WO2018214006A1 - 燃料组件及其装配方法 - Google Patents

燃料组件及其装配方法 Download PDF

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Publication number
WO2018214006A1
WO2018214006A1 PCT/CN2017/085415 CN2017085415W WO2018214006A1 WO 2018214006 A1 WO2018214006 A1 WO 2018214006A1 CN 2017085415 W CN2017085415 W CN 2017085415W WO 2018214006 A1 WO2018214006 A1 WO 2018214006A1
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WO
WIPO (PCT)
Prior art keywords
mixing
grid
fuel
wing
strip
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2017/085415
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English (en)
French (fr)
Inventor
李伟才
禹文池
傅先刚
周跃民
张国梁
陈建新
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
LING AO NUCLEAR POWER CO Ltd
China General Nuclear Power Corp
China Nuclear Power Technology Research Institute Co Ltd
China Nuclear Power Engineering Co Ltd
CGN Power Co Ltd
Lingdong Nuclear Power Co Ltd
Original Assignee
LING AO NUCLEAR POWER CO Ltd
China General Nuclear Power Corp
China Nuclear Power Technology Research Institute Co Ltd
China Nuclear Power Engineering Co Ltd
CGN Power Co Ltd
Lingdong Nuclear Power Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by LING AO NUCLEAR POWER CO Ltd, China General Nuclear Power Corp, China Nuclear Power Technology Research Institute Co Ltd, China Nuclear Power Engineering Co Ltd, CGN Power Co Ltd, Lingdong Nuclear Power Co Ltd filed Critical LING AO NUCLEAR POWER CO Ltd
Priority to PCT/CN2017/085415 priority Critical patent/WO2018214006A1/zh
Publication of WO2018214006A1 publication Critical patent/WO2018214006A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • G—PHYSICS
    • G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
    • G21C—NUCLEAR REACTORS
    • G21C3/00—Reactor fuel elements and their assemblies; Selection of substances for use as reactor fuel elements
    • G21C3/30—Assemblies of a number of fuel elements in the form of a rigid unit
    • G21C3/32—Bundles of parallel pin-, rod-, or tube-shaped fuel elements
    • 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
    • Y02E30/00—Energy generation of nuclear origin
    • Y02E30/30—Nuclear fission reactors

Definitions

  • the present invention relates to nuclear reactors, and more particularly to a fuel assembly for a nuclear reactor and a method of assembling the same.
  • a fuel assembly 1 disposed in a nuclear reactor includes an upper header 11, a guide tube 12, a grid 13, a fuel rod 14, and a lower header 15.
  • the grid 13 is disposed between the upper header 11 and the lower header 15 in a longitudinal direction.
  • the grid 13 includes a plurality of strips that intersect each other to form a plurality of grid units.
  • the guide tube 12 is disposed between the upper tube base 11 and the lower tube base 15 in a longitudinal direction, one end is fixedly connected to the upper tube base 11, and the other end is fixedly connected to the lower tube base 15, and the guide tubes 12 are parallel to each other and are disposed on In the grid unit, the grid 13 can thereby align the guide tubes 12 with each other and control the spacing between the guide tubes 12 to form a support skeleton of the fuel assembly 1.
  • the fuel rods 14 are disposed between the upper header 11 and the lower header 15 in the longitudinal direction and are disposed in the grid 13, and generally the fuel rods 14 are parallel to each other and disposed in the grid unit not occupied by the guide tubes 12.
  • a coolant of a cooling circulation system flows through a fuel rod 14 of a fuel assembly 1, for example, in the direction A
  • the mixing wings are usually also provided on the strip, and the mixing wings extend into the grid unit, and when the coolant fluid flows between the fuel rods 14 through the crucible, it will be blocked by the mixing wings 16 to form a lateral flow.
  • the coolant fluid is stirred, and then transitions from the laminar flow state to the turbulent flow state. After the steady state of the coolant fluid is destroyed, the heat of the fuel rod 14 is more easily derived, so that the thermal head of the fuel assembly 1 can be effectively improved.
  • the mixing wings are generally integrally formed with the strips, and are assembled into the grid 13 along with the strips, and then the fuel rods 14 are loaded into the grid of the grids 13. Within the cell unit.
  • the shape of the mixing wing is strictly required to be arbitrarily changed, but the mixing wing and the strip are integrally formed.
  • the effects of process dimensional tolerances and assembly tolerances need to be considered so that the mixing wings do not occupy too much area of the grid cells, and it is often necessary to leave sufficient clearance between the fuel rods 14 and the mixing wings.
