CN103742203B - Steam turbine final blade - Google Patents
Steam turbine final blade Download PDFInfo
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- CN103742203B CN103742203B CN201410047845.6A CN201410047845A CN103742203B CN 103742203 B CN103742203 B CN 103742203B CN 201410047845 A CN201410047845 A CN 201410047845A CN 103742203 B CN103742203 B CN 103742203B
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Abstract
The invention provides a kind of steam turbine final blade, comprise blade root connected successively, intermediate, blade and shroud, the height C of described blade is 1905mm; Along the short transverse of blade, the relative value of blade section area is decreased to 1.0 gradually by 7.33, the relative value of blade molded line axial width W is decreased to 1.0 gradually by 5.61, the relative value of blade molded line circumferential width H increases to 1.67 gradually by 1.0, the relative value of blade molded line chord length L is decreased to 1.0 gradually by 1.40, the relative value of blade molded line maximum ga(u)ge TMAX is decreased to 1.0 gradually by 5.89, and established angle α is increased to 76 ° gradually by 12 °.This steam turbine final blade increases the leaving area of exhaust stage blade by the length (namely height) increasing blade, and its leaving area is up to 30m
2, the application demand of the different back pressures such as CAP1400/CAP1700, unit grade nuclear steam turbine can be met.
Description
Technical field
The present invention relates to a kind of moving vane be arranged on turbine rotor, particularly relate to a kind of steam turbine final blade.
Background technique
Flourish along with China's Nuclear Electricity, the single-machine capacity of nuclear power generating sets is also progressively increasing, and all has corresponding unit in construction or in planning from 1000MW to 1700MW.Unit capacity is larger, and the quantity of low pressure (LP) cylinder and the total length of steam turbine also can be larger, and this is by the whole efficiency of extreme influence steam turbine.At present, the length by increasing last stage vane of steam turbine reduces the quantity of low pressure (LP) cylinder and the total length of steam turbine.
Last stage vane of steam turbine is the core component of steam turbine, and particularly for Large Copacity nuclear steam turbine, it represents the technical merit of nuclear steam turbine.At present, the capacity of the Capacity Ratio 1000MW grade unit of third generation reactor unit adds 20% ~ 80%, add coastal and in, the requirement of the low coolant water temperature in northern territory, third generation reactor unit needs larger leaving area requirement.In the Half Speed nuclear steam turbine put into operation, final blades are leaving area 15-20m
2grade, steam passage height is 1400mm grade, and its leaving area is less than normal, can not meet the requirement of third generation reactor nuclear steam turbine group.In order to meet the application demand of the nuclear steam turbine of the different back pressures such as CAP1400/CAP1700 and unit grade, each company is all concentrating strength on the linear leaf developing larger leaving area, but due to the problem of aerodynamics and strength vibration aspect, again limit the length of exhaust stage blade, thus the leaving area of restriction exhaust stage blade.
Summary of the invention
The shortcoming of prior art in view of the above, the object of the present invention is to provide a kind of steam turbine final blade, to overcome the defect that can not meet the nuclear steam turbine application demand of the different back pressures such as CAP1400/CAP1700 and unit grade in prior art because exhaust stage blade leaving area is little.
For achieving the above object, the invention provides a kind of steam turbine final blade, comprise blade root connected successively, intermediate, blade and shroud, the molded line of described blade is variable cross section distortion molded line, have relative torsion between adjacent two cross sections of blade, the height C of described blade is 1905mm; Along the short transverse of blade, the relative value of blade section area is decreased to 1.0 gradually by 7.33, the relative value of blade molded line axial width W is decreased to 1.0 gradually by 5.61, the relative value of blade molded line circumferential width H increases to 1.67 gradually by 1.0, the relative value of blade molded line chord length L is decreased to 1.0 gradually by 1.40, the relative value of blade molded line maximum ga(u)ge TMAX is decreased to 1.0 gradually by 5.89, and established angle α is increased to 76 ° gradually by 12 °.
