in a power station, which is characterized in that it includes: firstly, determining the fan renovation method according to the technical parameters of the fan before and after the energy-saving renovation of the axial fan with adjustable rotor blades; secondly, for According to different wind turbine transformation methods, determine the corresponding new moving blade modeling method; finally, implement fan energy-saving transformation according to the fan transformation plan and new moving blade modeling method determined above.
  2. 根据权利要求1所述的一种电站动叶可调式轴流风机节能改造新型动叶造型方法，其特征在于，对于单级动叶可调式轴流风机节能改造新型动叶造型，具体实现方法如下：According to claim 1, a new type of moving blade modeling method for energy-saving transformation of an axial flow fan with adjustable moving blades in a power station is characterized in that, for a new type of moving blade shape for energy-saving transformation of an axial flow fan with adjustable moving blades at a single stage, the specific implementation method is as follows :
    步骤1、确定风机改造技术方案，根据动叶可调式轴流风机改造前风机TB点选型参数对应的流量系数
    Figure PCTCN2022102929-appb-100001
    压力系数φ 1，风机节能改造后TB点选型参数对应的流量系数
    Figure PCTCN2022102929-appb-100002
    压力系数φ 2确定风机改造技术方案；     Step 1. Determine the technical plan for fan transformation, according to the flow coefficient corresponding to the fan TB point selection parameters before the transformation of the adjustable blade axial flow fan
    Figure PCTCN2022102929-appb-100001
    Pressure coefficient φ 1 , flow coefficient corresponding to TB point selection parameters after fan energy-saving transformation
    Figure PCTCN2022102929-appb-100002
    The pressure coefficient φ 2 determines the technical scheme of fan transformation;
    步骤2、确定风机新型动叶造型方法，风机改造技术方案分为风机叶片更换和风机局部改造两种方法。Step 2. Determine the modeling method of the new rotor blade of the fan. The technical plan for fan renovation is divided into two methods: fan blade replacement and fan partial modification.
  3. 根据权利要求2所述的一种电站动叶可调式轴流风机节能改造新型动叶造型方法，其特征在于，风机改造技术方案分为风机叶片更换和风机局部改造两种方法，两种方法分别陈述如下：According to claim 2, a new type of moving blade modeling method for energy-saving transformation of an axial flow fan with adjustable moving blades in a power station is characterized in that the technical scheme for fan transformation is divided into two methods: fan blade replacement and fan partial transformation, and the two methods are respectively The statement is as follows:
    (1)风机叶片更换方法，当风机改造前、后流量系数比满足
    Figure PCTCN2022102929-appb-100003
    时，仅需更换风机全部动叶片，而风机轮毂和机壳等其它结构的尺寸均保持不变；     (1) The fan blade replacement method, when the ratio of the flow coefficient before and after the fan modification satisfies
    Figure PCTCN2022102929-appb-100003
    , only need to replace all the moving blades of the fan, while the dimensions of other structures such as the hub and casing of the fan remain unchanged;
    (2)风机局部改造方法，当风机改造前、后流量系数比满足
    Figure PCTCN2022102929-appb-100004
    时，在风机叶片更换的同时，还需进行如下改动：     (2) Partial transformation method of the fan, when the ratio of the flow coefficient before and after the transformation of the fan satisfies
    Figure PCTCN2022102929-appb-100004
    When the fan blades are replaced, the following changes are also required:
    ①风机动叶片高度H′ 1调整，缩短改造后风机动叶片高度H′ 1，使其满足
    Figure PCTCN2022102929-appb-100005
    式中，H 1为风机改造前叶片高度，H′ 1为风机改造后叶片高度，单位 均为mm；     ①Adjust the height H′ 1 of the wind turbine blades, and shorten the height H′ 1 of the wind turbine blades after the transformation to meet the
    Figure PCTCN2022102929-appb-100005
    In the formula, H 1 is the height of the fan blade before modification, H′ 1 is the height of the fan blade after modification, and the unit is mm;
    ②风机机壳内径R′ shroud调整，缩短改造后风机机壳内径R′ shroud，使其满足R′ shroud＝R shroud+H′ 1-H 1，式中，R shroud为风机改造前机壳内径，R′ shroud为风机改造后机壳内径，单位均为mm，同时，改造前后风机叶顶间隙保持不变。 ②Adjust the inner diameter R′ shroud of the fan casing, shorten the inner diameter R′ shroud of the fan casing after the transformation, so that it meets R′ shroud = R shroud + H′ 1 -H 1 , where R shroud is the inner diameter of the fan casing before transformation , R′ shroud is the inner diameter of the casing after the transformation of the fan, and the unit is mm.