  • the gap is a key factor affecting the thermal head during the cooling cycle. If the gap is too large, the lateral flow generated by the mixing wing is weak, and the effect on the coolant fluid is too small; in, The closer the mixing wing portion of the fuel rod 14 is to the fluid layer on the surface of the fuel rod 14, the greater the influence on the fuel rod 14 is, so that the excessive gap cannot effectively destroy the fluid layer on the surface of the fuel rod 14, and the mixing effect is weakened. .
  • how to avoid the interference of the fuel rod 14 and the mixing wing in ensuring the thermal headroom is a problem to be solved.
  • the technical problem to be solved by the present invention is to provide a fuel assembly and an assembly method thereof for how to ensure the thermal headroom and avoid interference between the fuel rod and the mixing wing.
  • a method for assembling a fuel assembly comprising: punching a strip and pre-forming a blending wing on the strip; assembling the strip to form a plurality of grids a lattice of cells; an overmolding of the mixing wings on the grid; and loading of the fuel rods in the grid cells in the longitudinal direction.
  • a strip is punched and preformed in a blending wing on a strip, and the same strip of the punched strip is integrally punched with the blending wing.
  • the pre-formed mixing wing is cut to mix the wings in a secondary molding.
  • the cutting includes laser cutting.
  • a plurality of mixing wings are overmolded by laser cutting.
  • the mixing wings of the plurality of grid cells are overmolded by laser cutting, and the fuel rods are sequentially passed through the plurality of grid cells in the longitudinal direction.
  • the center of the fuel rod to be set in the grid unit is determined, and the grid unit is cut with the center of the circle as the axis and the length larger than the radius of the fuel rod Preformed mixing wings on the strip.
  • the outer contour of the mixing wing includes a first section and a second section, the first section being adjacent to the fuel rod in one grid unit; in the preformed mixing wing The second section is shaped and the first section of the pattern is predetermined, and the first section is shaped in the secondary forming mixing wing.
  • the present invention also provides a fuel assembly including a grid and a fuel rod mounted longitudinally in the grid;
  • the grid comprises a plurality of strips, the strips intersecting each other to form a plurality of grid units, the fuel rods are correspondingly located in the grid unit, the strips are also provided with a mixing wing, and the strips and the mixing wings are integrally formed into a structure.
  • the mixing wing further includes an overmolded portion.
  • the gap between the outer contour of the mixing wing adjacent to the fuel rod and the fuel rod is not more than 2 mm.
  • the outer contour of the mixing wing includes a first section and a second section, and the first section is adjacent to the fuel rod in one grid unit; the first section is an arc segment, and Centered with adjacent fuel rods.
  • the implementation of the present invention has the following beneficial effects:
  • a conventional punching method can be used to pre-form only the mixing wings of the strips, and then the high-precision preparation method can be used for the pre-formed mixing wings.
  • the secondary forming is used to shape the mixing wing.
  • the influence of dimensional tolerance and assembly tolerance is reduced due to the improvement of the preparation precision, so that the mixing and mixing can be correspondingly increased on the basis of the safety performance.
  • the area of the wing reduces the amount of clearance between the mixing wing and the fuel rod.
  • the resulting lateral flow increases, thereby increasing the effectiveness of the coolant fluid; meanwhile, the gap reduction causes the mixing wing to be relatively closer to the fuel rod, thereby being effective near the fuel rod.
  • the fluid layer on the surface of the fuel rod is destroyed, and the mixing effect is enhanced.
  • FIG. 1 is a schematic structural view of a fuel assembly in the prior art
  • FIG. 2 is a flow chart showing a method of assembling a fuel assembly in accordance with a first embodiment of the present invention
  • FIG. 3 is a schematic structural view of a predetermined type of mixing wing according to an embodiment of the present invention.
  • FIG. 4 is a schematic structural view of another predetermined type of mixing wing according to an embodiment of the present invention.
  • FIG. 5 is a partial cross-sectional structural view of a fuel assembly in accordance with an embodiment of the present invention.
  • FIG. 6 is a schematic structural view of a mixing wing according to an embodiment of the present invention.
  • a method for assembling a fuel assembly includes: Step S100, punching a strip and pre-forming a blending wing on a strip; Step S200, assembling a strip to form a plurality of grids a grid of cells; step S300, overmolding the mixing wings on the grid; and step S400, loading the fuel rods into the grid cells in the longitudinal direction.
  • the conventional mixing method can be used to pre-form the mixing wing on the same strip of the punched strip, and then the preformed blending wing can be over-formed by a high-precision preparation method to form a shape.
  • the precision of the preparation is improved, the influence of dimensional tolerance and assembly tolerance is reduced, so that the area of the mixing wing can be increased correspondingly on the basis of the safety performance, and the mixing is reduced.
  • the resulting lateral flow increases, thereby increasing the effectiveness of the coolant fluid; meanwhile, the gap reduction causes the mixing wing to be relatively closer to the fuel rod, thereby being effective near the fuel rod.
