WO2014166178A1 - 一种手征性耦合芯径光纤及其制造方法 - Google Patents

一种手征性耦合芯径光纤及其制造方法 Download PDF

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Publication number
WO2014166178A1
WO2014166178A1 PCT/CN2013/079970 CN2013079970W WO2014166178A1 WO 2014166178 A1 WO2014166178 A1 WO 2014166178A1 CN 2013079970 W CN2013079970 W CN 2013079970W WO 2014166178 A1 WO2014166178 A1 WO 2014166178A1
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Prior art keywords
core
preform
satellite
chiral
fiber
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English (en)
French (fr)
Inventor
杜城
陈伟
李诗愈
莫琦
张涛
柯一礼
罗文勇
杜琨
胡福明
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Fiberhome Telecommunication Technologies Co Ltd
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Fiberhome Telecommunication Technologies Co Ltd
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    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03B—MANUFACTURE, SHAPING, OR SUPPLEMENTARY PROCESSES
    • C03B37/00—Manufacture or treatment of flakes, fibres, or filaments from softened glass, minerals, or slags
    • C03B37/01—Manufacture of glass fibres or filaments
    • C03B37/012—Manufacture of preforms for drawing fibres or filaments
    • C03B37/01205—Manufacture of preforms for drawing fibres or filaments starting from tubes, rods, fibres or filaments
    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03B—MANUFACTURE, SHAPING, OR SUPPLEMENTARY PROCESSES
    • C03B37/00—Manufacture or treatment of flakes, fibres, or filaments from softened glass, minerals, or slags
    • C03B37/01—Manufacture of glass fibres or filaments
    • C03B37/012—Manufacture of preforms for drawing fibres or filaments
    • C03B37/01205—Manufacture of preforms for drawing fibres or filaments starting from tubes, rods, fibres or filaments
    • C03B37/01225—Means for changing or stabilising the shape, e.g. diameter, of tubes or rods in general, e.g. collapsing
    • C03B37/01228—Removal of preform material
    • C03B37/01234—Removal of preform material to form longitudinal grooves, e.g. by chamfering
    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03B—MANUFACTURE, SHAPING, OR SUPPLEMENTARY PROCESSES
    • C03B37/00—Manufacture or treatment of flakes, fibres, or filaments from softened glass, minerals, or slags
    • C03B37/01—Manufacture of glass fibres or filaments
    • C03B37/02—Manufacture of glass fibres or filaments by drawing or extruding, e.g. direct drawing of molten glass from nozzles; Cooling fins therefor
    • C03B37/025—Manufacture of glass fibres or filaments by drawing or extruding, e.g. direct drawing of molten glass from nozzles; Cooling fins therefor from reheated softened tubes, rods, fibres or filaments, e.g. drawing fibres from preforms
    • C03B37/027—Fibres composed of different sorts of glass, e.g. glass optical fibres
    • C03B37/02745—Fibres having rotational spin around the central longitudinal axis, e.g. alternating +/- spin to reduce polarisation mode dispersion
    • G—PHYSICS
    • G02—OPTICS
    • G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
    • G02B6/00—Light guides; Structural details of arrangements comprising light guides and other optical elements, e.g. couplings
    • G02B6/02—Optical fibres with cladding with or without a coating
    • G02B6/02042—Multicore optical fibres
    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03B—MANUFACTURE, SHAPING, OR SUPPLEMENTARY PROCESSES
    • C03B2203/00—Fibre product details, e.g. structure, shape
    • C03B2203/10—Internal structure or shape details
    • C03B2203/18—Axial perturbations, e.g. in refractive index or composition
    • C03B2203/20—Axial perturbations, e.g. in refractive index or composition helical
    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03B—MANUFACTURE, SHAPING, OR SUPPLEMENTARY PROCESSES
    • C03B2203/00—Fibre product details, e.g. structure, shape
    • C03B2203/32—Eccentric core or cladding
    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03B—MANUFACTURE, SHAPING, OR SUPPLEMENTARY PROCESSES
    • C03B2203/00—Fibre product details, e.g. structure, shape
    • C03B2203/34—Plural core other than bundles, e.g. double core
    • G—PHYSICS
    • G02—OPTICS
    • G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
    • G02B6/00—Light guides; Structural details of arrangements comprising light guides and other optical elements, e.g. couplings
    • G02B6/02—Optical fibres with cladding with or without a coating
    • G02B6/02057—Optical fibres with cladding with or without a coating comprising gratings
    • G02B6/02076—Refractive index modulation gratings, e.g. Bragg gratings
    • G02B6/0208—Refractive index modulation gratings, e.g. Bragg gratings characterised by their structure, wavelength response
    • G02B6/02085—Refractive index modulation gratings, e.g. Bragg gratings characterised by their structure, wavelength response characterised by the grating profile, e.g. chirped, apodised, tilted, helical
    • G02B2006/0209—Helical, chiral gratings

Definitions

  • the present invention relates to the field of fiber laser transmission and amplification, and in particular to a chiral coupled core fiber and a method of fabricating the same.
  • Fiber laser is a laser that uses optical fiber as the fiber medium. Fiber laser has become one of the mainstream lasers in laser applications due to its high conversion efficiency, good heat dissipation performance and stability.
  • the chiral coupling core fiber can realize the large mode field fiber characteristics, and can realize the single mode output of the laser fiber through the periodic surround satellite core suppression high-order mode transmission in the fiber. . Therefore, the chiral coupling core fiber can achieve the output power of the fiber laser.
  • the chiral coupled core fiber comprises a quartz cladding material, a guiding core located at the inner center of the quartz cladding material, and at least one satellite core surrounding the core of the guiding bow i.
  • the existing chiral coupling core fiber is generally manufactured by a jacketed rod (RIT) method or a mechanical drilling method.
  • RIT jacketed rod
  • the sleeve rod and the drilling method are used to manufacture the chiral coupling core fiber.
  • the coupled core fiber is used to control the rotation speed of the satellite core preform and the pressure inside the casing during the wire drawing process. In the drawing process, due to the satellite core preform in the casing and the guiding core preform, it is difficult to fit closely.
  • the air pressure in the casing needs to be adjusted online to avoid the air clamp.