  4. 根据权利要求3所述的一种电站动叶可调式轴流风机节能改造新型动叶造型方法，其特征在于，对于风机叶片更换方法，风机新型动叶具体造型方法如下：According to claim 3, a new type of moving blade modeling method for energy-saving retrofitting of an axial flow fan with adjustable moving blades in a power station is characterized in that, for the replacement method of fan blades, the specific modeling method of the new type of moving blades of the fan is as follows:
    (1)沿叶高方向将叶片在圆柱坐标系下等分为M个叶型截面，M取3～8之间的整数，并将M个叶型截面的叶型型线坐标展开到平面坐标系；(1) Divide the blade into M airfoil sections equally in the cylindrical coordinate system along the blade height direction, M takes an integer between 3 and 8, and expand the airfoil line coordinates of the M airfoil sections to plane coordinates Tie;
    (2)确定M个叶型截面的造型方法，对于M个叶型截面，每个叶型截面的造型方法相同；(2) determine the modeling method of M airfoil sections, for M airfoil sections, the modeling method of each airfoil section is the same;
    (3)确定新型动叶片第i个叶型截面的压力面型线PS′ i和吸力面型线SS′ i，构造新型动叶片第i个叶型截面的叶型型线BS′ i，根据上一步确定的新型动叶叶型截面中弧线C′ 1,i的型线，通过在中弧线C′ 1,i型线两侧叠加叶型厚度分布，并叶型截面前缘和尾缘完成前缘圆弧曲线和尾缘圆弧曲线的造型，就确定了新型动叶片第i个叶型截面的压力面型线PS′ i和吸力面型线SS′ i； (3) Determine the pressure surface profile PS′ i and the suction surface profile SS′ i of the i-th profile section of the new type of moving blade, and construct the profile line BS′ i of the i-th profile section of the new type of rotor blade, according to The profile line of the arc line C′ 1,i determined in the previous step is to superimpose the profile thickness distribution on both sides of the profile line of the center arc line C′ 1,i , and align the leading edge and trailing edge of the profile section. Complete the molding of the leading edge arc curve and the trailing edge arc curve, the pressure surface profile PS′ i and the suction surface profile SS′ i of the i-th airfoil section of the novel rotor blade are determined;
    (4)将新型动叶片M个叶型截面的叶型型线BS′ i沿叶高方向积叠，生成新型动叶片三维造型，根据新型动叶片第i个叶型截面的叶型型线BS′ i，求解得到第i个叶型截面的叶型重心O′ i，将新型动叶片M个叶型截面的叶型重心O′ i作为n阶贝塞尔曲线的控制点，i＝1,···,M，n＝M-1，O′ 1点为起点，O′ M点为终点，生成(M-1)阶贝塞尔曲线C 2，然后，将新型动叶片第i个叶型截面的叶型型线BS′ i通过贝塞尔曲线C 2沿叶高方向积叠，就完成了新型动叶片的三维造型。 (4) The blade profile lines BS′ i of the M airfoil sections of the new type of moving blade are stacked along the blade height direction to generate a three-dimensional model of the new type of moving blade. ′ i , the airfoil center of gravity O′ i of the i-th airfoil section is obtained by solving, and the airfoil center of gravity O′ i of the M airfoil sections of the new moving blade is used as the control point of the n-order Bezier curve, i=1, ···, M, n=M-1, O′ 1 point is the starting point, O′ M point is the end point, generate (M-1) order Bezier curve C 2 , and then, the i-th blade of the new rotor blade The blade profile line BS'i of the profile section is accumulated along the blade height direction through the Bezier curve C2 , and the three-dimensional modeling of the new type of moving blade is completed.