  • the fluid layer on the surface of the fuel rod is destroyed, and the mixing effect is enhanced.
  • steps S200 and S400 are not described in detail herein, those skilled in the art can reasonably implement steps S200 and S400 using any suitable method in the prior art, and no further description is provided herein. It should be understood that any technical solution formed based on the teachings of the present invention is within the scope of the present invention.
  • step S100 the same strip of the punched strip is integrally punched to form a mixing wing, and the pre-formed mixing wing and the strip are integrated, thereby still
  • the stabilizing wing can be kept in stable connection with the strip to prevent the mixing wing from falling off the strip.
  • the pre-formed mixing wings in S100 may be cut to over-mold the mixing wings, thereby finally shaping the mixing wings.
  • the cutting method includes laser cutting, wire cutting and other non-contact cutting or soft contact methods, and the final forming of the mixing wing is realized by setting the cutting path.
  • the secondary molding is performed by an easy-to-focus cutting method, which can improve the precision of the mixing wing.
  • the cutting path can be easily adjusted, and the multiple mixing wings can be cut at the same time, thereby improving production efficiency.
  • the heat affected zone during the cutting process has little effect on the final forming of the mixing wing, which is within an acceptable range.
  • a laser-cut secondary molding mixing wing can be used, and further, a laser cutting can also be used. Multiple mixing wings are formed in the second step.
  • laser cutting can be used to simultaneously shape the mixing wings of a plurality of grid units, and the fuel rods sequentially pass through the plurality of grid units in the longitudinal direction, so that the plurality of mixing wings in the same longitudinal direction can be cut in the longitudinal direction. .
  • step S300 first, determine the center position of the fuel rod to be set in the grid unit, and use the center of the center as the axis to be longer than the radius of the fuel rod.
  • a pre-formed mixing wing on the strip of the grid unit is cut for the shaft.
  • the predetermined type of mixing wing 160a on the strip includes a first portion 161a and a second portion 162a that are relatively closer to the fuel rod to be subsequently loaded.
  • step S300 the center of the fuel rod to be loaded is taken as the axis, and the length of the fuel rod is greater than the radius of the fuel rod, and the predetermined type of mixing wing 160a is cut by a circular pattern to remove the second portion 162a, thereby obtaining the final Shaped mixing wings.
  • the radius of the drawn circle is larger than the radius of the fuel rod to be set, for example, the difference between the lengths of the two radii is not more than 2 mm
  • the cutting line 163a is a sector of the circle drawn, which may also be called an arc segment, and the cutting line 163a and the loading line
  • the gap between the outer surfaces of the fuel rods after the entry is the gap between the above-mentioned mixing wings and the fuel rod, and the gap is not more than 2 mm.
  • the outer contour of the mixing wing thus obtained comprises a first section and a second section, the first section being a contour section obtained by cutting along the cutting line 163a, and the second section being a contour section other than the first section, the first section
  • the fuel rod is closer to the fuel rod in the grid unit where the mixing wing is located, and the first section is curved or fan-shaped, and is co-centered with the fuel rod adjacent to the grid unit, and the concentric structure can significantly raise the mixing wing s efficiency.
  • the structure of the predetermined type of mixing wings 160a illustrated in FIG. 3 is for example only and is not a limitation of the present invention, and those skilled in the art can facilitate the loading of the fuel rod into the grid based on the teachings of the present invention.
  • the structure of any suitable predetermined type of mixing wings is selected for the unit, and will not be enumerated here.
  • Fig. 4 there is shown the construction of another predetermined type of mixing wing 160b comprising a first portion 161b and a second portion 162b, the second portion 162b being relatively closer to the fuel rod,
  • the dividing line 163b between the portion 161b and the second portion 162b is the cutting line in step S300.
  • the outer contour of the mixing wing includes a first section and a second section, and in one grid unit, the first section is relatively closer to the fuel rod, and The gap between one section and the outer surface of the fuel rod is the gap between the above-mentioned mixing wing and the fuel rod.
  • the second section of the mixing wing is shaped and the first stage of the pattern is predetermined;
  • the first section is finalized, and the final setting is finalized. Stir the entire wing.
  • a fuel assembly according to an embodiment of the present invention includes a grid and a fuel rod 14 mounted longitudinally in the grid; wherein the grid includes a plurality of strips 131 that intersect each other to form a plurality of grids
  • the cell unit 130, the fuel rod 14 is correspondingly located in the grid unit 130, and the strip 131 is further provided with a mixing wing 16, the strip and the mixing wing are integrally formed into a punching structure, and the mixing wing further comprises an overmolded portion.
  • the preparation precision of the overmolded portion is improved, and the influence of dimensional tolerance and assembly tolerance is reduced, so that the area of the mixing wing can be correspondingly increased on the basis of the safety performance to reduce the mixing between the mixing wing and the fuel rod. gap.
