CN106446324B - Design method of final-stage twisted blade of large industrial steam turbine - Google Patents
Design method of final-stage twisted blade of large industrial steam turbine Download PDFInfo
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Abstract
本发明的目的在于提供一种大型工业汽轮机末级扭叶片设计方法,用于解决现有扭叶片造型技术中不同叶高截面叶型匹配时叶型型线容易畸变、叶片造型优化表面不易光顺的问题。实际实现了一种半参数化叶片设计的方法,可以通过调整叶片扭曲因子实现叶片中弧线分布规律变化,直观可靠,当对叶片进行进一步改进优化时,可直接调整指定截面中弧线形状,简单快速地达到需求效果。
The purpose of the present invention is to provide a design method for the twisted blade of the last stage of a large industrial steam turbine, which is used to solve the problem that the profile line of the blade is easily distorted and the optimized surface of the blade shape is not easy to be smooth when the blade shape of different blade heights is matched in the existing twisted blade modeling technology. The problem. A method of semi-parametric blade design is actually implemented, which can realize the change of the arc distribution law of the blade by adjusting the blade twist factor, which is intuitive and reliable. When the blade is further improved and optimized, the shape of the arc in the specified section can be directly adjusted. Simply and quickly achieve the desired effect.
Description
技术领域technical field
本发明涉及一种大型工业汽轮机末级扭叶片,特别是一种大型工业汽轮机末级扭叶片设计方法。The invention relates to a twisted blade at the last stage of a large industrial steam turbine, in particular to a design method for the twisted blade at the last stage of a large industrial steam turbine.
背景技术Background technique
为提高火力发电站热效率,电站给水泵采用汽轮机拖动来降低能耗。近年来,在“节能减排”背景下超临界及超超临界燃煤发电机组相继投产,相应的驱动给水泵汽轮机也呈现大型化趋势,而我国在大型电站驱动给水泵用工业汽轮机多为外国进口,引进设备成本高,对国家能源、经济安全也是隐患。In order to improve the thermal efficiency of the thermal power station, the feedwater pump of the power station is driven by a steam turbine to reduce energy consumption. In recent years, under the background of "energy saving and emission reduction", supercritical and ultra-supercritical coal-fired generating units have been put into operation one after another, and the corresponding steam turbines driving feedwater pumps have also shown a trend of large-scale, while the industrial steam turbines used to drive feedwater pumps in large power stations in my country are mostly foreign The cost of importing and introducing equipment is high, and it is also a hidden danger to national energy and economic security.
叶片是汽轮机的核心,大型电站驱动给水泵用工业汽轮机末级扭叶片长、转速高且变化范围大、容积流量大、负荷大、在湿蒸汽区运行,叶片离心力大、振动特性复杂,同时需要保证叶片有高的效率。低压级叶片核心技术长期为发达国家垄断,急需开发具有自主知识产权的大型电站驱动给水泵用工业汽轮机叶片,实现我国大型电站驱动给水泵用工业汽轮机国产化。The blade is the core of the steam turbine. The last-stage twisted blade of the industrial steam turbine used to drive the feedwater pump in a large power station has long blades, high rotational speed, large variation range, large volumetric flow rate, and heavy load. Operating in a wet steam area, the blades have large centrifugal force and complex vibration characteristics. At the same time, they need Ensure that the blades have high efficiency. The core technology of low-pressure blades has been monopolized by developed countries for a long time, and it is urgent to develop industrial steam turbine blades for large-scale power station-driven feedwater pumps with independent intellectual property rights to realize the localization of industrial steam turbines for large-scale power station-driven feedwater pumps in China.