  5. 根据权利要求4所述的一种电站动叶可调式轴流风机节能改造新型动叶 造型方法，其特征在于，步骤(2)中，对于以第i个叶型截面，i＝1,···,M，陈述新型动叶叶型截面造型方法如下：According to claim 4, a new type of moving blade modeling method for energy-saving transformation of an axial flow fan with adjustable moving blades in a power station is characterized in that, in step (2), for the i-th blade-shaped section, i=1,·· ·, M, state the section modeling method of the new rotor blade profile as follows:
    ①采用n阶贝塞尔曲线，对原始叶片第i个叶型截面的压力面型线PS i、吸力面型线SS i进行曲线拟合，n阶贝塞尔曲线公式如下： ① Use n-order Bezier curves to perform curve fitting on the pressure surface PS i and suction surface SS i of the i-th airfoil section of the original blade. The n-order Bezier curve formula is as follows:
    Figure PCTCN2022102929-appb-100006
    Figure PCTCN2022102929-appb-100006
    拟合过程中，保持叶片前缘点A i、叶片尾缘点B i位置不变，采用对第i个叶型截面的中弧线C 1,i两侧施加相同叶型厚度分布的方式对压力面型线PS i、吸力面型线SS i进行曲线拟合；采用最小二乘法，根据贝塞尔拟合曲线与中弧线C 1,i离散点之间误差平方和最小原则，求解贝塞尔曲线控制点P i，i＝0,1,...,n，并得到贝塞尔曲线阶数n，n≥3； During the fitting process, the positions of the blade leading edge point A i and the blade trailing edge point B i are kept unchanged, and the same blade thickness distribution is applied to both sides of the mid-arc line C 1,i of the i-th airfoil section. The pressure surface profile PS i and the suction surface profile line SS i are used for curve fitting; the least square method is used to solve the Bessel Bezier curve control point P i , i=0,1,...,n, and obtain Bezier curve order n, n≥3;
    拟合完成后得到原始叶片第i个叶型截面的中弧线C 1,i和叶型厚度分布的贝塞尔拟合曲线，获取了如下参数：原始叶片第i个叶型截面的前缘进口几何角α i，尾缘出口几何角β i，叶型弦长c i，叶片最大厚度位置距叶型前缘位置a i，叶片最大厚度b max,i参数； After the fitting is completed, the middle arc C 1,i of the i-th airfoil section of the original blade and the Bezier fitting curve of the airfoil thickness distribution are obtained, and the following parameters are obtained: the leading edge of the i-th airfoil section of the original blade Inlet geometric angle α i , trailing edge outlet geometric angle β i , airfoil chord length c i , blade maximum thickness position to airfoil leading edge position a i , blade maximum thickness b max,i parameters;
    ②调整原始叶片第i个叶型截面中弧线C 1,i的贝塞尔拟合曲线参数，得到新型动叶片第i个叶型截面中弧线的贝塞尔拟合曲线，完成新型动叶片第i个叶型截面中弧线C′ 1,i的造型； ②Adjust the Bezier fitting curve parameters of the arc C 1,i in the i-th profile section of the original blade to obtain the Bezier fitting curve of the arc in the i-th profile section of the new moving blade, and complete the new dynamic The shape of the arc C′ 1,i in the i-th airfoil section of the blade;
    新型动叶片叶型截面中弧线贝塞尔拟合曲线参数前缘进口几何角为α′ i，尾缘出口几何角为β′ i和叶型弦长c′ i按如下公式确定： The arc Bezier fitting curve parameters of the new-type moving blade airfoil cross - section are determined by the following formula :
    Figure PCTCN2022102929-appb-100007
    Figure PCTCN2022102929-appb-100007
    式中，k 1为叶型前缘进口几何角调整系数，k 2为叶型尾缘出口几何角调整系数，k 3为叶型弦长调整系数； In the formula, k 1 is the adjustment coefficient of the inlet geometric angle of the airfoil leading edge, k 2 is the adjustment coefficient of the geometric angle of the airfoil trailing edge outlet, and k 3 is the adjustment coefficient of the airfoil chord length;
    确定了上述参数，就唯一确定了新型动叶叶型截面中弧线C′ 1,i的型线。 After the above parameters are determined, the profile line of the arc C′ 1,i in the profile section of the new rotor blade is uniquely determined.
