CN109101722B - Composite forming design method for turbine blade - Google Patents
Composite forming design method for turbine blade Download PDFInfo
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- CN109101722B CN109101722B CN201810902234.3A CN201810902234A CN109101722B CN 109101722 B CN109101722 B CN 109101722B CN 201810902234 A CN201810902234 A CN 201810902234A CN 109101722 B CN109101722 B CN 109101722B
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Abstract
The invention discloses a composite molding design method of a turbine blade, wherein the blade adopts a variable cross-section twisted molded line which is formed by superposing a plurality of characteristic cross sections according to a certain rule; the profile line of the characteristic section is a closed curve formed by an inner arc curve and a back arc curve; the characteristic cross section has the parameters: mounting angle c, chord length b, pitch t, throat width o and relative grid distance t/b; the superposition rule of the characteristic cross sections is as follows: from the root end to the top along the blade direction of height, each characteristic cross-section is smooth transition in succession, and the relative grid distance of characteristic cross-section is unchangeable, and the erection angle radially changes along certain law to change the export geometry angular distribution of each cross-section, control fluid along the distribution law of blade direction of height, shift high-efficiency region area fluid to high efficiency region, promote blade through-flow efficiency, and then increase whole turbine efficiency.
Description
Technical Field
The invention belongs to the technical field of turbine through flow, and relates to a turbine blade composite forming design method.
Background
At present, with the increasing national requirements for energy conservation and emission reduction, the attention of owners to the efficiency index of the steam turbine is rapidly increased, and as the most critical component in the through-flow design technology, the performance of the blades directly determines the efficiency and the energy consumption of the steam turbine. Therefore, the development, design and application of efficient blades become the key and difficult point of the whole turbine through-flow design technology, and more, the core and key of the whole turbine design work. Especially for high-power steam turbines, the energy-saving effect is extremely great even if the efficiency is increased by only 1%, and the economic benefit and the social benefit generated by the energy-saving effect are also very remarkable. Therefore, a great deal of manpower and financial resources are invested by all related companies at home and abroad for a long time to develop, design and improve the efficient blade.
Research shows that for the turbine blade, in the region where the leakage fluid is poured into the main flow, the leakage fluid can be mixed with the main flow, the development of the secondary flow at the end part is deteriorated, and a high-loss region is formed; in the region where the leakage fluid sucks the main flow, the sucking action of the leakage fluid reduces the secondary flow action region and the high loss region. Therefore, in the blade design process, a design method of reducing the geometric angle of the blade outlet in the high loss area and increasing the geometric angle of the blade outlet in the high efficiency area can be adopted, namely, the flow distribution of the fluid is changed, the fluid in the high loss area is transferred to the low loss area, the proportion of the fluid in the high loss area is reduced, and the through-flow efficiency is increased.
Disclosure of Invention
The invention aims to: aiming at the existing problems, the composite forming design method for the turbine blade is provided, the relative grid pitch is kept unchanged along the height direction of the blade, and the installation angle is changed along the height direction of the blade according to a specific composite forming rule, so that the outlet geometric angle distribution of each section is changed, the distribution rule of fluid along the height direction of the blade is controlled, the fluid in a high-loss area is transferred to a high-efficiency area, the through-flow efficiency of the blade is improved, and the efficiency of the whole turbine is further improved.
The technical scheme adopted by the invention is as follows:
the invention relates to a composite molding design method of a turbine blade, wherein the blade adopts a variable cross-section twisted molded line which is formed by superposing a plurality of characteristic cross sections according to a certain rule; the profile line of the characteristic section is a closed curve formed by an inner arc curve and a back arc curve; the characteristic cross section has the parameters: mounting angle c, chord length b, pitch t, throat width o and relative grid distance t/b; the superposition rule of the characteristic cross sections is as follows: from the root end to the top along the blade direction of height, each characteristic cross section is smooth transition in succession, and characteristic cross section's relative grid distance is unchangeable, and the angle of erection is along following law radial change:
croot of herbaceous plant-cIn＝0°～3°，
cIn-cTop roof＝3°～7°，
Wherein, cTop roofIs a top section mounting angle, cInIs a middle section mounting angle, cRoot of herbaceous plantIs a root section mounting angle.