  • the fiber is inserted into the fiber, and the waveguide structure is easily deformed.
  • the accuracy of different chiral coupling core fibers is difficult to be uniform, and the process repeatability is poor, which is not suitable for mass production.
  • the circular machining hole is first drilled through the mechanical drill in the guiding core preform slightly away from the central axis, and then the satellite core preform is inserted into the circle.
  • the guiding core preform and the satellite core preform are formed into a chiral coupling core fiber by a rotating wire drawing process.
  • the defect when manufacturing chiral coupling core fiber by mechanical drilling is -
  • the satellite core preform When drilling, the satellite core preform has a circular cross section, and the satellite core is located at the center of the satellite core preform. Since the satellite core preform is provided with a certain thickness of the cladding, the satellite The spacing between the core and the guiding core is large; in order to reduce the spacing between the satellite core and the guiding core i, it is necessary to reduce the aperture of the processed through hole and the volume of the satellite core preform, and reduce The aperture of the machined through hole and the volume of the satellite core preform are relatively sleepy Aiming at the defects existing in the prior art, the object of the present invention is to provide a chiral coupling core fiber and a manufacturing method thereof, and the chiral coupling core fiber manufactured by the invention not only has good optical performance and reliability, Moreover, it is less difficult to manufacture and is suitable for mass production.
  • the method for manufacturing a chiral coupling core fiber comprises the following steps: A. processing a guided core preform semi-finished product and a satellite core preform semi-finished product to form a satellite core prefabrication a rod and a lead core preform having a core slot; the shape of the core slot matching the shape of the satellite core preform; B.
  • the satellite core preform embedding the satellite core preform into a core slot, the satellite
  • the core of the satellite in the core preform, the center of the core slot and the guiding core in the guiding core preform are located on the same plane;
  • the tapered taper is formed at the end of the guiding core preform to form a chiral Coupling core diameter optical fiber preform;
  • the chiral coupling core diameter optical fiber preform is drawn at a temperature of 1800't: ⁇ 2200 ° C, drawing speed is 15m / min ⁇ i80m / min, wire drawing
  • the tension is (), 25N ⁇ 1, 42N;
  • the satellite core is rotated at a rotation speed of 18r min ⁇ 83 ⁇ 4 rain during the drawing process, and the satellite core is spirally wrapped around the guiding core, and the chiral coupling core fiber preform is used.
  • the output beam quality of the chiral coupled core fiber is less than 1.1, the fundamental mode loss is less than 0,5 dB/m, and the high-order mode loss is greater than 100 dBZra.
  • step A includes the following process: opening a core groove in a radial direction on an outer sidewall of the guiding core preform semi-finished product to form a guiding core preform with a core groove;
  • the shape of the trough processes the satellite core preform semi-finished product to form a satellite core preform having a shape that matches the shape of the satellite core preform.
  • step A includes the following processes: processing the satellite core preform semi-finished product; forming a satellite core preform; according to the shape of the satellite core preform, on the outer side of the guided core preform semi-finished product
  • the wall opens in the radial direction of the core groove to form an opening A cored preform having a core slot, the shape of the core slot matching the shape of the processed fiber core preform.
  • the cross section of the core groove and the cross section of the guiding core preform are both rectangular.
  • the length of the cross section of the satellite core preform is 4.22 ⁇ 33 33 mm, and the width is 2.17 ⁇ ⁇ 17.87 ⁇ , and the dimension deviation between the satellite core preform and the core slot is less than 0.25. Mm.
  • the distance between the side wall of the satellite core preform and the guiding core and the satellite core is 1.84. Mm ⁇ 4.02mm.
  • step A and step B further include the following steps: polishing the core slot.
  • the diameter of the cladding of the guiding core preform semi-finished product is 12 mm to 72.02 mm, and the diameter of the guiding core is 3.50 mm to 16, 50 mm.
  • the chiral coupling core fiber provided by the present invention is manufactured by the above manufacturing method.
  • the chiral coupling core fiber has an output beam quality of less than 1.1, a fundamental mode loss of less than 0,5 dB/m, and a high order mode loss greater than i00 dBZm. .
  • the diameter of the chiral coupling core fiber is 400 ⁇ m ⁇ 410 ⁇ m ⁇ ⁇ .
  • the core groove is opened radially in the outer side wall of the guiding core preform semi-finished product, and the satellite core preform matched with the core groove is embedded in the core Inside the slot.
  • the invention only needs to open the core groove radially on the outer side wall of the guiding core preform semi-finished product through the numerical control machine tool.
  • Open core slot does not require high precision mechanical drill, open fiber
  • the process of the core groove is not only easy, but also the manufacturing cost is low; and the process of smoothing the inner wall of the core groove is less difficult, and the shape of the core groove and the shape of the satellite core preform are easily matched. Therefore, when the chiral coupling core fiber is manufactured by the method of the present invention, it is not only difficult to manufacture, but also has high work efficiency, and is suitable for mass production and large-scale production.
  • the center of the satellite core and the core slot in the satellite core preform and the guiding core in the guiding core preform are located on the same plane.
  • the satellite core can accurately surround the guiding core as required during drawing; the distance between the side wall of the satellite core preform and the satellite core and the satellite core is Imm ⁇ 49mm, satellite core and guide The core of the lead is close, which is easy to draw. Therefore, when the chiral coupling core fiber is manufactured by the invention, the satellite core is easily surrounded around the guiding core, and the position control of the satellite core and the guiding core is not only low, but also the waveguide structure can be accurately realized. Assume.
  • the output beam quality of the chiral coupled core fiber obtained by the manufacturing method of the present invention is less than Li, the fundamental mode loss is less than 0,5 dB/m, and the high order mode loss is greater than 100 dB/m; chiral coupling core fiber Both optical performance and reliability are good.
  • Figure 1 is a flow chart of the method of the present invention
  • FIG. 2 is a schematic structural view of a chiral coupling core fiber preform in the present invention
  • FIG. 3 is a schematic structural view of a chiral coupling core fiber in the present invention.