  6. 根据权利要求5所述的一种电站动叶可调式轴流风机节能改造新型动叶造型方法，其特征在于，步骤(3)中，具体实施方法如下：According to claim 5, a new type of rotor blade modeling method for energy-saving retrofit of an axial flow fan with adjustable rotor blades in a power station is characterized in that, in step (3), the specific implementation method is as follows:
    ①以叶片前缘点A i为坐标原点0，叶片前缘点A i到叶片尾缘点B i为x轴正方向建立坐标系，以叶型中弧线C′ 1,i上某一点在x方向距离坐标原点0的距离为x，以该点处的叶型厚度分布为b(x)，根据第二步得到的原始叶片第i个叶型截面叶型厚度分布的贝塞尔拟合曲线，得到该截面叶型厚度分布函数b(x)＝f 1(x),0≤x≤c i，令
    Figure PCTCN2022102929-appb-100008
    将叶型厚度分布函数无量纲化处理，整理得到函数b(j)＝f 2(j),0≤j≤1；     ① Take the blade leading edge point A i as the coordinate origin 0, the blade leading edge point A i to the blade trailing edge point B i as the positive direction of the x-axis to establish a coordinate system, and take a certain point on the arc C′ 1,i of the blade shape at The distance from the coordinate origin 0 in the x direction is x, and the profile thickness distribution at this point is b(x), according to the Bessel fitting of the profile thickness distribution of the i-th profile section of the original blade obtained in the second step Curve, get the profile thickness distribution function b(x)=f 1 (x), 0≤x≤c i , let
    Figure PCTCN2022102929-appb-100008
    The blade thickness distribution function is dimensionless, and the function b(j)=f 2 (j), 0≤j≤1 is obtained;
    ②保持新型动叶片与原始叶片在第i个叶型截面相同相对弦长位置叶型的厚度分布相同，即假设新型动叶片第i个叶型截面横坐标为x′，而叶型截面弦长为c′ i，则
    Figure PCTCN2022102929-appb-100009
    将其整理为新型动叶片第i个叶型截面叶型厚度分布函数b(x′)＝f 3(x′),0≤x′≤c′ i，这样，就确定了新型动叶片第i个叶型截面的叶型厚度分布规律；     ②Keep the thickness distribution of the blade profile at the same relative chord length position of the new rotor blade and the original blade at the i-th blade profile section, that is, assume that the abscissa of the i-th profile section of the new rotor blade is x′, and the blade profile chord length is c′ i , then
    Figure PCTCN2022102929-appb-100009
    It is sorted into the profile thickness distribution function b(x′)=f 3 (x′), 0≤x′≤c′ i of the i-th airfoil section of the new type of moving blade, so that the i-th blade of the new type of moving blade Airfoil thickness distribution law of each airfoil section;
    ③将上面步骤确定新型动叶片第i个叶型截面的叶型厚度分布规律叠加于该叶型截面的中弧线C′ 1,i型线上，生成压力面曲线和吸力面曲线，然后，在叶型截面前缘和尾缘分别构造前缘圆弧曲线和尾缘圆弧曲线，前缘圆弧曲线和尾缘圆弧曲线均为一段圆弧，分别与上面生成的压力面曲线和吸力面曲线相切，且 在该叶型截面，新型动叶片前缘圆弧曲线圆弧半径R′ 1,i满足：0＜R′ 1,i≤3％·c′ i；新型动叶片尾缘圆弧曲线圆弧半径R′ 2,i满足：0＜R′ 2,i≤2％·c′ i，这样，就确定了新型动叶片第i个叶型截面的压力面型线PS′ i和吸力面型线SS′ i，将压力面型线PS′ i和吸力面型线SS′ i组合在一起，将完成了新型动叶片第i个叶型截面的叶型型线BS′ i的构造。 ③ superimpose the profile thickness distribution law of the i-th profile section of the new moving blade determined by the above steps on the mid-arc line C' 1, i -shaped line of the profile section to generate a pressure surface curve and a suction surface curve, and then, The leading edge arc curve and the trailing edge arc curve are respectively constructed on the leading edge and the trailing edge of the airfoil section. The leading edge arc curve and the trailing edge arc curve are both arcs, which are respectively related to the pressure surface curve and suction generated above. The surface curves are tangent, and in the section of the airfoil, the arc radius R′ 1,i of the leading edge arc curve of the new type of moving blade satisfies: 0<R′ 1,i ≤ 3% c′ i ; the trailing edge of the new type of moving blade The arc radius R′ 2,i of the arc curve satisfies: 0<R′ 2,i ≤ 2% c′ i , thus, the pressure surface profile line PS′ i of the i-th airfoil section of the new moving blade is determined and the suction surface profile line SS′ i , combining the pressure surface profile line PS′ i and the suction surface profile line SS′ i to complete the blade profile line BS′ i of the i-th profile section of the new rotor blade structure.