Preferably, the actual value of described blade section area is by 17600mm
2be decreased to 2400mm gradually
2the actual value of blade molded line axial width W is decreased to 77mm gradually by 432mm, the actual value of blade molded line circumferential width H increases to 306mm gradually by 183mm, the actual value of blade molded line chord length L is decreased to 315mm gradually by 442mm, and the actual value of blade molded line maximum ga(u)ge TMAX is decreased to 9mm gradually by 53mm.
Further, the axial width of described intermediate is identical with the axial width E of blade root, is 480mm; The height sum D of intermediate and blade root is 153.62mm.
Preferably, the axial width A of described shroud is 77.59mm, and the height B of shroud is 15 ~ 50mm.
Further, described blade root is the fir-tree root of Rouno Cormer Pregrinding Wheel, stress concentration.
Preferably, the both sides bottom described blade root all offer locating slot.
Further, being horizontally set with a cross section in described blade is oval boss, and this boss is one-body molded with blade, and described boss comprises the first coupling front end and first and to be coupled rear end.
Preferably, the upper end of described blade is provided with anti-water eroded areas at admission avris, and described anti-water eroded areas is coated in the surface of blade by laser melting coating.
As mentioned above, the steam turbine final blade that the present invention relates to, has following beneficial effect:
This steam turbine final blade increases the leaving area of exhaust stage blade by the length (namely height) increasing blade, and its leaving area is up to 30m
2, the application demand of the different back pressures such as CAP1400/CAP1700, unit grade nuclear steam turbine can be met.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is the side view of Fig. 1.
Fig. 3 is blade molded line scale diagrams.
Fig. 4 is the long-pending folded schematic diagram of blade molded line.
Fig. 5 is the plan view of intermediate.
Fig. 6 is the plan view of boss in the present invention.
Structural drawing when Fig. 7 is two boss couplings.
Fig. 8 is the plan view of shroud in the present invention.
Structural drawing when Fig. 9 is two shroud couplings.
Element numbers explanation
1 blade root
2 intermediates
3 blades
4 shrouds
41 second coupling front end
42 second coupling rear ends
5 locating slots
6 boss
61 first coupling front end
62 first coupling rear ends
7 anti-water eroded areas
8 leading edges
9 lagging edges
Embodiment
By particular specific embodiment, embodiments of the present invention are described below, person skilled in the art scholar the content disclosed by this specification can understand other advantages of the present invention and effect easily.
Notice, structure, ratio, size etc. that this specification institute accompanying drawings illustrates, content all only in order to coordinate specification to disclose, understand for person skilled in the art scholar and read, and be not used to limit the enforceable qualifications of the present invention, therefore the not technical essential meaning of tool, the adjustment of the modification of any structure, the change of proportionate relationship or size, do not affecting under effect that the present invention can produce and the object that can reach, still all should drop on disclosed technology contents and obtain in the scope that can contain.Simultaneously, quote in this specification as " on ", D score, "left", "right", " centre " and " one " etc. term, also only for ease of understanding of describing, and be not used to limit the enforceable scope of the present invention, the change of its relativeness or adjustment, under changing technology contents without essence, when being also considered as the enforceable category of the present invention.
The invention provides a kind of leaving area can up to 30m
2steam turbine final blade, as depicted in figs. 1 and 2, this steam turbine final blade comprise be connected successively blade root 1, intermediate 2, blade 3 and shroud 4, and blade root 1, intermediate 2, blade 3 and shroud 4 are structure as a whole.Described blade 3 is the variable cross section twisted blade adopting full three dimensional design analytical method to determine, namely the molded line of this blade 3 is variable cross section distortion molded line, along the short transverse of blade, the shape in adjacent two cross sections of blade 3 is different, and has relative torsion between adjacent two cross sections of blade 3.In the present invention, in order to improve the leaving area of final blades, the height C of described blade 3 is designed to 1905mm, this is highly the steam passage length of last stage vane of steam turbine.While increasing blade height (namely length of blade), blade also to be made to meet designing requirement in aeroperformance, intensity etc., therefore need repeatedly to revise the geometrical shape of blade in blade 3, that is repeatedly revise the molded line in each cross section of blade 3.