Furthermore, the installation angle takes a large value at the root of the blade, a medium value at the middle of the blade and a small value at the top of the blade; after the mounting angles at the root, the middle and the top of the blade are determined, the mounting angle change curve of the whole blade height is obtained by spline fitting.
Further, the characteristic cross section also has the parameters: blade exit geometry angle sin-1(o/t), the blade exit geometry angle varies radially along the following law:
in which sin-1(o/t)Top roofIs the tip vane exit geometry angle, sin-1(o/t)InIs the middle blade exit geometric angle, sin-1(o/t)Root of herbaceous plantThe root blade exit geometry angle.
Furthermore, the geometric angle of the blade outlet takes a large value at the root of the blade, a medium value at the middle of the blade and a small value at the top of the blade; after the geometric angles of the outlets at the root, the middle and the top of the blade are determined, the change curve of the geometric angles of the outlets of the whole blade height is obtained by spline fitting.
With the above-described method arrangement, there are generally two methods based on the change to the blade exit geometry angle: one is to keep the installation angle of each section of the blade unchanged and adjust the outlet geometric angle at each section position by changing the relative grid distance of each section; the invention relates to a turbine blade, which is characterized in that the relative grid pitch of each section is kept unchanged, and the outlet geometric angle at the position of each section is adjusted directly by changing the installation angle of each section.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. the turbine blade composite forming design method is simple and has strong operability and practicability.
2. The blade molded by the composite molding design method of the turbine blade has good circulation efficiency, can transfer the fluid in a high loss area to a high efficiency area, and greatly improves the efficiency of the turbine.
3. The blade molded by the composite molding design method of the turbine blade has high-order smooth molded lines and excellent pneumatic performance, the technical performance index reaches or exceeds the prior similar products, and the integral comprehensive performance is superior to the prior similar products.
Drawings
FIG. 1 is a three-dimensional schematic view of a blade;
FIG. 2 is a front view of the blade;
FIG. 3 is a top view of the blade;
FIG. 4 is a schematic radial cross-section of a blade;
FIG. 5 is the variation rule of the relative grid distance t/b of the blade with the height of the blade;
FIG. 6 is a rule of variation of the geometrical angle of the blade outlet with the height of the blade;
the labels in the figure are: 1-a blade; 11-top section; 12-middle section; 13-root section;
l-effective height of the blade, i.e. length of the body part of the blade: the distance between the top section of the blade body and the root section of the blade body;
b-chord length: the distance between the steam inlet edge and the steam outlet edge of the blade body section;
c-blade setting angle: the included angle between the chord length b and the Y direction;
t-pitch: circumferential spacing of adjacent blades;
o-throat width: the outlet width of the vane passage;
t/b-relative pitch: the ratio of pitch to chord length;
sin-1(o/t) -vane exit geometry angle.
Detailed Description
The present invention will be described in detail with reference to examples.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in fig. 1 to 6, a composite molding design method for a turbine blade, the blade adopts a variable cross-section twisted profile, which is formed by superposing a plurality of characteristic cross sections according to a certain rule; the profile line of the characteristic section is a closed curve formed by an inner arc curve and a back arc curve, and the outline profile of the profile line is shown in figures 1, 2 and 3; the characteristic cross section has the parameters: mounting angle c, chord length b, pitch t, throat width o and relative grid distance t/b; the superposition rule of the characteristic cross sections is as follows: from the root end to the top end along the blade height direction, each characteristic section is in continuous and smooth transition, the relative value of the blade height L is monotonically increased from 0.0 (root section) to 1.0 (top section), the relative grid distance of the characteristic sections is unchanged, and the installation angle is changed along the following rule in a radial direction:
croot of herbaceous plant-cIn＝0°～3°，
cIn-cTop roof＝3°～7°，
Wherein, cTop roofIs a top section mounting angle, cInIs a middle section mounting angle, cRoot of herbaceous plantIs a root section mounting angle. The installation angle takes a large value at the root of the blade, a medium value at the middle of the blade and a small value at the top of the blade; after the root, middle and top mount angles of the blade are determined, the change curve of the mount angles of the whole blade height is obtained by spline fitting, and is shown in FIG. 5.