  • a method for manufacturing a chiral coupling core fiber includes the following steps:
  • Sh processes the guided core preform semi-finished product and the satellite core preform semi-finished product to form a satellite core preform 3 and a guided core preform 1 with a core slot 2; the shape and satellite of the core slot 2
  • the shape of the core preform 3 is matched, and the cross section of the core groove 2 and the cross section of the guide core preform 1 are both rectangular.
  • the diameter of the cladding of the guided core preform semi-finished product is 12mm ⁇ 72.02mm, the diameter of the guiding core 5 is 3,50 mm ⁇ l 6.50mm; the length of the cross section of the satellite core preform 3 is 4,22mm ⁇ 33mm, width 2.17mm ⁇ 17.87mm, .
  • the deviation between the satellite core preform 3 and the core slot 2 is less than 0.25mm.
  • S1 can be achieved in the following two ways -
  • Polishing the core groove 2 enables the core groove 2 to have a high finish and minimize impurities in the core groove 2.
  • the satellite core preform 3 is embedded in the polished core groove 2, the satellite core The preform 3 can be in close contact with the core groove 2.
  • the satellite core preform 3 is embedded in the core slot 2, after the satellite core preform 3 is embedded in the core slot 2, the satellite core 4 in the satellite core preform 3, the center 5 of the core slot 1 And the guiding core 5 in the guiding core preform 1 is located in the same plane, and the distance between the side wall of the satellite core preform 3 near the guiding core 5 and the satellite core 4 is 84 mm to 4.02 mm c
  • the satellite core 4 in the satellite core preform 3, the center 5 of the core slot 2 and the guiding core 5 in the guiding core preform i are located on the same plane to ensure that the satellite core 4 can be accurately spirally wound around Guide the core 5 weeks.
  • a melting taper is formed at the end of the guiding core preform 1 to form a chiral coupling core fiber preform 6.
  • the melting of the taper at the end of the guiding core preform 1 prevents the positioning of the core preform preform i and the satellite core preform 3 inside the guiding core preform 1, and the hand formed by the melting taper
  • the magnetic coupling preform 6 of the magnetic coupling is convenient for drawing.
  • the chiral coupling core fiber preform 6 is melt drawn at a temperature of 1800 ° C to 220 ° C.
  • the drawing speed is 15 m/mii! ⁇ 180m/min, drawing tension is 0,25N ⁇ 1, 42N; 18r mii in the drawing process!
  • the chiral coupling core fiber 7 has a diameter of 400 ⁇ to 4 ⁇ 0 ⁇ , an output beam quality of less than 1.1, a fundamental mode loss of less than 0 coordinator5 dB/m, and a high order mode loss of more than 100 dB/m.
  • the chiral coupling core fiber 7 in the embodiment of the present invention is fabricated by the above manufacturing method, and the chiral coupling core fiber 7 includes a guiding core 5 and a spiral surrounding the guiding core 5.
  • the chiral coupling core fiber 7 has a diameter of 400 ⁇ m to 4 ⁇ 0 ⁇ , an output beam quality of less than 1.1, a fundamental mode loss of less than 0 admitted5 dB/m, and a high order mode loss greater than l() (BZm.
  • Example 1 A chiral coupled core fiber 7 having a beam quality of 1.07 was fabricated.
  • a semi-finished core of a guide core preform having a cladding diameter of 42.10 mra and a guide core 5 having a diameter of 7.50 mm is selected, and the core groove 2 is opened radially in the outer side wall of the guide core preform semi-finished product.
  • the core preform 2 of the core slot 2 is guided.
  • the core groove 2 has a rectangular cross section, and the satellite core preform semi-finished product (the satellite core 4 rare earth doping inside the satellite core preform semi-finished product) is processed according to the shape of the core groove 2 to form a satellite core preform.
  • the cross section of the satellite core preform 3 is also rectangular, and has a length of 17. (5 mm) and a width of 9.60 mm; the dimensional deviation of the satellite core preform 3 from the core groove 2 is 0.15 mra.
  • the core slot 2 is polished, the satellite core preform 3 is embedded in the core slot 2, and after the satellite core preform 3 is embedded in the core slot 2, the satellite core 4 and the core slot in the satellite core preform 3
  • the center 5 of the second core 5 and the guiding core 5 in the guiding core preform 1 are located on the same plane, and the distance between the side wall of the satellite core preform 3 near the guiding core 5 and the satellite core 4 is 4, 02mm.
  • Melting taper is formed at the end of the guiding core preform 1 to form a chiral coupling core fiber preform 26; the chiral coupling core fiber preform 6 is melted and drawn at a temperature of 205 CTC, and the drawing speed is Ii()m/min, the drawing tension is 0.88N; the satellite core 4 is rotated at a rotation speed of 57iVmm during the drawing process, and the satellite core 4 is spirally wound around the guiding core 5, and the chiral coupling core fiber prefabrication After the rod 6 is drawn, a chiral coupling core fiber 7 is formed.
  • the outer coating of the chiral coupling core fiber 7 in Example 1 has a diameter of 564 ⁇ m ⁇ , and the diameter of the chiral coupling core fiber 7 is 4 () 2 ⁇ , the working wavelength is 1082, 05 nm, and the inner package
  • the layer has a numerical aperture of 0,46, a beam quality of 1,07, a cladding absorption coefficient of 2.97 dB/m, a fundamental mode loss of 0 J5 dB/m, and a high-order mode loss of i02 dBZm.
  • Example 2 A chiral coupling core fiber 7 having a beam quality of L09 was fabricated.
  • a guide core preform semi-finished product having a cladding diameter of 12.12 mra and a guide core 5 having a diameter of 3.60 mm is selected, and a core is opened radially on the outer side wall of the guide core preform semi-finished product.
  • the groove 2 forms a guide core preform 1 with the core groove 2 opened.
  • the core groove 2 has a rectangular cross section, and the satellite core preform semi-finished product (the satellite core 4 inside the satellite core preform semi-finished product is dilute) is processed according to the shape of the core groove 2 to form a satellite core prefabrication.
  • the satellite core preform 3 is also rectangular in cross section, having a length of 4.22 mra and a width of 2.17 mm; the dimensional deviation of the satellite core preform 3 from the core slot 2 is (lmm).