As shown in Figure 3, blade molded line has following characteristic parameter:
Section area: the area in blade cross section;
Chord length L: the distance in blade cross section between leading edge 8 and lagging edge 9;
Maximum ga(u)ge TMAX: the tangential width in blade cross section;
Established angle α: chord length L with the angle of axially (X to).
In the application, through amended blade 3 each cross section molded line repeatedly, there is following characteristics: along the short transverse of blade 3, namely along blade root 1 to the direction of shroud 4, the relative value of blade section area is decreased to 1.0 gradually by 7.33, the relative value of blade molded line axial width W is decreased to 1.0 gradually by 5.61, the relative value of blade molded line circumferential width H increases to 1.67 gradually by 1.0, the relative value of blade molded line chord length L is decreased to 1.0 gradually by 1.40, the relative value of blade molded line maximum ga(u)ge TMAX is decreased to 1.0 gradually by 5.89, established angle α is increased to 76 ° gradually by 12 °.
Provide blade 3 one preferably embodiment below:
Table 1 each cross section basic parameter
In above-described embodiment, along the short transverse of blade 3, the section area of blade is by 17600mm
2be decreased to 2400mm gradually
2the axial width W of blade molded line is decreased to 77mm gradually by 432mm, the circumferential width H of blade molded line increases to 306mm gradually by 183mm, the chord length L of blade molded line is decreased to 315mm gradually by 442mm, the maximum ga(u)ge TMAX of blade molded line is decreased to 9mm gradually by 53mm, established angle α is increased to 76 ° gradually by 12 °, and the molded line in each cross section as shown in Figure 4.In addition, in above-mentioned table 1, lagging edge 9 thickness refers to the thickness of each cross section molded line in lagging edge 9 side of blade 3.
Further, as shown in Figure 1, the axial width of described intermediate 2 is identical with the axial width E of blade root 1, is 480mm; The height sum D of intermediate 2 and blade root 1 is 153.62mm; The axial width A of described shroud 4 is 77.59mm, and the height B of shroud 4 is 15 ~ 50mm.
When installing this steam turbine final blade, be arranged in the race of rotor by blade root 1, a circle amounts to 70 blades.In the present embodiment, described blade root 1 is the fir-tree root of side dress, Rouno Cormer Pregrinding Wheel, stress concentration, can reduce stress significantly and concentrate, and reduces the maximum stress of blade root 1 and race, to improve the strength character of anti-low cycle fatigue and stress corrosion resistant.Preferably, as shown in Figure 1 and Figure 5, the both sides bottom described blade root 1 all offer locating slot 5, during assembling, can load supporting bar in locating slot 5, to avoid blade axial float, ensure the safe and stable operation of steam turbine.
Further, as shown in Figure 6 and Figure 7, being horizontally set with a cross section in described blade 3 is oval boss 6, this boss 6 is one-body molded with blade 3, described boss 6 comprises the first coupling front end 61 and the first coupling rear end 62, and the first coupling front end 61 and the first coupling rear end 62 suitable, the major axis F of described ellipse is 103mm, and minor axis G is 35mm.As shown in Figure 8 and Figure 9, described shroud 4 comprises the second coupling front end 41 and the second coupling rear end 42, described second coupling front end 41 and the second coupling rear end 42 suitable.Be arranged on by these final blades after in the race of turbine rotor, can leave the gap of 1-2mm between the shroud 4 of adjacent two blades and the working surface of boss 6, namely during static state, blade is monolithic structure, under working speed, shroud 4 and the boss 6 of adjacent two blades twist under the influence of centrifugal force, the boss 6 of adjacent two blades is coupled by the first coupling rear end 62 and the first cooperatively interacting of coupling front end 61, the shroud 4 of adjacent two blades is coupled by the second coupling rear end 42 and the second cooperatively interacting of coupling front end 41, thus make the gap between the shroud 4 of adjacent two blades and the working surface of boss 6 be 0, adjacent blades is connected into whole circle, and then improve the rigidity of blade, significantly reduce dynamic stress, frequency modulation exponent number is low, dynamic frequency effectively improves.