  • the mixing wing 26 includes a first portion 261 and a second portion 262 that are closer to the fuel rod within the grid unit, the first portion 261 and the second portion 262
  • the boundary 263 is not actually present and is defined only for convenience of presentation.
  • the first portion 261 is integral with the second portion 262.
  • the outer contour 26a of the second portion 262 adjacent to the fuel rod is an overmolded portion, and the other outer contour 26b is an integrally formed portion with the strip.
  • the gap 17 between the outer contour of the mixing wing 16 adjacent to the fuel rod 14 and the fuel rod 14 is no more than 2 mm.
  • This gap 17 is smaller than the conventional conventional gap.
  • the outer contour of the mixing wing 16 includes a first segment 161 and a second segment 162, the first segment 161 being an arc segment;
  • the first section 1 61 of the cell unit 130 is adjacent to the fuel rod 14 and is concentric with the adjacent fuel rods 14, which enhances the efficiency of the mixing wing 16.
  • the radius of the fuel rod 14 is smaller than the radius of the arc segment (specifically, the fitting radius of the arc segment), and the difference is not more than 2 mm.
  • the strip 131 is further provided with a rigid convex member 18 that protrudes into the grid unit 130 and abuts against the fuel rod.
  • the rigid male member 18 includes an associated support portion 181 and abutting portion 182.
  • the support portion 181 is a rigid member that is coupled to the strip 131.
  • the abutting portion 182 extends into the grid unit 130 and abuts the fuel rod 14. Elastic parts.
  • At least two of the four strips 131 of the same grid unit 130 are respectively provided with rigid protruding members 18, and the rigid protruding members 18 are used for abutting against the fuel rods 14, and the plurality of rigid protruding members 18 of the same grid unit 130 are provided.
  • the fuel rod 14 having a radius of approximately circular with a radius fitting the contour line (not shown), fit the approximately circular outer contour of the fuel rod surface and contour line 14 substantially coincide.