  • the core slot 2 is polished, the satellite core preform 3 is embedded in the core slot 2, and after the satellite core preform 3 is embedded in the core slot 2, the satellite core 4 and the core slot in the satellite core preform 3
  • the center 5 of the second core 5 and the guiding core 5 in the guiding core preform 1 are located on the same plane, and the distance between the side wall of the satellite core preform 3 near the guiding core 5 and the satellite core 4 is 1. 84mm.
  • Melt taper is formed at the end of the guiding core preform 1 to form a chiral coupling core fiber preform 6; the chiral coupling core fiber preform 6 is at 18 () (TC temperature) Drawing, drawing speed is 15m/miri, drawing tension is 0.25N; in the drawing process, the satellite core 4 is rotated at a rotation speed of 89r/mm, and the satellite core 4 is spirally wrapped around the guiding core 5, chiral coupling The core-diameter optical fiber preform 6 is drawn to form a chiral coupling core fiber 7.
  • the diameter of the outer coating of the chiral coupling core fiber 7 in Example 2 is 570 ⁇ , and the diameter of the chiral coupling core fiber 7 is 405 ⁇ , the working wavelength is i070.94 nm, and the inner cladding numerical aperture The ratio is 0.46, the beam quality is 1.09, the cladding absorption coefficient is 2.76 dB/m, the fundamental mode loss is 0.32 dB/m, and the high-order mode loss is 103 dB/m.
  • Example 3 A chiral coupled core fiber 7 having a beam quality of 1.01 was fabricated.
  • a semi-finished core of a guide core preform having a cladding diameter of 72.01 mm and a diameter of the guide core 5 of 16.40 mm is selected, and a core slot 2 is opened radially in the outer side wall of the guide core preform semi-finished product.
  • the core preform 2 of the core slot 2 is guided.
  • the core groove 2 has a rectangular cross section, and the satellite core prefabricated semi-finished product according to the shape of the core groove 2 (satellite core pre- The satellite core 4 rare earth doping inside the rod semi-finished product is processed to form a satellite core preform 3.
  • the satellite core preform 3 is also rectangular in cross section and has a length of 32.92 mm and a width of 17.87 mm ; the dimensional deviation of the satellite core preform 3 from the core slot 2 is 0, 23 nm.
  • the core slot 2 is polished, the satellite core preform 3 is embedded in the core slot 2, and after the satellite core preform 3 is embedded in the core slot 2, the satellite core 4 and the core slot in the satellite core preform 3