In addition, final blades operationally, because the temperature of low pressure (LP) cylinder, pressure are relatively low, wet vapor is in operation and easily condenses into little water droplet, under the influence of centrifugal force, little water droplet constantly impacts the leading edge 8 of blade, easily cause the water erosion of blade inlet edge 8, blade erosion can cause blade to occur cellular texture, blade inlet edge 8 edge can be made time serious to present flexuose, form much tiny crackle, leaf top edge even can be made to form breach, cause blade fatigue intensity to reduce, affect unit safety.In order to solve blade inlet edge 8 water erosion problem, in the application, the upper end of described blade 3 is provided with anti-water eroded areas 7 in leading edge 8 side, and this anti-water eroded areas 7 is between shroud 4 and boss 6, and described anti-water eroded areas 7 is coated in the surface of blade 3 by laser melting coating.Described anti-water eroded areas 7 adopts laser melting and coating technique, itself and the soldering stellite alloy film ratio of routine, has the advantages such as laminating degree is good, difficult drop-off, to improve water erosion resistent ability.In addition, except anti-water eroded areas 7 cladding layer, the remaining part of blade is all adopt the alloyed steel solid forging of same high-intensity performance to form, thus avoids the defect that stress is concentrated, and improves the safety reliability of blade.
In sum, the steam turbine final blade that the present invention relates to has the following advantages:
1, the leaving area of these final blades is up to 30m
2, no matter be applicable to the nuclear steam turbines such as CAP1400/CAP1700, be all reach advanced world standards in Economy, safety reliability, and steam discharge loss obviously reduces, and under certain backpressure condition, can reduce by a low pressure (LP) cylinder, reduce investment, bring great benefit to power plant;
2,1905mm final blades adopt advanced complete three-dimensional reaction blade design proposal, greatly reduce aerodynamic loss, and adopt large-scale full three dimensional viscous flowfield CFD software to carry out being optimized molded line, make this grade blade have good aerodynamic characteristic; Flow characteristic in moving vane runner is complicated, radially exists from subsonic speed-transonic speed-Supersonic Flow change; Carry out full three-dimensional optimized design to stator blade, with most effective position target, dynamic and static leaf has best matching relationship simultaneously, under the prerequisite ensureing safety reliability, allows blade have best efficiency;
What 3, blade employing was advanced carries shroud, boss whole circle self-locking damping structural type, with all the other structural type blade ratios of equal length grade, there is the features such as lightweight, frequency modulation exponent number is few, frequency stabliltiy good, anti-Flutter Performance is strong, the Security run under severe strength environment can be met;
4, while theory analysis examination, by setting up Special test rotor and blade in kind carries out dynamic frequency modulation test and designs detailed frequency modulation scheme, guarantee that blade has good vibration characteristics;
5, anti-water erosion measure is laser melting coating, and the soldering stellite alloy film ratio with routine, has the advantages such as laminating degree is good, difficult drop-off, to improve water erosion resistent ability stability;
6, easy to assembly, utilize the reaction torque of centrifugal force to form whole circle self-locking damping, more reliable compared with the whole circle effect formed by mechanical structure, be conducive to adjustment and frequency modulation.
So the present invention effectively overcomes various shortcoming of the prior art and tool high industrial utilization.
Above-described embodiment is illustrative principle of the present invention and effect thereof only, but not for limiting the present invention.Any person skilled in the art scholar all without prejudice under spirit of the present invention and category, can modify above-described embodiment or changes.Therefore, such as have in art usually know the knowledgeable do not depart from complete under disclosed spirit and technological thought all equivalence modify or change, must be contained by claim of the present invention.