  • the radius of the fuel rod may be a radius to form a circular fitting contour for the plurality of rigid convex members in the same grid unit.
  • the center of the circular fitting contour can be determined as the center of the fuel rod with the loading.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Plasma & Fusion (AREA)
  • General Engineering & Computer Science (AREA)
  • High Energy & Nuclear Physics (AREA)
  • Fuel Cell (AREA)

Abstract

一种燃料组件及其装配方法，包括格架以及沿纵向安装于格架中的燃料棒（14）；其中，格架包括多个条带（131），条带（131）彼此相交配合形成多个栅格单元（130），燃料棒（14）对应位于栅格单元（130）内，条带（131）上还设有搅混翼（16），条带（131）与搅混翼（16）为一体冲制成型结构，且搅混翼（16）还包括二次成型部分。由于二次成型制备精度提高，减少了尺寸公差和装配公差带来的影响，从而产生的横向流动增强，对冷却剂流体产生的效力提高；同时，在燃料棒（14）附近有效地破坏燃料棒（14）表面的流体层，搅混效果增强。

Description

燃料组件及其装配方法
技术领域
[0001] 本发明涉及核反应堆， 尤其涉及一种用于核反应堆的燃料组件及其装配方法。
背景技术
[0002] 参见图 1， 设于核反应堆中的燃料组件 1包括上管座 11、 导向管 12、 格架 13、 燃 料棒 14、 以及下管座 15。 格架 13沿纵向设于上管座 11与下管座 15之间， 该格架 1 3包括多个条带， 条带彼此相交配合形成多个栅格单元。 导向管 12沿纵向设于上 管座 11与下管座 15之间， 一端与上管座 11固定相连， 另一端与下管座 15固定相 连， 导向管 12之间可彼此平行， 并设于栅格单元中， 由此格架 13可将导向管 12 彼此间隔幵， 并控制导向管 12之间的间距， 形成燃料组件 1的支撑骨架。 燃料棒 14沿纵向设于上管座 11与下管座 15之间， 并设于格架 13中， 一般各燃料棒 14彼 此平行， 设于没有被导向管 12占据的栅格单元中。
[0003] 核反应堆中， 冷却循环系统的冷却剂流经燃料组件 1的燃料棒 14， 例如沿 A方向
(即纵向） 流经， 以将中子慢化并带走裂变能。 针对上述冷却循环， 通常还在 条带上设置搅混翼， 搅混翼伸入格栅单元内， 当冷却剂流体在各燃料棒 14之间 流过吋， 将受到搅混翼 16的阻挡而形成横向流动， 使冷却剂流体被搅混， 继而 从层流态向湍流态过渡， 冷却剂流体的稳定态被破坏后， 燃料棒 14的热量更易 于导出， 从而可有效提高燃料组件 1的热工余量。
[0004] 目前， 在燃料组件 1的装配过程中， 搅混翼一般与条带一体成型制成， 并随着 条带一并装配成格架 13， 随后将燃料棒 14装入格架 13的栅格单元内。 为确保燃 料棒 14安全装入栅格单元中， 需防止装配过程中燃料棒 14碰触到搅混翼， 而搅 混翼的外形制作要求严格， 不能随意变动， 然而搅混翼与条带在一体成型过程 中需要考虑工艺尺寸公差和装配公差带来的影响， 使得搅混翼不能占据栅格单 元过多的面积， 通常需在燃料棒 14与搅混翼之间留有足够的间隙。
[0005] 该间隙是影响冷却循环过程中热工余量的一个关键因素， 若间隙过大， 搅混翼 产生的横向流动较弱， 对冷却剂流体产生的效力过小； 同吋， 在搅混过程中， 越靠近燃料棒 14的搅混翼部分越能破坏燃料棒 14表面的流体层， 继而对燃料棒 1 4的影响越大， 因此过大的间隙无法有效破坏燃料棒 14表面的流体层， 搅混效果 减弱。 综上， 如何在确保热工余量的同吋， 避免燃料棒 14与搅混翼发生干涉， 是目前有待解决的问题。
技术问题
[0006] 本发明要解决的技术问题在于， 针对如何在确保热工余量的同吋、 避免燃料棒 与搅混翼发生干涉， 提供一种燃料组件及其装配方法。
问题的解决方案
技术解决方案
[0007] 本发明解决其技术问题所采用的技术方案是： 提供了一种燃料组件的装配方法 ， 包括： 冲制条带并在条带上预成型搅混翼； 装配条带以形成具有若干栅格单 元的格架； 在格架上二次成型搅混翼； 以及沿纵向在栅格单元中装入燃料棒。
[0008] 在根据本发明实施例的燃料组件的装配方法中， 冲制条带并在条带上预成型搅 混翼中， 冲制条带的同吋一体冲制搅混翼。
[0009] 在根据本发明实施例的燃料组件的装配方法中， 切割预成型的搅混翼以二次成 型搅混翼。
[0010] 在根据本发明实施例的燃料组件的装配方法中， 切割包括激光切割。
[0011] 在根据本发明实施例的燃料组件的装配方法中， 采用激光切割同吋二次成型多 个搅混翼。