  7. 根据权利要求6所述的一种电站动叶可调式轴流风机节能改造新型动叶造型方法，其特征在于，对于风机局部改造方法，风机新型动叶具体造型方法如下：According to claim 6, a new type of rotor blade modeling method for energy-saving transformation of an axial flow fan with adjustable rotor blades in a power station is characterized in that, for the partial modification method of the fan, the specific molding method of the new rotor blade of the fan is as follows:
    (1)按照风机叶片更换方法中(1)～(4)部分的内容完成新型动叶片的三维造型，新型动叶片原始叶高H 2与原始叶片叶高H 1保持一致，即H 2＝H 1； (1) Complete the three-dimensional modeling of the new moving blade according to the contents of parts (1) to (4) in the fan blade replacement method. The original blade height H 2 of the new moving blade is consistent with the original blade height H 1 , that is, H 2 =H 1 ;
    (2)将新型动叶片叶顶处进行切割，缩短叶片高度，由第1步骤可知，风机局部改造后，风机叶片高度要缩短至H′ 1，
    Figure PCTCN2022102929-appb-100010
    所以对叶片顶部进行切割，将叶片固定安装于轮毂后，采用圆柱坐标系，以轮毂中心线为回转轴，将叶片顶部切掉(H 2-H′ 1)高度，H 2-H′ 1＝H 1-H′ 1，新型动叶片高度就缩短至H′ 1，叶片其它部分保持不变。     (2) Cut the top of the new moving blade to shorten the height of the blade. From the first step, it can be known that after the partial modification of the fan, the height of the fan blade should be shortened to H′ 1 ,
    Figure PCTCN2022102929-appb-100010
    So cut the top of the blade, fix the blade on the hub, use the cylindrical coordinate system, take the hub centerline as the axis of rotation, cut off the top of the blade to a height of (H 2 -H′ 1 ), H 2 -H′ 1 = H 1 -H′ 1 , the height of the new moving blade is shortened to H′ 1 , and the other parts of the blade remain unchanged.
  8. 根据权利要求7所述的一种电站动叶可调式轴流风机节能改造新型动叶造型方法，其特征在于，对于双级动叶可调式轴流风机节能改造新型动叶造型，第一级和第二级的新型动叶造型方法相同，均按照单级动叶可调式轴流风机节能改造新型动叶造型的方法进行造型：第一级按照单级动叶可调式轴流风机节能改造新型动叶造型的方法完成单级风机新型动叶片的造型后，第二级再重复上述过程，第一级和第二级的风机动叶片造型完全相同。According to claim 7, a new type of rotor blade modeling method for energy-saving retrofit of an axial flow fan with adjustable rotor blades in a power station is characterized in that, for the new type of rotor blade shape for energy-saving retrofit of an axial fan with adjustable rotor blades at two stages, the first stage and The modeling method of the new moving blades of the second stage is the same, and they are all shaped according to the method of energy-saving transformation of the new moving blades of the single-stage adjustable moving-blade axial flow fan: the first stage is based on the energy-saving transformation of the new type of moving The method of blade modeling After the modeling of the new moving blades of the single-stage fan is completed, the above process is repeated for the second stage, and the shapes of the moving blades of the first and second stages are exactly the same.
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