在汽轮机叶片设计中,通常的方法是预先建立标准叶型库,应用时在标准叶型库中选用型线,标准叶型库中的型线一般是按照进汽角等关键参数分类归档的,每档有一个标准叶型,一般标准型线是不连续的,因此不能保证叶型与气流角要求完全一致,不能避免攻角损失。目前还有一种较为流行的完全参数化叶片设计,使用关键参数(进出汽角、安装角、弦长等)和样条叶型型线,控制截面叶型,再给定积叠规律实现叶片三维造型,该方法可以快速实现直叶片或扭转较小叶片的造型和优化,但对于扭转较大的末级叶片,使用该方法实现不同叶高截面叶型匹配和改进优化时,容易出现叶型型线畸变和叶片表面不能光顺的问题。In the design of steam turbine blades, the usual method is to establish a standard blade library in advance, and select profiles in the standard blade library during application. The profiles in the standard blade library are generally classified and archived according to key parameters such as steam inlet angle. Each gear has a standard airfoil shape, and the general standard shape line is discontinuous, so it cannot be guaranteed that the airfoil shape is completely consistent with the requirements of the airflow angle, and the loss of the angle of attack cannot be avoided. At present, there is a more popular completely parametric blade design, using key parameters (inlet and outlet steam angle, installation angle, chord length, etc.) This method can quickly realize the shape and optimization of straight blades or blades with small torsion, but for the final stage blades with large torsion, when using this method to achieve the matching and improvement of different blade height cross-section blade shapes, it is easy to appear The problem of line distortion and blade surface not being smooth.
发明内容Contents of the invention
鉴于以上所述的现有技术缺点,本发明的目的在于提供一种大型工业汽轮机末级扭叶片设计方法,用于解决现有扭叶片造型技术中不同叶高截面叶型匹配时叶型型线容易畸变、叶片造型优化表面不易光顺的问题。In view of the disadvantages of the prior art described above, the purpose of the present invention is to provide a design method for the twisted blades of the last stage of a large industrial steam turbine, which is used to solve the problem of the blade profile when matching different blade heights and cross-sections in the existing twisted blade modeling technology. It is easy to be distorted, and the surface of the optimized blade shape is not easy to be smooth.
为实现上述目的及其他相应目标,本发明提供一种大型工业汽轮机末级扭叶片设计方法,包括以下步骤:In order to achieve the above purpose and other corresponding goals, the present invention provides a method for designing the last stage twisted blade of a large industrial steam turbine, comprising the following steps:
1)使用一维快速热力设计,实现各级初步焓降分配,确定各级平均半径位置叶型进、出口气流角,初步得到子午面图;1) Use one-dimensional rapid thermal design to realize the initial enthalpy drop distribution at all levels, determine the airflow angles of the air inlet and outlet of the blade shape at the average radius position of each level, and initially obtain the meridian surface map;
2)选定扭转因子,根据末级子午流面及平均半径位置叶型参数,应用基于流线曲率的S2方法确定末级叶片沿叶高叶型截面进口气流角分布规律;2) Select the torsion factor, and use the S2 method based on the streamline curvature to determine the distribution law of the inlet airflow angle of the last stage blade along the blade height blade shape section according to the last stage meridian flow surface and the average radius position blade shape parameters;
3)将叶片沿叶高方向分为N个截面,根据工业汽轮机末级叶片设计规律,选定叶根截面和叶顶截面中弧线弦长,根据进口气流角,使用样条曲线(如Bezier曲线)构造出沿叶高各截面叶型中弧线;3) Divide the blade into N sections along the blade height direction. According to the design rules of the last stage blades of industrial steam turbines, select the arc chord length of the blade root section and the blade top section, and use spline curves (such as Bezier curve) to construct the mid-arc of each section along the height of the blade;
4)根据沿叶高各截面中弧线和进口气流角,考虑到强度、振动要求,确定厚度分布规律,在厚度分布曲线数据库中查取合适的厚度分布曲线;4) According to the arc of each section along the height of the blade and the inlet airflow angle, considering the strength and vibration requirements, determine the thickness distribution law, and check the appropriate thickness distribution curve in the thickness distribution curve database;
5)根据厚度分布规律,使用样条曲线(如Bezier曲线)拟合截面叶型背弧和内弧,叶型前缘和尾缘使用小圆代替,背弧、内弧与小圆相切;5) According to the law of thickness distribution, use spline curves (such as Bezier curves) to fit the back arc and inner arc of the cross-section airfoil. The leading edge and trailing edge of the airfoil are replaced by small circles, and the back arc and inner arc are tangent to the small circle;
6)根据各截面叶型型线,使用曲面样条生成叶片曲面;6) According to the profile line of each section, use surface spline to generate the blade surface;
7)选定叶根、拉筋凸台和围带形式,完成三维叶片结构设计。7) Select the blade root, rib boss and shroud form to complete the three-dimensional blade structure design.