Claims (8)
1. a steam turbine final blade, comprise blade root (1) connected successively, intermediate (2), blade (3) and shroud (4), the molded line of described blade (3) is variable cross section distortion molded line, there is relative torsion between adjacent two cross sections of blade (3), it is characterized in that: the height C of described blade (3) is 1905mm; Along the short transverse of blade (3), the relative value of blade section area is decreased to 1.0 gradually by 7.33, the relative value of blade molded line axial width W is decreased to 1.0 gradually by 5.61, the relative value of blade molded line circumferential width H increases to 1.67 gradually by 1.0, the relative value of blade molded line chord length L is decreased to 1.0 gradually by 1.40, the relative value of blade molded line maximum ga(u)ge TMAX is decreased to 1.0 gradually by 5.89, and established angle α is increased to 76 ° gradually by 12 °; When established angle α is 12 °, 17 °, 22 °, 28 °, 35 °, 42 °, 49 °, 56 °, the upper trailing edge thickness of blade (3) is 2.5mm, when established angle α is 63 °, the upper trailing edge thickness of blade (3) is 2.2mm, when established angle α is 70 °, the upper trailing edge thickness of blade (3) is 2.1mm, and when established angle α is 76 °, the upper trailing edge thickness of blade (3) is 2.0mm.
2. steam turbine final blade according to claim 1, is characterized in that: along the short transverse of blade (3), and the actual value of described blade section area is by 17600mm
2be decreased to 2400mm gradually
2the actual value of blade molded line axial width W is decreased to 77mm gradually by 432mm, the actual value of blade molded line circumferential width H increases to 306mm gradually by 183mm, the actual value of blade molded line chord length L is decreased to 315mm gradually by 442mm, and the actual value of blade molded line maximum ga(u)ge TMAX is decreased to 9mm gradually by 53mm.
3. steam turbine final blade according to claim 1, is characterized in that: the axial width of described intermediate (2) is identical with the axial width E of blade root (1), is 480mm; The height sum D of intermediate (2) and blade root (1) is 153.62mm.
4. steam turbine final blade according to claim 1, is characterized in that: the axial width A of described shroud (4) is 77.59mm, and the height B of shroud (4) is 15 ~ 50mm.
5. steam turbine final blade according to claim 1, is characterized in that: described blade root (1) is Rouno Cormer Pregrinding Wheel, the fir-tree root of stress concentration.
6. steam turbine final blade according to claim 1 or 5, is characterized in that: the both sides of described blade root (1) bottom all offer locating slot (5).
7. steam turbine final blade according to claim 1, it is characterized in that: being horizontally set with a cross section in described blade (3) is oval boss (6), this boss (6) is one-body molded with blade (3), and described boss (6) comprises the first coupling front end (61) and the first coupling rear end (62).
8. steam turbine final blade according to claim 1, it is characterized in that: the upper end of described blade (3) is provided with anti-water eroded areas (7) in leading edge (8) side, and described anti-water eroded areas (7) is coated in the surface of blade (3) by laser melting coating.
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| CN201410047845.6A CN103742203B (en) | 2014-02-11 | 2014-02-11 | Steam turbine final blade |
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| CN201410047845.6A CN103742203B (en) | 2014-02-11 | 2014-02-11 | Steam turbine final blade |
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| CN103742203B true CN103742203B (en) | 2016-04-27 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105240054B (en) * | 2014-07-07 | 2017-03-22 | 上海电气电站设备有限公司 | Penultimate-stage moving blade for half-speed high-capacity nuclear turbine |
| CN105317466B (en) * | 2014-07-07 | 2017-03-22 | 上海电气电站设备有限公司 | Secondary-secondary last-stage moving blade for half-speed high-capacity nuclear turbine |
| CN104533536A (en) * | 2014-12-31 | 2015-04-22 | 东方电气集团东方汽轮机有限公司 | Integral shroud structure of last-stage moving blade |
| CN108204249A (en) * | 2016-12-20 | 2018-06-26 | 上海汽轮机厂有限公司 | Variable speed last-stage moving blade of air-cooled steam turbine |
| CN109063352B (en) * | 2018-08-10 | 2023-01-06 | 上海汽轮机厂有限公司 | Method for improving surface smoothness of turbine blade profile |
| CN109707462B (en) * | 2018-12-28 | 2022-03-18 | 东方电气集团东方汽轮机有限公司 | 1450mm titanium alloy final-stage blade of full-speed steam turbine |
| CN112580164B (en) * | 2020-12-14 | 2022-07-22 | 哈尔滨汽轮机厂有限责任公司 | Design method of low-pressure long blade of nuclear turbine |
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