  • the center 5 of the core 5 and the guiding core 5 in the guiding core preform 1 are located on the same plane, and the distance between the side wall of the satellite core preform 3 near the guiding core 5 and the satellite core 4 is 3. () 8mm.
  • Melt taper is formed at the end of the guiding core preform 1 to form a chiral coupling core diameter optical fiber preform 6; the chiral coupling core diameter optical fiber preform 6 is melted and drawn at 220 (TC temperature, drawing The speed is I 80mZmin, the drawing tension is L42N; the satellite core 4 is rotated at the rotation speed of i 8r/min during the drawing process, and the satellite core 4 is spirally wrapped around the guiding core 5, and the chiral coupling core fiber prefabrication After the rod 6 is drawn, a chiral coupling core fiber 7 is formed.
  • the diameter of the outer coating of the chiral coupling core fiber 7 in Example 3 is 570 ⁇
  • the diameter of the chiral coupling core fiber 7 is 410 ⁇
  • the working wavelength is ⁇ 068
  • the numerical aperture of the 77 ⁇ inner cladding is 0.46
  • the beam quality is 1.01
  • the cladding absorption coefficient is 2.01dB/m
  • the fundamental mode loss is 0.45dB/m
  • the high-order mode loss is ll ldB/m.

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Abstract

一种手征性耦合芯径光纤及其制造方法，涉及光纤激光传输与放大领域。该制造方法包括以下步骤：对导引纤芯预制棒半成品和卫星纤芯预制棒半成品进行加工，形成卫星纤芯预制棒和开有纤芯槽的导引纤芯预制棒；将卫星纤芯预制棒嵌入纤芯槽；在导引纤芯预制棒的端部进行熔融拉锥，形成手征性耦合芯径光纤预制棒；将手征性耦合芯径光纤预制棒熔融拉丝，形成手征性耦合芯径光纤。该手征性耦合芯径光纤的输出光束质量小于1.1，基模损耗小于0.5dB/m，高阶模损耗大于100dB/m。

Description

本发明涉及光纤激光传输与放大领域，具体涉及一种手征性耦合 芯径光纤及其制造方法。
光纤激光器是采用光纤作为光纤介质的激光器，光纤激光器以其 高转换效率、 良好散热性能和稳定性的特点， 已成为激光器应用领域 的主流激光器之一。
随着激光器应用领域的不断扩展，用户对光纤激光器输出功率的 需求越来越高。人们一般采用大模场面积光纤来提升光纤激光器的输 出功率； 由于大模场光纤纤芯中的激光模式振荡会造成光束质量下 降， 因此为了优化光束质量， 人们一般采取降低光纤纤芯的数值孔径 的方式。 但是， 光纤纤芯数值孔径下降会造成光纤光束缚能力下降， 不利于光纤弯曲使用， 并且现有降低数值孔径的幅度有限。
随着时代的进步，人们发现手征性耦合芯径光纤在能够实现大模 场面积光纤特性的同时，可以通过周期性环绕的卫星纤芯抑制光纤中 高阶模式传输， 实现激光光纤的单模输出。 因此， 手征性耦合芯径光 纤可以实现光纤激光器的输出功率的目的。手征性耦合芯径光纤包括 石英包层材料、位于石英包层材料内部中心的导引纤芯和至少一根螺 旋环绕于导弓 i纤芯周围的卫星纤芯。
现有的手征性耦合芯径光纤的制造时一般采用管套棒 （RIT) 法 或者机械钻孔法。但是，管套棒和钻孔法制造手征性耦合芯径光纤时， 分别存在以下缺陷- 采用管套棒法制造手征性耦合芯径光纤时，将导引纤芯预制棒和 卫星纤芯预制棒装在套管中， 对套管进行加温和拉丝， 形成手征性耦 合芯径光纤，拉丝过程中控制卫星纤芯预制棒装的旋转速度与套管内 的压力。管套棒法在拉丝过程中， 由于套管与导引纤芯预制棒中有卫 星纤芯预制棒， 难以紧密贴合， 旋转拉丝过程中需要在线调节套管中 的气压， 以避免空气线夹入光纤， 而且波导结构容易变形， 不同手征 性耦合芯径光纤的精度难以统一，工艺重复性差，不适合大批量生产。
采用机械钻孔法制造手征性耦合芯径光纤时，首先遥过机械钻在 导引纤芯预制棒中略偏离中心轴的位置钻圆形的加工通孔，然后将卫 星纤芯预制棒插入圆孔中，将导引纤芯预制棒和卫星纤芯预制棒通过 旋转的拉丝工艺形成手征性耦合芯径光纤。采用机械钻孔法制造手征 性耦合芯径光纤时的缺陷为-
( 1 ) 机械钻钻圆形的加工通孔时， 由于需要保证加工通孔内表 面的粗糙度、 以及加工通孔与卫星纤芯预制棒匹配度， 因此机械钻钻 加工通孔时需要较高的机械加工精度； 而且机械钻钻加工通孔， 机械 钻的钻头的力度难以控制， 随着加工通孔深度的增大， 机械钻的钻头 的尖端会产生向导引纤芯预制棒外壁方向甩动的离心力，进而造成加 工通孔的两端的尺寸不同。 因此， 采用机械钻孔法制造手征性耦合芯 径光纤制造难度较大， 不便于人们制造。