[0012] 在根据本发明实施例的燃料组件的装配方法中， 采用激光切割同吋二次成型多 个栅格单元的搅混翼； 且燃料棒沿纵向依次穿过该多个栅格单元。
[0013] 在根据本发明实施例的燃料组件的装配方法中， 确定栅格单元中待设燃料棒的 圆心， 并以圆心为轴心、 以大于燃料棒半径的长度为轴切割该栅格单元的条带 上的预成型的搅混翼。
[0014] 在根据本发明实施例的燃料组件的装配方法中， 搅混翼的外轮廓包括第一段和 第二段， 在一个栅格单元内第一段邻近燃料棒； 在预成型搅混翼中定型第二段 并预定型第一段， 在二次成型搅混翼中定型第一段。
[0015] 本发明还提供了一种燃料组件， 包括格架以及沿纵向安装于格架中的燃料棒； 格架包括多个条带， 条带彼此相交配合形成多个栅格单元， 燃料棒对应位于栅 格单元内， 条带上还设有搅混翼， 条带与搅混翼为一体冲制成型结构， 且搅混 翼还包括二次成型部分。
[0016] 在根据本发明实施例的燃料组件中， 搅混翼与燃料棒邻近的外轮廓与燃料棒之 间的间隙不大于 2mm。
[0017] 在根据本发明实施例的燃料组件中， 搅混翼的外轮廓包括第一段和第二段， 在 一个栅格单元内第一段邻近燃料棒； 第一段为弧形段， 并与邻近的燃料棒共圆 心。
发明的有益效果
有益效果
[0018] 实施本发明具有以下有益效果： 装配方法中， 可采用常规的冲制方法在冲制条 带的同吋仅预成型搅混翼， 随后可采用高精度的制备方法对预成型的搅混翼进 行二次成型以定型搅混翼， 在二次成型搅混翼的过程中， 因制备精度提高， 减 少了尺寸公差和装配公差带来的影响， 从而可在安全性能得到保障的基础上相 应增大搅混翼的面积， 减少搅混翼与燃料棒之间的间隙大小。 搅混翼在栅格单 元中的面积增大后， 产生的横向流动增强， 从而对冷却剂流体产生的效力提高 ； 同吋， 间隙减少使得搅混翼相对更靠近燃料棒， 从而可在燃料棒附近有效破 坏燃料棒表面的流体层， 搅混效果增强。
对附图的简要说明
附图说明
[0019] 下面将结合附图及实施例对本发明作进一步说明， 附图中：
[0020] 图 1是现有技术中燃料组件的结构示意图；
[0021] 图 2是依据本发明第一实施例的燃料组件的装配方法的流程图；
[0022] 图 3是依据本发明实施例的一预定型的搅混翼的结构示意图；
[0023] 图 4是依据本发明实施例的另一预定型的搅混翼的结构示意图；
[0024] 图 5是依据本发明一实施例的燃料组件的局部截面结构示意图；
[0025] 图 6是依据本发明一具体实施方式的搅混翼的结构示意图。 实施该发明的最佳实施例
本发明的最佳实施方式
[0026] 参见图 2， 依据本发明第一实施例的燃料组件的装配方法包括： 步骤 S100、 冲 制条带并在条带上预成型搅混翼； 步骤 S200、 装配条带以形成具有若干栅格单 元的格架； 步骤 S300、 在格架上二次成型搅混翼； 以及步骤 S400、 沿纵向在栅 格单元中装入燃料棒。
[0027] 在上述装配方法中， 可采用常规的冲制方法在冲制条带的同吋仅预成型搅混翼 ， 随后可采用高精度的制备方法对预成型的搅混翼进行二次成型以定型搅混翼 ， 在二次成型搅混翼的过程中， 因制备精度提高， 减少了尺寸公差和装配公差 带来的影响， 从而可在安全性能得到保障的基础上相应增大搅混翼的面积， 减 少搅混翼与燃料棒之间的间隙大小。 搅混翼在栅格单元中的面积增大后， 产生 的横向流动增强， 从而对冷却剂流体产生的效力提高； 同吋， 间隙减少使得搅 混翼相对更靠近燃料棒， 从而可在燃料棒附近有效破坏燃料棒表面的流体层， 搅混效果增强。
[0028] 此处虽未详细描述步骤 S200和 S400， 但是本领域的普通技术人员可合理使用现 有技术中任意适合的方法实施步骤 S200和 S400， 文中不再赘述。 应当知晓的是 ， 任何基于本发明的教导形成的技术方案， 均在本发明的保护范围之内。
[0029] 依据本发明第二实施例的燃料组件的装配方法中， 对于步骤 S100， 冲制条带的 同吋一体冲制形成搅混翼， 预成型的搅混翼和条带为一体结构， 从而仍能保持 搅混翼与条带的稳定相连， 避免搅混翼从条带上脱落。
[0030] 依据本发明第三实施例的燃料组件的装配方法中， 对于步骤 S300， 可对 S100中 预成型的搅混翼进行切割， 以二次成型搅混翼， 从而最终定型搅混翼。 该切割 方式包括激光切割、 线切割等多种非接触式切割或软接触式方式， 通过设定切 割路径实现搅混翼的最终成型。 采用易于聚焦的切割方式进行二次成型， 可提 高搅混翼定型精度； 另， 切割路径易于调节， 可实现同吋切割多个搅混翼， 从 而提高生产效率。 与此同吋， 切割过程中的热影响区对搅混翼的最终成型影响 不大， 在可接受范围内。
[0031] 例如， 可采用激光切割二次成型搅混翼， 进一步地， 还可采用激光切割同吋二 次成型多个搅混翼。 通常， 采用激光切割可同吋二次成型多个栅格单元的搅混 翼， 燃料棒沿纵向依次穿过该多个栅格单元， 即可沿纵向同吋切割位于同一纵 向上的多个搅混翼。