作为优选:As preferred:
所述的步骤3)中叶片沿叶高方向的截面的数目N为11~19个。The number N of sections of the blade along the blade height direction in step 3) is 11-19.
所述的步骤3)中叶片根部弦长在120mm~160mm范围内,叶片顶部弦长在60~90mm范围内。In step 3), the chord length of the blade root is in the range of 120 mm to 160 mm, and the chord length of the blade top is in the range of 60 mm to 90 mm.
所述的步骤4中厚度分布曲线选择需保证叶片根部截面面积在1800mm2~2200mm2范围内,叶片顶部截面面积在300mm2~500mm2范围内。The selection of the thickness distribution curve in step 4 needs to ensure that the cross-sectional area of the blade root is within the range of 1800mm 2 ~2200mm 2 , and the cross-sectional area of the blade top is within the range of 300mm 2 ~500mm 2 .
所述的步骤5)中背弧、内弧的样条曲线控制点P的数目为5~10个。The number of control points P of the spline curve of the back arc and the inner arc in the step 5) is 5-10.
如上所述,本发明大型工业汽轮机末级扭叶片设计方法,具有以下有益效果:As mentioned above, the method for designing the last-stage twisted blades of large-scale industrial steam turbines of the present invention has the following beneficial effects:
该大型工业汽轮机末级扭叶片设计方法,实际为一种半参数化叶片设计方法。叶片中弧线为参数化设计,在叶片设计初期,可以通过调整叶片扭曲因子实现叶片中弧线分布规律变化,直观可靠,当对叶片进行进一步改进优化时,可直接调整指定截面中弧线形状,简单快速地达到需求效果。截面叶型背弧、内弧型线使用已有的厚度分布曲线库数据,可以保证叶片具有良好的气动性能,同时能有效避免各截面叶型匹配和改进优化过程中容易出现型线畸变和叶片表面不光顺的问题。The design method of the last-stage twisted blade of a large industrial steam turbine is actually a semi-parametric blade design method. The central arc of the blade is a parametric design. In the early stage of blade design, the distribution of the central arc of the blade can be changed by adjusting the blade twist factor, which is intuitive and reliable. When the blade is further improved and optimized, the shape of the arc in the specified section can be directly adjusted , simply and quickly achieve the required effect. The back arc and inner arc of the cross-section airfoil use the existing thickness distribution curve database data, which can ensure that the blade has good aerodynamic performance, and can effectively avoid profile distortion and blade The surface is not smooth.
附图说明Description of drawings
图1显示为本发明设计方法步骤2)的示意图;Fig. 1 is a schematic diagram showing step 2) of the design method of the present invention;
图2显示为本发明设计方法步骤3)的示意图;Fig. 2 is a schematic diagram showing step 3) of the design method of the present invention;
图3显示为本发明设计方法步骤4)叶高和厚度曲线的示意图;Fig. 3 shows the schematic diagram of leaf height and thickness curves for step 4) of the design method of the present invention;
图4显示为本发明设计方法步骤4)截面相对厚度与相对轴向弦长的曲线示意图;Fig. 4 shows a schematic diagram of the curves of the relative thickness of the section and the relative axial chord length in step 4) of the design method of the present invention;
图5显示为本发明设计方法步骤5)的示意图;Fig. 5 is a schematic diagram showing step 5) of the design method of the present invention;
图6显示为本发明设计方法步骤6)的示意简图;图7显示为本发明设计方法步骤6)的网格示意图;Fig. 6 shows a schematic diagram of step 6) of the design method of the present invention; Fig. 7 shows a schematic diagram of a grid of step 6) of the design method of the present invention;
图8显示为本发明设计方法步骤7)的示意图。Fig. 8 is a schematic diagram of step 7) of the design method of the present invention.