( 2 ) 钻孔法加工时， 卫星纤芯预制棒的横截面为圆形， 卫星纤 芯位于卫星纤芯预制棒的中心，由于卫星纤芯预制棒外部设置有一定 厚度的包层， 因此卫星纤芯与导引纤芯之间的间距较大； 为了减小卫 星纤芯与导弓 i纤芯之间的间距，必须减小加工通孔的孔径和卫星纤芯 预制棒的体积，减小加工通孔的孔径和卫星纤芯预制棒的体积比较困 针对现有技术中存在的缺陷，本发明的目的在于提供一种手征性 耦合芯径光纤及其制造方法，本发明制造的手征性耦合芯径光纤不仅 光学性能和可靠性均较好， 而且制造难度较低， 适合大批量生产。
为达到以上目的，本发明提供的种手征性耦合芯径光纤的制造方 法， 包括以下步骤： A、 对导引纤芯预制棒半成品和卫星纤芯预制棒 半成品进行加工，形成卫星纤芯预制棒和开有纤芯槽的导引纤芯预制 棒； 所述纤芯槽的形状与卫星纤芯预制棒的外形匹配； B、 将所述卫 星纤芯预制棒嵌入纤芯槽， 所述卫星纤芯预制棒内的卫星纤芯、纤芯 槽的中心和导引纤芯预制棒内的导引纤芯位于同一平面；在导引纤芯 预制棒的端部进行熔融拉锥， 形成手征性耦合芯径光纤预制棒； （、 将所述手征性耦合芯径光纤预制棒在 1800't：〜 2200°C的温度下瑢融 拉丝， 拉丝速度为 15m/min〜i80m/min， 拉丝张力为 （),25N〜1 ,42N; 拉丝过程中以 18r min〜8¾ rain的旋转速度旋转卫星纤芯， 将卫星纤 芯螺旋环绕于导引纤芯周围，手征性耦合芯径光纤预制棒拉丝后形成 手征性耦合芯径光纤；所述手征性耦合芯径光纤的输出光束质量小于 1.1 , 基模损耗小于 0,5dB/m， 高阶模损耗大于 100dBZra。
在上述技术方案的基础上， 步骤 A包括以下流程： 在导引纤芯 预制棒半成品的外侧壁沿径向开纤芯槽，形成开有纤芯槽的导引纤芯 预制棒； 根据纤芯槽的形状对卫星纤芯预制棒半成品进行加工， 形成 卫星纤芯预制棒， 所述纤芯槽的形状与卫星纤芯预制棒的外形匹配。
在上述技术方案的基础上， 步骤 A包括以下流程： 对卫星纤芯 预制棒半成品进行加工； 形成卫星纤芯预制棒； 根据卫星纤芯预制棒 的形状， 在导引纤芯预制棒半成品的外侧壁沿径向开纤芯槽， 形成开 有纤芯槽的导引纤芯预制棒，所述纤芯槽的形状与加工后的卫纤芯预 制棒的外形匹配。
在上述技术方案的基础上，所述纤芯槽的横截面和导引纤芯预制 棒的横截面均为矩形。
在上述技术方案的基础上，所述卫星纤芯预制棒的横截面的长度 为 4.22瞧〜 33mm， 宽度为 2.17匪〜 17.87匪， 所述卫星纤芯预制 棒与纤芯槽的尺寸偏差小于 0.25mm。
在上述技术方案的基础上， 步骤 B 中将所述卫星纤芯预制棒嵌 入纤芯槽后，所述卫星纤芯预制棒靠近导引纤芯的侧壁与卫星纤芯之 间的间距为 1.84mm〜4.02mm。
在上述技术方案的基础上， 步骤 A和步骤 B之间还包括以下步 骤： 对所述纤芯槽进行抛光。
在上述技术方案的基础上，所述导引纤芯预制棒半成品的包层的 直径为 12mm〜72.02mm, 所述导引纤芯的直径为 3.50 mm~16,50mm。
本发明提供的手征性耦合芯径光纤， 釆 ffl上述制造方法制成， 所 述手征性耦合芯径光纤的输出光束质量小于 1.1， 基模损耗小于 0,5dB/m, 高阶模损耗大于 i00dBZm。
在上述技术方案的基础上， 所述手征性耦合芯径光纤的直径为 400μιπ~410μιτΐο
与现有技术相比， 本发明的有益效果在于：
( ! ) 本发明制造手征性耦合芯径光纤时， 在导引纤芯预制棒半 成品的外侧壁沿径向开纤芯槽，将外形与纤芯槽匹配的卫星纤芯预制 棒嵌入纤芯槽内。与现有技术中通过机械钻钻加工遥孔制造的手征性 耦合芯径光纤相比，本发明只需通过数控机床在导引纤芯预制棒半成 品的外侧壁沿径向开纤芯槽， 开纤芯槽不需要高精度的机械钻， 开纤 芯槽的过程不仅比较容易， 制造成本较低； 而且纤芯槽内壁的光洁度 处理的工艺难度较低，纤芯槽的形状和卫星纤芯预制棒的外形容易匹 配。 因此， 通过本发明的方法制造手征性耦合芯径光纤时， 不仅制造 难度较低， 工作效率较高， 而且适合大批量、 规模化生产。
(2 ) 本发明将卫星纤芯预制棒嵌入纤芯槽后， 卫星纤芯预制棒 内的卫星纤芯、纤芯槽的中心和导引纤芯预制棒内的导引纤芯位于同 一平面， 卫星纤芯在拉丝时能够按照需求准确的环绕于导引纤芯周 围； 卫星纤芯预制棒靠近导引纤芯的侧壁与卫星纤芯之间的间距为 Imm〜49mm， 卫星纤芯与导引纤芯的距离较近， 便于拉丝。 因此， 本发明制造手征性耦合芯径光纤时，容易将卫星纤芯环绕于导引纤芯 周围， 卫星纤芯和导引纤芯的位置控制难度不仅较低， 而且能够精确 的实现波导结构设 。
(3 ) 通过本发明的制造方法制得的手征性耦合芯径光纤的输出 光束质量小于 Li，基模损耗小于 0,5dB/m,高阶模损耗大于 IOOdB/m; 手征性耦合芯径光纤光学性能和可靠性均较好。
图 1为本发明中方法的流程图；
图 2为本发明中手征性耦合芯径光纤预制棒的结构示意图； 图 3为本发明中手征性耦合芯径光纤的结构示意图。
图中： 1-导引纤芯预制棒， 2-纤芯槽， 3-卫星纤芯预制棒， 4-卫 星纤芯， 5-导引纤芯， 6手征性耦合芯径光纤预制棒， 7-手征性耦合 芯径光纤。 参见图 1、 图 2所示， 本发明实施例中的手征性耦合芯径光纤的 制造方法， 包括以下步骤：
Sh 对导引纤芯预制棒半成品和卫星纤芯预制棒半成品进行加 工， 形成卫星纤芯预制棒 3和开有纤芯槽 2的导引纤芯预制棒 1 ; 纤 芯槽 2的形状与卫星纤芯预制棒 3的外形匹配，纤芯槽 2的横截面和 导引纤芯预制棒 1的横截面均为矩形。
导引纤芯预制棒半成品的包层的直径为 12mm〜72.02mm，导引纤 芯 5的直径为 3,50 mm~l 6.50mm;卫星纤芯预制棒 3的横截面的长度 为 4,22mm〜33mm， 宽度为 2.17mm~ 17.87mm , .卫星纤芯预制棒 3 与纤芯槽 2的尺寸偏差小于 0.25mm。
为了满足眉户不同的需求， S1可以通过以下两种方式实现-
( 1 ) 在导引纤芯预制棒半成品的外侧壁沿径向开纤芯槽 2， 形 成开有纤芯槽 2的导引纤芯预制棒 1 ; 根据纤芯槽 2的形状对卫星纤 芯预制棒半成品进行加工， 形成卫星纤芯预制棒 3， 纤芯槽 2的形状 与卫星纤芯预制棒 3的外形匹配；