[0032] 在上述第三实施例的一具体实施方式中， 在步骤 S300中， 首先确定栅格单元中 待设燃料棒的圆心位置， 并以此圆心为轴心、 以大于燃料棒半径的长度为轴切 割该栅格单元的条带上的预成型的搅混翼。 具体参见图 3， 条带上预定型的搅混 翼 160a包括第一部分 161a和第二部分 162a， 第二部分 162a相对更靠近后续将要装 入的燃料棒。 步骤 S300中， 以有待装入的燃料棒的圆心位置为轴心、 以大于燃 料棒半径的长度为轴， 采用画圆的方式切割预定型的搅混翼 160a， 去除第二部分 162a, 从而得到最终定型的搅混翼。 所画圆的半径大于待设燃料棒的半径， 例如 两个半径的长度差不大于 2mm， 切割线 163a为所画圆的一个扇形段， 也可称为 弧形段， 该切割线 163a与装入后的燃料棒外表面之间的间隙即上述搅混翼与燃料 棒之间的间隙， 该间隙不大于 2mm。 由此获得的搅混翼的外轮廓包括第一段和 第二段， 第一段为沿切割线 163a切割获得的轮廓段， 第二段为除第一段之外的其 他轮廓段， 第一段在搅混翼所在的栅格单元内更接近燃料棒， 且第一段为弧形 或扇形， 并与该栅格单元内相邻近的燃料棒共圆心， 采用该同心结构， 可显著 提升搅混翼的效率。
[0033] 图 3示出的预定型的搅混翼 160a的结构仅用作举例， 并不是对本发明的限制， 本领域的普通技术人员可基于本发明的教导， 为方便将燃料棒装入栅格单元而 选择任意适合的预定型的搅混翼的结构， 此处不再一一列举。 例如， 参见图 4， 其示出了另一种预定型的搅混翼 160b的结构， 该预定型的搅混翼 160b包括第一 部分 161b和第二部分 162b， 第二部分 162b相对更靠近燃料棒， 第一部分 161b和 第二部分 162b之间的分隔线 163b为步骤 S300中的切割线。
[0034] 依据本发明第四实施例的燃料组件的装配方法中， 搅混翼的外轮廓包括第一段 和第二段， 在一个栅格单元内， 第一段相对更靠近燃料棒， 且第一段与燃料棒 外表面之间的间隙为上述搅混翼与燃料棒之间的间隙。 对于步骤 S100， 在预定 型搅混翼过程中， 定型搅混翼的第二段， 并预定型第一段； 对于步骤 S300， 在 二次成型搅混翼的过程中， 定型所述第一段， 最终定型整个搅混翼。 [0035] 本发明还提供了一种燃料组件， 采用依据本发明任意实施例的装配方法装配而 成。 参见图 5， 依据本发明一实施例的燃料组件包括格架以及沿纵向安装于格架 中的燃料棒 14; 其中， 格架包括多个条带 131， 条带 131彼此相交配合形成多个 栅格单元 130， 燃料棒 14对应位于栅格单元 130内， 条带 131上还设有搅混翼 16， 条带与搅混翼为一体冲制成型结构， 且搅混翼还包括二次成型部分。 该二次成 型部分的制备精度提高， 减少了尺寸公差和装配公差带来的影响， 从而可在安 全性能得到保障的基础上相应增大搅混翼的面积， 以减少搅混翼与燃料棒之间 的间隙。
[0036] 参见图 6， 在一具体实施方式中， 搅混翼 26包括第一部分 261和第二部分 262， 第二部分 262在栅格单元内更接近燃料棒， 第一部分 261与第二部分 262之间的界 线 263并不实际存在， 仅为表述方便而定义， 第一部分 261与第二部分 262为一整 体。 第二部分 262中靠近燃料棒的外轮廓 26a为二次成型部分， 其他外轮廓 26b为 与条带的一体成型部分。
[0037] 仍参见图 5， 燃料组件中， 搅混翼 16与燃料棒 14邻近的外轮廓与燃料棒 14之间 的间隙 17不大于 2mm。 这个间隙 17比现有的常规间隙小。 通过减少间隙 17大小 可使得搅混翼 16在栅格单元 130中的面积增大后， 产生的横向流动增强， 从而对 冷却剂流体产生的效力提高； 同吋， 间隙 17减少使得搅混翼 16相对更靠近燃料 棒 14， 从而可在燃料棒 14附近有效破坏燃料棒 14表面的流体层， 搅混效果增强
[0038] 仍参见图 5， 在本发明的一示例实施方式的燃料组件中， 搅混翼 16的外轮廓包 括第一段 161和第二段 162， 第一段 161为弧形段； 在一个栅格单元 130内第一段 1 61邻近燃料棒 14， 并与邻近的燃料棒 14共圆心， 该共圆心结构可提高搅混翼 16 的工作效率。 基于上述圆心， 燃料棒 14的半径小于弧形段的半径 （具体可以是 弧形段的拟合半径） ， 且差值不大于 2mm。
[0039] 仍参见图 5， 在本发明的另一示例实施方式的燃料组件中， 条带 131上还设有刚 凸构件 18， 刚凸构件 18伸入栅格单元 130内并抵靠燃料棒 14的外表面。 具体地， 刚凸构件 18包括相连的支持部 181和抵靠部 182， 支持部 181为与条带 131相连的 刚性部件， 抵靠部 182为伸入栅格单元 130内并抵靠燃料棒 14的弹性部件。 围成 同一栅格单元 130的四个条带 131中的至少两个上分别设有刚凸构件 18， 因刚凸 构件 18用于抵靠燃料棒 14， 同一栅格单元 130的多个刚凸构件 18配合， 具有以燃 料棒 14的半径为半径的近似圆形拟合轮廓线 （图中未示出） ， 该近似圆形拟合 轮廓线与燃料棒 14的外表面轮廓线基本重合。
[0040] 相应地， 在步骤 S300中， 若格架的条带上设有刚凸构件， 可以燃料棒的半径为 半径对同一栅格单元内的多个刚凸构件做圆形拟合轮廓线， 该圆形拟合轮廓线 的圆心即可确定为带装入的燃料棒的圆心。