Further, the characteristic cross section also has the parameters: blade exit geometry angle sin-1(o/t), the blade exit geometry angle varies radially along the following law:
in which sin-1(o/t)Top roofIs the tip vane exit geometry angle, sin-1(o/t)InIs the middle blade exit geometric angle, sin-1(o/t)Root of herbaceous plantIs the root blade exit geometry angle; the geometric angle of the blade outlet takes a large value at the root of the blade, a medium value at the middle of the blade and a small value at the top of the blade; after the geometric angles of the outlets at the root, the middle and the top of the blade are determined, the change curve of the geometric angles of the outlets of the whole blade height is obtained by spline fitting, and is shown in FIG. 6.
The blade for the turbine formed by the method has the advantages that the molded line of the blade is high-order smooth, the pneumatic performance is excellent, the technical performance index reaches or exceeds the prior similar products, and the integral comprehensive performance is superior to the prior similar products. Meanwhile, the structural elements of the turbine blade are different from the existing products, the relative grid distance of each section is kept unchanged along the height direction of the blade, the installation angle is changed along the height direction of the blade according to a specific composite forming rule, the outlet geometric angle of each section is changed along with the change, the distribution rule of fluid along the height direction of the blade is controlled, the fluid in a high loss area is transferred to a high-efficiency area, the through-flow efficiency of the blade is improved, and the efficiency of the whole turbine is improved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (4)
1. A turbine blade composite molding design method is characterized in that a blade adopts a variable cross-section twisted molded line which is formed by superposing a plurality of characteristic cross sections according to a certain rule; the profile line of the characteristic section is a closed curve formed by an inner arc curve and a back arc curve; the characteristic cross section has the parameters: mounting angle c, chord length b, pitch t, throat width o and relative grid distance t/b; the superposition rule of the characteristic cross sections is as follows: from the root end to the top along the blade direction of height, each characteristic cross section is smooth transition in succession, and characteristic cross section's relative grid distance is unchangeable, and the angle of erection is along following law radial change:
croot of herbaceous plant-cIn＝0°～3°，
cIn-cTop roof＝3°～7°，
Wherein, cTop roofIs a top section mounting angle, cInIs a middle section mounting angle, cRoot of herbaceous plantIs a root section mounting angle.
2. The method of claim 1, wherein the stagger angle is large at the root of the blade, medium at the middle of the blade, and small at the tip of the blade; after the mounting angles at the root, the middle and the top of the blade are determined, the mounting angle change curve of the whole blade height is obtained by spline fitting.
3. The turbine blade composite profile design method as claimed in claim 1 or 2, wherein the characteristic cross section further has parameters: blade exit geometry angle sin-1(o/t), the blade exit geometry angle varies radially along the following law:
in which sin-1(o/t)Top roofIs the tip vane exit geometry angle, sin-1(o/t)InIs the middle blade exit geometric angle, sin-1(o/t)Root of herbaceous plantThe root blade exit geometry angle.
4. The method of claim 3, wherein the blade exit geometry angle is a large value at the root of the blade, a medium value at the middle of the blade, and a small value at the tip of the blade; after the geometric angles of the outlets at the root, the middle and the top of the blade are determined, the change curve of the geometric angles of the outlets of the whole blade height is obtained by spline fitting.
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| CN109101722B true CN109101722B (en) | 2022-03-22 |
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| CN114483204B (en) * | 2021-12-29 | 2023-07-14 | 东方电气集团东方汽轮机有限公司 | Stationary blade suitable for radial-axial vertical non-vertical air inlet |
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