(2 ) 对卫星纤芯预制棒半成品进行加工； 形成卫星纤芯预制棒 3； 根据卫星纤芯预制棒 3的形状， 在导引纤芯预制棒半成品的外侧 壁沿径向开纤芯槽 2， 形成开有纤芯槽 2的导引纤芯预制棒 1， 纤芯 槽 2的形状与加工后的卫纤芯预制棒 3的外形匹配。
82： 对纤芯槽 2进行抛光处理。
对纤芯槽 2进行抛光处理能够使得纤芯槽 2的光洁度较高，将纤 芯槽 2内的杂质降到最低， 卫星纤芯预制棒 3嵌入抛光后的纤芯槽 2 时， 卫星纤芯预制棒 3能够与纤芯槽 2紧密贴合。
S3： 将卫星纤芯预制棒 3嵌入纤芯槽 2， 卫星纤芯预制棒 3嵌入 纤芯槽 2后， 卫星纤芯预制棒 3内的卫星纤芯 4、 纤芯槽 1的中心 5 和导引纤芯预制棒 1内的导引纤芯 5位于同一平面，卫星纤芯预制棒 3 靠近导引纤芯 5 的侧壁与卫星纤芯 4 之间的间距为 ,84mm〜 4.02mmc
卫星纤芯预制棒 3内的卫星纤芯 4、 纤芯槽 2的中心 5和导引纤 芯预制棒 i内的导引纤芯 5位于同一平面能够保证卫星纤芯 4能够准 确的螺旋环绕于导引纤芯 5周園。
S4:在导引纤芯预制棒 1的端部进行熔融拉锥， 形成手征性耦合 芯径光纤预制棒 6。
在导引纤芯预制棒 1 的端部进行熔融拉锥能够防止导引纤芯预 制棒 i和导引纤芯预制棒 1 内部的卫星纤芯预制棒 3发生位亍，熔融 拉锥形成的手征性耦合芯径光纤预制棒 6便于拉丝。
85： 将手征性耦合芯径光纤预制棒 6在 1800°C〜； 220()°C的温度下 熔融拉丝，拉丝速度为 15m/mii！〜 180m/min,拉丝张力为 0,25N〜1 ,42N; 拉丝过程中以 18r mii！〜 89r/min的旋转速度旋转卫星纤芯 4,将卫星纤 芯 4螺旋环绕于导引纤芯 5周園，手征性耦合芯径光纤预制棒 6拉丝 后形成手征性耦合芯径光纤。 手征性耦合芯径光纤 7 的直径为 400μπι〜4ί0μηι、 输出光束质量小于 1.1、 基模损耗小于 0„5dB/m、 高 阶模损耗大于 100dB/m。
参见图 3所示，本发明实施例中的手征性耦合芯径光纤 7通过上 述制造方法制成，手征性耦合芯径光纤 7包括导引纤芯 5和螺旋环绕 于导引纤芯 5周围的卫星纤芯 4。 该手征性耦合芯径光纤 7的直径为 400μπι〜4ί0μηι、 输出光束质量小于 1.1、 基模损耗小于 0„5dB/m、 高 阶模损耗大于 l()( BZm。
下面通过三个实施例进行具体说明。
实施例 1 : 制造光束质量为 1.07的手征性耦合芯径光纤 7。 选择包层直径为 42.10mra、导引纤芯 5的直径为 7.50mm的导引 纤芯预制棒半成品，在导引纤芯预制棒半成品的外侧壁沿径向开纤芯 槽 2, 形成开有纤芯槽 2的导引纤芯预制棒 1。 纤芯槽 2的横截面为 矩形， 根据纤芯槽 2的形状对卫星纤芯预制棒半成品（卫星纤芯预制 棒半成品内部的卫星纤芯 4稀土掺杂）进行加工， 形成卫星纤芯预制 棒 3。 卫星纤芯预制棒 3的横截面也为矩形， 其长度为 17.()5mm， 宽 度为 9.60mm; 卫星纤芯预制棒 3与纤芯槽 2的尺寸偏差为 0.15mra。
对纤芯槽 2进行抛光， 将卫星纤芯预制棒 3嵌入纤芯槽 2， 卫星 纤芯预制棒 3嵌入纤芯槽 2后， 卫星纤芯预制棒 3内的卫星纤芯 4、 纤芯槽 2的中心 5和导引纤芯预制棒 1内的导引纤芯 5位于同一平面， 卫星纤芯预制棒 3靠近导引纤芯 5的侧壁与卫星纤芯 4之间的间距为 4,02mm。
在导引纤芯预制棒 1的端部进行熔融拉锥，形成手征性耦合芯径 光纤预制棒 6;将手征性耦合芯径光纤预制棒 6在 205CTC的温度下熔 融拉丝， 拉丝速度为 i i()m/min， 拉丝张力为 0.88N; 拉丝过程中以 57iVmm的旋转速度旋转卫星纤芯 4, 将卫星纤芯 4螺旋环绕于导引 纤芯 5周围，手征性耦合芯径光纤预制棒 6拉丝后形成手征性耦合芯 径光纤 7。
经验证得出，实施例 1中的手征性耦合芯径光纤 7外部涂层的直 径为 564μιτι, 手征性耦合芯径光纤 7的直径为 4()2μηι、 工作波长为 1082,05nm、 内包层数值孔径为 0,46、 光束质量为 1 ,07、 包层吸收系 数为 2.97 dB/m、 基模损耗为 0J5dB/m、 高阶模损耗为 i02dBZm。
实施例 2: 制造光束质量为 L09的手征性耦合芯径光纤 7。
选择包层直径为 12.12mra、导引纤芯 5的直径为 3.60mm的导引 纤芯预制棒半成品，在导引纤芯预制棒半成品的外侧壁沿径向开纤芯 槽 2， 形成开有纤芯槽 2的导引纤芯预制棒 1。 纤芯槽 2的横截面为 矩形， 根据纤芯槽 2的形状对卫星纤芯预制棒半成品（卫星纤芯预制 棒半成品内部的卫星纤芯 4稀丄惨杂）进行加工， 形成卫星纤芯预制 棒 3。 卫星纤芯预制棒 3的横截面也为矩形， 其长度为 4.22mra， 宽 度为 2.17mm; 卫星纤芯预制棒 3与纤芯槽 2的尺寸偏差为 ( lmm。
对纤芯槽 2进行抛光， 将卫星纤芯预制棒 3嵌入纤芯槽 2， 卫星 纤芯预制棒 3嵌入纤芯槽 2后， 卫星纤芯预制棒 3内的卫星纤芯 4、 纤芯槽 2的中心 5和导引纤芯预制棒 1内的导引纤芯 5位于同一平面， 卫星纤芯预制棒 3靠近导引纤芯 5的侧壁与卫星纤芯 4之间的间距为 1 ,84mm。
在导引纤芯预制棒 1的端部进行熔融拉锥，形成手征性耦合芯径 光纤预制棒 6;将手征性耦合芯径光纤预制棒 6在 18()(TC的温度下瑢 融拉丝， 拉丝速度为 15m/miri， 拉丝张力为 0.25N; 拉丝过程中以 89r/mm的旋转速度旋转卫星纤芯 4， 将卫星纤芯 4螺旋环绕于导引 纤芯 5周围，手征性耦合芯径光纤预制棒 6拉丝后形成手征性耦合芯 径光纤 7。
经验证得出，实施例 2中的手征性耦合芯径光纤 7外部涂层的直 径为 570μια, 手征性耦合芯径光纤 7的直径为 405μΐϊΐ、 工作波长为 i070.94nm, 内包层数值孔径为 0.46、 光束质量为 1.09、 包层吸收系 数为 2。76dB/m、 基模损耗为 0.32dB/m、 高阶模损耗为 103dB/m。
实施例 3 : 制造光束质量为 1.01的手征性耦合芯径光纤 7。