[0041] 可以理解的， 以上实施例仅表达了本发明的优选实施方式， 其描述较为具体和 详细， 但并不能因此而理解为对本发明专利范围的限制； 应当指出的是， 对于 本领域的普通技术人员来说， 在不脱离本发明构思的前提下， 可以对上述技术 特点进行自由组合， 还可以做出若干变形和改进， 这些都属于本发明的保护范 围； 因此， 凡跟本发明权利要求范围所做的等同变换与修饰， 均应属于本发明 权利要求的涵盖范围。

Claims
权利要求书 一种燃料组件的装配方法， 其特征在于， 包括： 冲制条带并在所述条 带上预成型搅混翼； 装配所述条带以形成具有若干栅格单元的格架； 在所述格架上二次成型所述搅混翼； 以及沿纵向在所述栅格单元中装 入燃料棒。
根据权利要求 1所述的燃料组件的装配方法， 其特征在于， 所述冲制 条带并在所述条带上预成型搅混翼中， 冲制所述条带的同吋一体冲制 所述搅混翼。
根据权利要求 1所述的燃料组件的装配方法， 其特征在于， 切割预成 型的所述搅混翼以二次成型所述搅混翼。
根据权利要求 3所述的格架的燃料组件的装配方法， 其特征在于， 所 述切割包括激光切割。
根据权利要求 4所述的燃料组件的装配方法， 其特征在于， 采用激光 切割同吋二次成型多个所述搅混翼。
根据权利要求 4所述的燃料组件的装配方法， 其特征在于， 采用激光 切割同吋二次成型多个栅格单元的搅混翼； 且所述燃料棒沿纵向依次 穿过该多个栅格单元。
根据权利要求 4所述的燃料组件的装配方法， 其特征在于， 确定所述 栅格单元中待设所述燃料棒的圆心， 并以所述圆心为轴心、 以大于所 述燃料棒半径的长度为轴切割该栅格单元的所述条带上的预成型的所 述搅混翼。
根据权利要求 1-7任一项所述的燃料组件的装配方法， 其特征在于， 所述搅混翼的外轮廓包括第一段和第二段， 在一个所述栅格单元内所 述第一段邻近所述燃料棒； 在所述预成型搅混翼中定型所述第二段并 预定型所述第一段， 在所述二次成型搅混翼中定型所述第一段。 一种燃料组件， 包括格架以及沿纵向安装于所述格架中的燃料棒； 所 述格架包括多个条带， 所述条带彼此相交配合形成多个栅格单元， 所 述燃料棒对应位于所述栅格单元内， 其特征在于， 所述条带上还设有 搅混翼， 所述条带与所述搅混翼为一体冲制成型结构， 且所述搅混翼 还包括二次成型部分。
[权利要求 10] 根据权利要求 9所述的燃料组件， 其特征在于， 所述搅混翼与所述燃 料棒邻近的外轮廓与所述燃料棒之间的间隙不大于 2mm。
[权利要求 11] 根据权利要求 9所述的燃料组件， 其特征在于， 所述搅混翼的外轮廓 包括第一段和第二段， 在一个所述栅格单元内所述第一段邻近所述燃 料棒； 所述第一段为弧形段， 并与邻近的所述燃料棒共圆心。
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DE1439362A1 (de) * 1964-04-09 1969-04-10 Siemens Ag Abstandshalter fuer Brennelemente
US3746619A (en) * 1970-06-01 1973-07-17 Continental Oil Co Nuclear reactor fuel element spacer assembly
US3933584A (en) * 1973-04-23 1976-01-20 Nuclear Fuel Services, Inc. Grid for nuclear fuel assembly
CN107195335A (zh) * 2017-05-22 2017-09-22 岭东核电有限公司 燃料组件及其装配方法
CN206849509U (zh) * 2017-05-22 2018-01-05 岭东核电有限公司 燃料组件及用于燃料组件的格架

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1439362A1 (de) * 1964-04-09 1969-04-10 Siemens Ag Abstandshalter fuer Brennelemente
US3746619A (en) * 1970-06-01 1973-07-17 Continental Oil Co Nuclear reactor fuel element spacer assembly
US3933584A (en) * 1973-04-23 1976-01-20 Nuclear Fuel Services, Inc. Grid for nuclear fuel assembly
CN107195335A (zh) * 2017-05-22 2017-09-22 岭东核电有限公司 燃料组件及其装配方法
CN206849509U (zh) * 2017-05-22 2018-01-05 岭东核电有限公司 燃料组件及用于燃料组件的格架

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