元件标号说明Component designation description
1 中弧线1 arc
2 内弧2 inner arc
3 背弧3 back arc
4 叶身4 leaves
5 叶根5 leaf roots
6 拉筋凸台6 Tension bosses
7 围带7 belt
具体实施方式Detailed ways
以下通过特定的具体实例说明本发明的实施方法,本领域技术人员可以由本说明书所叙述的内容轻易地了解本发明所具有的优点。本发明还可以通过另外不同的具体实例实施方式加以实施和应用,本说明书中的各项细节也可以在没有背离本发明的精神下进行各种修饰和改变,实施不同观点与应用。The implementation method of the present invention is described below through specific examples, and those skilled in the art can easily understand the advantages of the present invention from the content described in this specification. The present invention can also be implemented and applied through other different specific example embodiments, and various modifications and changes can be made to the details in this specification without departing from the spirit of the present invention, so as to implement different viewpoints and applications.
请参阅图1至图8。需要说明的是,本实施实例中所提供的图示仅以示意图方式说明本发明的基本构想,因此图示中仅显示与本发明中有关的组件而非按照实际实施时的组件数目、尺寸及形状绘制,实际实施时各组件的数目、尺寸及形状可以随意改变,且其组件布局形态具体形态也可能更为复杂。See Figures 1 through 8. It should be noted that the diagrams provided in this implementation example are only schematic diagrams illustrating the basic concept of the present invention, so only the components related to the present invention are shown in the diagrams rather than the number, size and size of components in actual implementation. Shape drawing, the number, size and shape of each component can be changed at will during actual implementation, and the specific form of the layout of the components may also be more complicated.
本发明大型工业汽轮机末级扭叶片设计方法,包括以下步骤:The design method of the last stage twisted blade of large industrial steam turbine of the present invention comprises the following steps:
1)使用一维快速热力设计,实现各级初步焓降分配,确定各级平均半径位置叶型进口气流角α、出口气流角β,初步得到子午面图。1) Use one-dimensional rapid thermal design to realize the distribution of preliminary enthalpy drop at all levels, determine the inlet airflow angle α and outlet airflow angle β of the blade profile at the average radius position of each level, and initially obtain the meridian surface map.
2)选定扭转因子z,根据经过步骤1)获得的末级子午流面及平均半径位置叶型参数,应用基于流线曲率的S2方法确定末级叶片沿叶高叶型截面进口气流角α和出口气流角β的分布规律,如图1所示。2) Select the torsion factor z, and use the S2 method based on the streamline curvature to determine the inlet airflow angle α of the final stage blade along the blade height profile section according to the final stage meridian flow surface and the average radius position blade shape parameters obtained through step 1) and the distribution law of the outlet airflow angle β, as shown in Figure 1.