选择包层直径为 72.01mm、 导引纤芯 5的直径为 16.40mm的导 引纤芯预制棒半成品，在导引纤芯预制棒半成品的外侧壁沿径向开纤 芯槽 2， 形成开有纤芯槽 2的导引纤芯预制棒 1。 纤芯槽 2的橫截面 为矩形， 根据纤芯槽 2的形状对卫星纤芯预制棒半成品（卫星纤芯预 制棒半成品内部的卫星纤芯 4稀土掺杂）进行加工， 形成卫星纤芯预 制棒 3。 卫星纤芯预制棒 3的横截面也为矩形， 其长度为 32.92mm, 宽度为 17。87mm; 卫星纤芯预制棒 3 与纤芯槽 2 的尺寸偏差为 0,23nim。
对纤芯槽 2进行抛光， 将卫星纤芯预制棒 3嵌入纤芯槽 2， 卫星 纤芯预制棒 3嵌入纤芯槽 2后， 卫星纤芯预制棒 3内的卫星纤芯 4、 纤芯槽 2的中心 5和导引纤芯预制棒 1内的导引纤芯 5位于同一平面， 卫星纤芯预制棒 3靠近导引纤芯 5的侧壁与卫星纤芯 4之间的间距为 3.()8mm。
在导引纤芯预制棒 1的端部进行熔融拉锥，形成手征性耦合芯径 光纤预制棒 6;将手征性耦合芯径光纤预制棒 6在 220(TC的温度下熔 融拉丝， 拉丝速度为 I 80mZmin， 拉丝张力为 L42N; 拉丝过程中以 i 8r/min的旋转速度旋转卫星纤芯 4， 将卫星纤芯 4螺旋环绕于导引 纤芯 5周围，手征性耦合芯径光纤预制棒 6拉丝后形成手征性耦合芯 径光纤 7。
经验证得出，实施例 3中的手征性耦合芯径光纤 7外部涂层的直 径为 570μηι， 手征性耦合芯径光纤 7的直径为 410μπι、 工作波长为 Ι068,77ηπ 内包层数值孔径为 0.46、 光束质量为 1.01、 包层吸系数 为 2.01dB/m、 基模损耗为 0.45dB/m、 高阶模损耗为 l l ldB/m。
本发明不局限于上述实施方式，对于本技术领域的普通技术人员 来说， 在不脱离本发明原理的前提下， 还可以做出若千改进和润饰， 这些改进和润饰也视为本发明的保护范围之内。本说明书中未作详细 描述的内容属于本领域专业技术人员公知的现有技术。

Claims

1. 一种手征性耦合芯径光纤的制造方法， 其特征在于： 包括以 下步骤：
A、 对导引纤芯预制棒半成品和卫星纤芯预制棒半成品进行加 工， 形成卫星纤芯预制棒（3)和开有纤芯槽（2) 的导引纤芯预制棒
(1)； 所述纤芯槽 （2) 的形状与卫星纤芯预制棒 （3) 的外形匹配；
B、 将所述卫星纤芯预制棒 （3) 嵌入纤芯槽 （2)， 所述卫星纤 芯预制棒 (3) 内的卫星纤芯 （4)、 纤芯槽 (2) 的中心 (5) 和导引 纤芯预制棒（1) 内的导引纤芯 （5)位亍同一平面； 在导引纤芯预制 棒（i) 的端部进行熔融拉锥， 形成手征性耦合芯径光纤预制棒（6);
C、 将所述手征性耦合芯径光纤预制棒（6)在 1800°C〜220(TC的 温度下熔融拉丝， 拉丝速度为 15m/mii！〜 80m/min， 拉丝张力为 0,25N〜i。42N; 拉丝过程中以 i8imin〜89r/min的旋转速度旋转卫星纤 芯 （4)， 将卫星纤芯 （4) 螺旋环绕于导引纤芯 （5)周围， 手征性耦 合芯径光纤预制棒 （6) 拉丝后形成手征性耦合芯径光纤 （7); 所述 手征性耦合芯径光纤 （7) 的输出光束质量小于 1J， 基模损耗小于 0.5dB/m, 高阶模损耗大于 100dB/ra。
2. 如权利要求 i所述的手征性耦合芯径光纤的制造方法， 其特 征在于， 步骤 A包括以下流程： 在导引纤芯预制棒半成品的外侧壁 沿径向开纤芯槽（2)， 形成开有纤芯槽（2) 的导引纤芯预制棒（1); 根据纤芯槽 （2) 的形状对卫星纤芯预制棒半成品进行加工， 形成卫 星纤芯预制棒 （3), 所述纤芯槽 （2) 的形状与卫星纤芯预制棒 （3) 的外形匹配。
3. 如权利要求 i 所述的手征性耦合芯径光纤的制造方法， 其特 征在于， 步骤 A包括以下流程： 对卫星纤芯预制棒半成品进行加工； 形成卫星纤芯预制棒 （3 ); 根据卫星纤芯预制棒 （3 ) 的形状， 在导 引纤芯预制棒半成品的外侧壁沿径向开纤芯槽（2)， 形成开有纤芯槽 (2 ) 的导引纤芯预制棒 （1 )， 所述纤芯槽（2 ) 的形状与加工后的卫 纤芯预制棒 （3 ) 的外形匹配。
4. 如权利要求 i 所述的手征性耦合芯径光纤的制造方法， 其特 征在于： 所述纤芯槽（2) 的横截面和导引纤芯预制棒（1 ) 的横截面 均为矩形。
5. 如权利要求 4所述的手征性耦合芯径光纤的制造方法， 其特 征在于：所述卫星纤芯预制棒（3 )的横截面的长度为 4.22mm〜33mm， 宽度为 2„17mm〜17,87mm， 所述卫星纤芯预制棒 （3 ) 与纤芯槽（2) 的尺寸偏差小于 0„25mm。
6. 如权利要求 I 所述的手征性耦合芯径光纤的制造方法， 其特 征在于： 步骤 B中将所述卫星纤芯预制棒 （3 ) 嵌入纤芯槽 （2) 后， 所述卫星纤芯预制棒（3 )靠近导引纤芯 （5 ) 的侧壁与卫星纤芯（4 ) 之间的间距为 1.84mm— 4.02mm。
7. 如权利要求 1至 6任一项所述的手征性耦合芯径光纤的制造 方法， 其特征在于： 步骤 A和步骤 B之间还包括以下步骤： 对所述 纤芯槽 （2 ) 进行抛光。
8. 如权利要求 1至 6任一项所述的手征性耦合芯径光纤的制造 方法， 其特征在于： 所述导引纤芯预制棒半成品的包层的直径为 12mra〜72.02ram， 所述导引纤芯 ( 5 ) 的直径为 3.50 mm〜l 6,50mm。
9. 一种手征性耦合芯径光纤， 其特征在于： 采用权利要求 1至 8 任一项所述的制造方法制成， 所述手征性耦合芯径光纤 （7 ) 的输出 光束质量小于！.1，基模损耗小于 0.5dB/m，高阶模损耗大于 100dB/m。
10. 如权利要求 9所述手征性耦合芯径光纤， 其特征在于： 所述 手征性; (7) 的直径为 400μηι〜410μιτ
PCT/CN2013/079970 2013-04-11 2013-07-24 一种手征性耦合芯径光纤及其制造方法 Ceased WO2014166178A1 (zh)

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