WO2018141128A1 - 一种用于涡轮叶片主导边双面同步激光冲击强化的方法 - Google Patents

一种用于涡轮叶片主导边双面同步激光冲击强化的方法 Download PDF

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WO2018141128A1
WO2018141128A1 PCT/CN2017/078518 CN2017078518W WO2018141128A1 WO 2018141128 A1 WO2018141128 A1 WO 2018141128A1 CN 2017078518 W CN2017078518 W CN 2017078518W WO 2018141128 A1 WO2018141128 A1 WO 2018141128A1
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laser
spot
turbine blade
leading edge
impact
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French (fr)
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鲁金忠
卢海飞
罗开玉
吴刘军
王长雨
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Jiangsu University
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Jiangsu University
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    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
    • C21D10/005—Modifying the physical properties by methods other than heat treatment or deformation by laser shock processing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B39/00—Burnishing machines or devices, i.e. requiring pressure members for compacting the surface zone; Accessories therefor
    • B24B39/006—Peening and tools therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/02—Positioning or observing the workpiece, e.g. with respect to the point of impact; Aligning, aiming or focusing the laser beam
    • B23K26/06—Shaping the laser beam, e.g. by masks or multi-focusing
    • B23K26/0604—Shaping the laser beam, e.g. by masks or multi-focusing by a combination of beams
    • B23K26/0619—Shaping the laser beam, e.g. by masks or multi-focusing by a combination of beams with spots located on opposed surfaces of the workpiece
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/02—Positioning or observing the workpiece, e.g. with respect to the point of impact; Aligning, aiming or focusing the laser beam
    • B23K26/06—Shaping the laser beam, e.g. by masks or multi-focusing
    • B23K26/062—Shaping the laser beam, e.g. by masks or multi-focusing by direct control of the laser beam
    • B23K26/0622—Shaping the laser beam, e.g. by masks or multi-focusing by direct control of the laser beam by shaping pulses
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/14—Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beam; Nozzles therefor
    • B23K26/146—Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beam; Nozzles therefor the fluid stream containing a liquid
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/352—Working by laser beam, e.g. welding, cutting or boring for surface treatment
    • B23K26/356—Working by laser beam, e.g. welding, cutting or boring for surface treatment by shock processing
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/02—Iron or ferrous alloys
    • B23K2103/04—Steel or steel alloys
    • B23K2103/05—Stainless steel
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/08—Non-ferrous metals or alloys
    • B23K2103/10—Aluminium or alloys thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/08—Non-ferrous metals or alloys
    • B23K2103/14—Titanium or alloys thereof
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2221/00—Treating localised areas of an article
    • C21D2221/02—Edge parts

Definitions

  • the invention relates to the field of surface engineering technology and laser processing technology, in particular to a method for double-sided synchronous laser impact strengthening of a leading edge of a turbine blade.
  • Laser shock peening/processing is a new type of surface enhancement technology that uses laser irradiation with short pulses (tens of nanoseconds) and high peak power density (>10 9 W/cm 2 ).
  • the laser beam is absorbed by the absorption layer after passing through the constraining layer, and the absorption layer obtains energy to form explosive vaporization evaporation, which generates a high-temperature and high-pressure plasma. Due to the constraint of the outer constraining layer, the plasma forms a high-pressure shock wave to the inside of the material.
  • the force effect of the shock wave is plastically deformed on the surface of the material, which causes the microstructure of the surface material to change, and generates residual compressive stress in the impact region, which improves the strength, hardness, wear resistance and stress corrosion resistance of the material. Improve the fatigue strength of key parts of key components of aerospace engines.
  • Turbine blades are one of the important parts of the engine. They have the characteristics of complex structure, variety, large quantity, great influence on engine performance, long design and manufacturing cycle, etc. Turbine blades generally bear large working stress and high working temperature. And the changes in stress and temperature are frequent and intense, in addition to the problems of corrosion and wear, and the working conditions are very demanding. Therefore, there is a need to improve the surface performance of turbine blades and increase the service life of aircraft turbine blades.