3)将叶片沿叶高方向分为N个截面,其中横截面数量N为11至19个,如图6所示,根据工业汽轮机末级叶片设计规律,选定叶根截面和叶顶截面叶型中弧线1的弦长b(即叶型截面前缘小圆圆心与尾缘小圆圆心之间的直线距离),根部叶型截面弦长b在120mm~160mm范围内,顶部叶型弦长b在60~90mm范围内。对于每个横截面根据进口气流角α,使用Bezier样条曲线构造出截面叶型中弧线1,并将所有的中弧线1按照某种重叠(例如尾缘重叠、前缘重叠等)规律放置在一起,形成如图2所示的图,可以清晰地反映叶片的扭曲规律,并能对指定的中弧线1进行微调。3) Divide the blade into N sections along the blade height direction, and the number of cross sections N is 11 to 19, as shown in Figure 6. The chord length b of arc 1 in the profile (that is, the straight-line distance between the center of the small circle at the leading edge of the profile section and the center of the small circle at the trailing edge), the chord length b of the profile section at the root is within the range of 120 mm to 160 mm, and the chord length of the profile at the top is The length b is in the range of 60~90mm. For each cross-section according to the inlet airflow angle α, use the Bezier spline curve to construct the mid-arc 1 of the cross-section airfoil, and make all the mid-arc 1 according to a certain overlapping (such as trailing edge overlap, leading edge overlap, etc.) Put them together to form a diagram as shown in Figure 2, which can clearly reflect the twisting law of the blade, and can fine-tune the specified mid-arc 1.
Bezier样条曲线的定义为:The definition of a Bezier spline is:
其中,。in, .
如图5所示,由Bezier样条曲线定义可知,可通过调整控制点,得到不同的中弧线1形状。As shown in Figure 5, from the definition of the Bezier spline curve, it can be known that different shapes of the middle arc 1 can be obtained by adjusting the control points.
4)根据沿叶高各截面中弧线1和进口气流角α,并考虑强度、振动要求确定厚度分布规律,如图3、图4所示。厚度分布曲线来自于厚度分布曲线数据库,厚度分布曲线是反映中弧线1为直线的原始叶型沿弦长b从叶型前缘到尾缘叶型相对厚度C(即相对于弦长b的百分比)的分布规律。对于工业汽轮机,厚度分布曲线选择需要保证叶片根部截面面积A在1800mm2~2200mm2范围内,叶片顶部截面面积A在300mm2~500mm2范围内。4) According to the arc 1 of each section along the height of the blade and the inlet airflow angle α, and considering the strength and vibration requirements, the thickness distribution law is determined, as shown in Figure 3 and Figure 4. The thickness distribution curve comes from the thickness distribution curve database. The thickness distribution curve reflects the original airfoil profile whose central arc 1 is a straight line along the chord length b from the leading edge to the trailing edge. percentage) distribution. For industrial steam turbines, the selection of the thickness distribution curve needs to ensure that the cross-sectional area A of the blade root is in the range of 1800mm 2 ~2200mm 2 , and the cross-sectional area A of the blade top is in the range of 300mm 2 ~500mm 2 .
5)根据厚度分布规律,使用样条Bezier样条曲线拟合截面叶型内弧2和背弧3,叶型前缘和尾缘型线使用小圆代替,内弧2、背弧3与小圆相切,如图5所示,Bezier样条曲线控制点P的数目为5-10个,定义与步骤3)中一致。5) According to the law of thickness distribution, use the spline Bezier spline curve to fit the inner arc 2 and back arc 3 of the cross-section airfoil. The circle is tangent, as shown in Figure 5, the number of control points P of the Bezier spline curve is 5-10, and the definition is consistent with that in step 3).
6)根据N个截面叶型型线,使用曲面样条生成叶片曲面,如图6、图7所示。6) According to the N cross-sectional airfoil lines, use surface splines to generate the blade surface, as shown in Figure 6 and Figure 7.
7)选定叶根5、拉筋凸台6和围带7的形式,完成三维叶片结构设计,如图8所示。7) Select the form of the blade root 5, the rib boss 6 and the shroud 7 to complete the three-dimensional blade structure design, as shown in Figure 8.
通过上述方法,首先就固定沿叶高各截面叶型中弧线1,可以很好的保证叶片进、出口气流角按照设计要求分布,保证良好的气动性能,同时厚度曲线选择能很好地满足强度、振动要求,保证所设计的工业汽轮机末级扭叶片工作安全可靠。Through the above method, the arc 1 of each section along the height of the blade is first fixed, which can well ensure that the inlet and outlet airflow angles of the blade are distributed according to the design requirements, and ensure good aerodynamic performance. At the same time, the selection of the thickness curve can well meet the The strength and vibration requirements ensure the safe and reliable operation of the designed twisted blades of the last stage of industrial steam turbines.