  • the double-sided simultaneous laser impact enhancement is applied to the front and back of the turbine blade, that is, the same laser impact process parameters (including pulse width, pulse energy, spot diameter) are used on the front and back of a certain point of the turbine blade, but this method will be in the blade.
  • the intermediate position produces a large tensile stress, which also brings about uneven enhancement of the leading edge of the entire blade.
  • One-sided impingement of the blade is also a way of strengthening the blade. Since the pulsed laser belongs to a Gaussian distribution, when the central region of the spot reaches the strengthening effect, the edge region of the spot cannot be reached, and when the edge region of the spot reaches the strengthening effect, the central region of the spot will have energy. If it is too high, it will easily cause macroscopic deformation and damage of the blade, and the best strengthening effect cannot be achieved.
  • the present invention proposes a method for double-sided synchronous laser impact enhancement of a leading edge of a turbine blade, that is, the same diameter and different pulses are used on the front and back of each point in the range of 8 to 10 mm of the leading edge of the blade.
  • the two laser beams of energy are simultaneously shocked, and the front laser pulse energy is greater than the back laser pulse energy.
  • the laser power density used on the front side is used to cause dynamic plastic deformation of the entire laser impact spot area, and the laser power density used on the back side is used.
  • the excessive shock wave pressure in the central area of the frontal impact spot is offset to avoid macroscopic deformation of the blade in the central area of the front impact spot.
  • the concrete steps are as follows: the fixture fixes the turbine blade, and the running water is used as the constraining layer, according to the dynamic yield strength of the material. Calculate the Hugoniot elastic limit of the material Where v is the Poisson's ratio of the material, wherein the laser spot of each impact point on the front side of the blade and the laser spot of each impact point on the opposite side of the blade are placed on a line perpendicular to the surface of the blade by a positioning device.
  • the laser control system enables the two lasers on the front and back sides to simultaneously strike.
  • the laser power density I 1 is used for lap laser shock enhancement on the front side of the leading edge of the turbine blade, wherein wherein the laser pulse energy E 1 is a front impact, the laser pulse width [tau], d is the diameter of the spot, the spot is calculated according to a circular Gaussian distribution and a peak pressure, peak positive pressure to give Where ⁇ is the plasma – material interaction coefficient, Z is the equivalent acoustic impedance, I 1 is the laser power density, and the front spot edge pressure Where P 1 (t) is the front peak pressure and R is the spot diameter. According to Where K F is a coefficient, generally taken as 1.1, t 1 is the thickness of the material, and d is the spot diameter.
  • the thickness t 0 of the material needs to satisfy 0 ⁇ t 0 ⁇ t 1 .
  • the laser power density I 2 used on the back side of the leading edge of the turbine blade is used to offset the excessive shock wave pressure in the central region of the frontal impact spot.
  • E 2 is the laser pulse energy of the back impact
  • ⁇ is the laser pulse width
  • d is the spot diameter.
  • the back peak pressure is obtained.
  • ⁇ is the plasma – material interaction coefficient
  • Z is the equivalent acoustic impedance
  • I 2 is the laser power density
  • R is the spot diameter.
  • E 1 is the laser pulse energy of the frontal impact
  • E 2 is the laser pulse energy of the back impact
  • P 1 is the front peak pressure
  • the turbine blade material is an aluminum alloy, a stainless steel, a titanium alloy or a nickel based alloy.
  • the laser impact path is reciprocating linear or bow-shaped; the laser spot is circular, and the laser shock enhancement parameters are as follows: spot diameter is 3 mm, pulse width is 8-30 ns, pulse energy is 2-15 J, and lateral and longitudinal overlap are 50. %.
  • the laser light intensity obeys the Gaussian distribution, and the temporal and spatial distribution of the pressure pulse is expressed by the following quasi-Gaussian formula: Where x is the surface coordinate and R is the spot diameter.
  • the invention has the beneficial effects that the lasing laser impact reinforcement is performed on the front side of the leading edge of the turbine blade by using a large laser power density, and the macroscopic deformation and damage of the blade in the central region of the spot are avoided, and finally the best strengthening effect is achieved.
  • Figure 1 is a schematic view of the overall impact of a turbine blade.
  • Figure 2 is a schematic view of the impact of the leading edge of the turbine blade.
  • Figure 3 is a schematic diagram of the double-sided impact action.
  • Figure 4 is a distribution diagram of shock waves at the center of the sample.
  • Table 1 compares the results of vibration fatigue test of turbine blades under different conditions.
  • 1, 2, 5 are laser beams
  • 3 is blades
  • 4 is a water spray pipe.
  • the invention adopts TC4 titanium alloy turbine blade.
  • the main mechanical properties of the material are density of 4.5 g ⁇ cm -3 , dynamic yield strength of 1.43 GPa, Poisson's ratio of 0.3, and water resistance of 1.14 ⁇ 10 6 g ⁇ Cm -2 ⁇ s -1 , the acoustic impedance is 2.75 ⁇ 10 6 g ⁇ cm -2 ⁇ s -1 .
  • the front and back sides of each point of the front and back sides of the leading edge of the turbine blade are simultaneously shocked by two laser beams of the same diameter and different pulse energies.
  • Figure 1 and Figure 2 are schematic diagrams of the overall impact of the turbine blade and the impact of the leading edge of the turbine blade.
  • the laser spot of each impact point on the front side of the blade and the laser spot of each impact point on the opposite side of the blade are placed on a line perpendicular to the surface of the blade.
  • the two lasers on the front and back can be simultaneously shocked.