现有技术采用离散点记录叶型截面轮廓,并通过人工调整各点坐标来获得叶型轮廓的方法非常繁琐不便,而完全参数化的叶型又很难保证叶型型线的气动性能,本发明在厚度分布曲线基础上进行样条曲线拟合控制,只需要有限的控制点P即可完成叶型造型,即保证了所得型线的良好气动性能,设计操作又十分方便,可以快速地获得整个三维叶栅轮廓。The existing technology uses discrete points to record the profile of the airfoil section, and the method of manually adjusting the coordinates of each point to obtain the profile of the airfoil is very cumbersome and inconvenient, and it is difficult to guarantee the aerodynamic performance of the airfoil profile with a fully parameterized airfoil. The invention performs spline curve fitting control on the basis of the thickness distribution curve, and only needs a limited control point P to complete the airfoil shape, which ensures the good aerodynamic performance of the obtained shape line, and the design operation is very convenient, and can be quickly obtained The entire 3D cascade profile.
现有技术多采用的使用多个截面叶型沿径向按指定规律积叠获得三维叶型的造型方法,在对某个截面进行调整时,十分容易出现叶型型线畸变和叶片表面不能光顺的问题,本发明使用的中弧线控制方法,可以方便快捷的实现叶片微调,并能有效地避免上述问题。The existing technology mostly adopts the modeling method of using multiple cross-section airfoils to accumulate along the radial direction according to a specified rule to obtain a three-dimensional airfoil shape. When adjusting a certain cross-section, it is very easy to cause distortion of the airfoil shape line and the surface of the blade cannot be smooth. For the problem of smoothness, the middle arc control method used in the present invention can realize the fine adjustment of the blade conveniently and quickly, and can effectively avoid the above-mentioned problems.
综上所述,本发明大型工业汽轮机末级扭叶片设计方法,叶片采用中弧线控制,保证叶片进、出口气流角按照设计要求分布,截面叶型型线基于厚度分布曲线确定,并使用样条曲线(如Bezier曲线)进行参数化,即保证了叶型的良好气动性能,又保证了型线的光滑过渡,方便高效的生成气动性能优异的工业汽轮机末级扭叶片。所以,本发明有效地克服了现有技术中一些缺点,具有明显的产业利用价值。To sum up, in the design method of the twisted blade of the last stage of a large industrial steam turbine in the present invention, the blade is controlled by the middle arc to ensure that the airflow angle of the blade inlet and outlet is distributed according to the design requirements, and the cross-sectional blade shape is determined based on the thickness distribution curve. The parameterization of a curve (such as a Bezier curve) not only ensures the good aerodynamic performance of the blade shape, but also ensures the smooth transition of the profile line, and conveniently and efficiently generates the last-stage twisted blade of an industrial steam turbine with excellent aerodynamic performance. Therefore, the present invention effectively overcomes some shortcomings in the prior art, and has obvious industrial application value.
上述实施例仅例示性说明本发明的原理及优点,而非用于限制本发明。任何熟悉此技术的认识皆可在不违背本发明的精神及范畴下,对上述实施例进行修饰或改变。因此,举凡所述技术领域中具有通常知识者在未脱离本发明所揭示的精神与技术思想下所完成的一切等效修饰或改变,仍应由本发明的权利要求所涵盖。The above-mentioned embodiments are only illustrative to illustrate the principles and advantages of the present invention, but not intended to limit the present invention. Anyone familiar with the technology can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or changes made by persons with ordinary knowledge in the technical field without departing from the spirit and technical ideas disclosed in the present invention should still be covered by the claims of the present invention.
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