  • Figure 3 and Figure 4 are the schematic diagram of the double-sided impact action and the distribution of the shock wave at the center of the sample.
  • the blade In order to produce dynamic plastic deformation of the entire laser impact spot area, the blade does not produce macroscopic deformation in the central area of the spot. The result is: P 1 >2.5 ⁇ H , 2 ⁇ H ⁇ P 1 -P 3 ⁇ 2.5 ⁇ H , P 2 -P 4 ⁇ H .
  • the vibration fatigue test was carried out on the blades after the impact.

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Abstract

一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其主要是在叶片（3）主导边8～10mm的范围内的每一个点正面和背面采用相同直径、不同脉冲能量的两束激光同步进行冲击，且正面激光脉冲能量大于背面激光脉冲能量，其中正面采用的激光功率密度，用来使整个激光冲击光斑区域产生动态塑性变形，背面采用的激光功率密度主要用来抵消正面冲击光斑中心区域过大的冲击波压力，避免在正面冲击光斑中心区域叶片（3）产生宏观变形，最终可以达到最佳的强化效果，是一种针对涡轮叶片和薄壁零件强化的有效方法。该发明可以应用到航空和民用中飞机涡轮、整体叶盘、汽轮机和水轮机等多个领域。

Description

一种用于涡轮叶片主导边双面同步激光冲击强化的方法 技术领域
本发明涉及表面工程技术与激光加工技术领域，具体涉及一种涡轮叶片主导边双面同步激光冲击强化的方法。
背景技术
激光冲击强化(laser shock peening/processing,LSP)是一种新型的表面强化技术，主要是采用短脉冲(几十纳秒)、高峰值功率密度(>109W/cm2)的激光辐照在金属表面，激光束通过约束层之后被吸收层吸收，吸收层从而获得能量形成爆炸性气化蒸发，产生高温高压的等离子体，由于外层约束层的约束，等离子体形成高压冲击波从而向材料内部传播，利用冲击波的力效应在材料表层发生塑性变形，使得表层材料微观组织发生变化，同时在冲击区域产生残余压应力，提高材料的强度、硬度、耐磨性和耐应力腐蚀性能，主要用于提高航空发动机关键构件关键部位的疲劳强度。
涡轮叶片是发动机重要的零部件之一，具有结构复杂、品种多、数量大、对发动机性能影响大、设计制造周期长等特点，涡轮叶片一般承受较大的工作应力和较高的工作温度，且应力和温度的变化比较频繁和剧烈，此外还有腐蚀和磨损的问题，对其工作条件的要求非常苛刻。因此，需要提高涡轮叶片表面性能，增加飞机涡轮叶片的服役寿命。通常国际上在涡轮叶片正反面采用双面同时激光冲击强化，即在涡轮叶片某一点的正反面采用相同激光冲击工艺参数(包括脉宽、脉冲能量、光斑直径)，但是这种方法会在叶片中间位置产生较大的拉应力，同时也会带来整个叶片主导边不均匀强化效果。叶片单面受冲也是叶片强化的一种方式，由于脉冲激光属于高斯分布，当光斑中心区域达到强化作用时，光斑边缘区域无法达到，而当光斑边缘区域达到强化作用时，光斑中心区域会能量过高，容易造成叶片的宏观变形与破坏，无法实现最佳的强化效果。
发明内容
为了解决上述问题，本发明提出了一种用于涡轮叶片主导边双面同步激光冲击强化的方法，即在叶片主导边8～10mm的范围内的每一个点正面和背面采用相同直径、不同脉冲能量的两束激光同步进行冲击，且正面激光脉冲能量大于背面激光脉冲能量，其中正面采用的激光功率密度，用来使整个激光冲击光斑区域产生动态塑性变形，背面采用的激光功率密度，用来抵消正面冲击光斑中心区域过大的冲击波压力，避免在正面冲击光斑中心区域叶片产生宏观变形。
其具体实步骤如下：夹具固定涡轮叶片，以流水作为约束层，根据材料的动态屈服强度
Figure PCTCN2017078518-appb-000001
计算出材料的Hugoniot弹性极限
Figure PCTCN2017078518-appb-000002
式中v为材料的泊松比，其中通过定位装置，使叶片正面的每一个冲击点的激光光斑和对应的叶片反面的每一个冲击点的激光光斑处于一条垂直于叶片表面的直线上，通过激光控制系统，使正反面的两束激光能够同步进行冲击。在涡轮叶片主导边正面采用激光功率密度I1进行搭接激光冲击强化，其中
Figure PCTCN2017078518-appb-000003
式中E1为正面冲击的激光脉冲能量，τ为激光脉宽，d为光斑直径，根据圆形光斑高斯分布规律以及峰值压力计算公式，得到正面峰值压力
Figure PCTCN2017078518-appb-000004
式中α为等离子体–材料相互作用系数，Z为折合声阻抗，I1为激光功率密度，正面光斑边缘压力
Figure PCTCN2017078518-appb-000005
式中P1(t)为正面峰值压力，R为光斑直径。又根据
Figure PCTCN2017078518-appb-000006
式中KF为系数，一般取1.1，t1为材料的厚度，d为光斑直径，
Figure PCTCN2017078518-appb-000007
为材料的动态屈服强度，可以得到材料的厚度t0需满足0<t0≤t1。而在涡轮叶片主导边背面采用的激光功率密度I2用来抵消正面冲击光斑中心区域过大的冲击波压力，其中
Figure PCTCN2017078518-appb-000008
式中E2为背面冲击的激光脉冲能量，τ为激光脉宽，d为光斑直径，根据圆形光斑高斯分布规律以及峰值压力计算公式，得到背面峰值压力
Figure PCTCN2017078518-appb-000009
式中α为等离子体–材料相互作用系数，Z为折合声阻抗，I2为激光功率密度，背面光斑边缘压力
Figure PCTCN2017078518-appb-000010
式中P2(t)为背面峰值压力，R为光斑直径。其中
Figure PCTCN2017078518-appb-000011
E1为正面冲击的激光脉冲能量，E2为背面冲击的激光脉冲能量，P1为正面峰值压力，为使整个激光冲击光斑区域产生动态塑性变形，而光斑中心区域叶片不产生宏观变形，满足P1>2.5σH，2σH≤P1-P3≤2.5σH，P2-P4≥σH。
所述涡轮叶片材料为铝合金、不锈钢、钛合金或镍基合金。
激光冲击路径为往复直线型或弓字形；激光光斑为圆形，激光冲击强化参数如下：光斑直径为3mm，脉宽为8-30ns，脉冲能量2-15J，横向和纵向搭接率均为50％。
激光光强服从高斯分布，压力脉冲的时空分布情况用如下准高斯公式表示：
Figure PCTCN2017078518-appb-000012
式中x，y是表面坐标，R是光斑直径。
本发明有益效果：在涡轮叶片主导边正面采用较大激光功率密度进行搭接激光冲击强化，而又避免光斑中心区域叶片产生宏观变形和破坏，最终达到最佳的强化效果。
附图说明
为了更清楚地说明本申请实施例或现有技术中的技术方案，下面将对实例或现有技术描述中所需要使用的附图作简单地介绍。
图1为涡轮叶片整体冲击示意图。
图2为涡轮叶片主导边冲击示意图。
图3为双面冲击作用原理图。
图4为试样中心位置冲击波的分布图。
表1为不同状态下涡轮叶片振动疲劳试验结果对比。
其中1、2、5是激光束，3是叶片，4是喷水管。
具体实施方式
下面结合附图和实施例对本发明的具体实施方式做详细的说明，但本发明不应仅限于实施例。
本发明所采用的是TC4钛合金涡轮叶片，该材料的主要力学性能是密度为4.5g·cm-3，动态屈服强度为1.43GPa，泊松比为0.3，水阻抗为1.14×106g·cm-2·s-1，声阻抗为2.75×106g·cm-2·s-1。
Figure PCTCN2017078518-appb-000013
实施例1：
涡轮叶片主导边单面采用激光脉宽τ＝10ns，激光脉冲能量E＝12J，光斑直径d＝3mm的脉冲激光进行冲击，并对冲击后的叶片进行振动疲劳试验。
实施例2：
涡轮叶片主导边正反面的每一个点正面和背面采用相同直径、相同脉冲能量的两束激光同步进行冲击，其中激光脉宽τ＝10ns，激光脉冲能量E＝12J，光斑直径d＝3mm，并对冲击后的叶片进行振动疲劳试验。
实施例3：
本发明的技术方案，涡轮叶片主导边正反面的每一个点正面和背面采用相同直径、不同脉冲能量的两束激光同步进行冲击。图1、图2分别是涡轮叶片整体冲击示意图和涡轮叶片主导边冲击示意图。通过定位装置，使叶片正面的每一个冲击点的激光光斑和对应的叶片反面的每一个冲击点的激光光斑处于一条垂直于叶片表面的直线上。通过激光控制系统，使正反面的两束激光能够同步进行冲击。涡轮叶片主导边正面采用激光脉宽为τ＝10ns，激光脉冲能量E1＝12J，光斑直径d＝3mm；涡轮叶片主导边背面采用激光脉宽为τ＝10ns，激光脉冲能量为E2＝12J，光斑直径d＝3mm。
Figure PCTCN2017078518-appb-000014
其中
Figure PCTCN2017078518-appb-000015
即
Figure PCTCN2017078518-appb-000016
可得t1＝8.8mm，即0<t0≤8.8mm
Figure PCTCN2017078518-appb-000017
Figure PCTCN2017078518-appb-000018
Figure PCTCN2017078518-appb-000019
图3、图4分别是双面冲击作用原理图和试样中心位置冲击波的分布图，为使整个激光冲击光斑区域产生动态塑性变形，而光斑中心区域叶片不产生宏观变形，结果满足：P1>2.5σH，2σH≤P1-P3≤2.5σH，P2-P4≥σH。并对冲击后的叶片进行振动疲劳试验。
从表1可以看出，未冲击(1-1、1-2)，单面冲击(2-1、2-2)，相同直径、相同脉冲能量双面同步冲击(3-1、3-2)以及相同直径、不同脉冲能量双面同步冲击(4-1、4-2)四个不同状态下的振动疲劳寿命试验，在430MPa、560MPa不同应力条件下，结果表明经过相同直径、不同脉冲能量双面同步冲击处理后的涡轮叶片的疲劳寿命明显提高，且满足：P1>2.5σH，2σH≤P1-P3≤2.5σH，P2-P4≥σH，最终实现光斑中心区域叶片不产生宏观变形和破坏，又达到最佳的强化效果。
表1
状态 应力/MPa 疲劳寿命
1-1(未冲击) 430 2.49×107
1-2(未冲击) 560 1.23×107
2-1(实施例1) 430 3×107
2-2(实施例1) 560 2.49×107
3-1(实施例2) 430 3.26×107
3-2(实施例2) 560 2.86×107
4-1(实施例3) 430 3.51×107
4-2(实施例3) 560 3.05×107

Claims (10)

  1. 一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于：在叶片主导边8～10mm的范围内的每一个点正面和背面采用相同直径、不同脉冲能量的两束激光同步进行冲击，且正面激光脉冲能量大于背面激光脉冲能量，其中正面采用的激光功率密度，用来使整个激光冲击光斑区域产生动态塑性变形，背面采用的激光功率密度用来抵消正面冲击光斑中心区域过大的冲击波压力，避免在正面冲击光斑中心区域叶片产生宏观变形，最终达到最佳的强化效果。
  2. 如权利要求1所述的一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于，具体步骤如下：夹具固定涡轮叶片，以流水作为约束层，其中通过定位装置，使叶片正面的每一个冲击点的激光光斑和对应的叶片反面的每一个冲击点的激光光斑处于一条垂直于叶片表面的直线上，通过激光控制系统，使叶片正反面的两束激光能够同步进行冲击，最终采用两种不同激光功率密度I1和I2的脉冲激光双面同步冲击涡轮叶片主导边。
  3. 如权利要求1或2所述的一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于，正反面的峰值压力分别为P1、P3，正反面光斑边缘的压力分别为P2、P4，为使整个激光冲击光斑区域产生动态塑性变形，而光斑中心区域叶片不产生宏观变形，满足P1>2.5σH，2σH≤P1-P3≤2.5σH，P2-P4≥σH；σH为涡轮叶片材料的Hugoniot弹性极限。
  4. 如权利要求1-3任一所述的一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于，所述涡轮叶片材料为铝合金、不锈钢、钛合金或镍基合金；涡轮叶片材料的Hugoniot弹性极限定义为：
    Figure PCTCN2017078518-appb-100001
    式中v为材料的泊松比，
    Figure PCTCN2017078518-appb-100002
    为动态屈服强度。
  5. 如权利要求1或2中所述的一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于：激光冲击路径为往复直线型或弓字形；激光光斑为圆形，激光冲击强化参数如下：光斑直径为3mm，脉宽为8-30ns，脉冲能量2-15J，横向和纵向搭接率均为50％。
  6. 如权利要求1或2所述的一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于，在涡轮叶片主导边正面采用激光功率密度I1进行搭接激光冲击强化，其 中
    Figure PCTCN2017078518-appb-100003
    式中E1为正面冲击的激光脉冲能量，τ为激光脉宽，d为光斑直径；而在涡轮叶片主导边背面采用的激光功率密度I2用来抵消正面冲击光斑中心区域过大的冲击波压力，其中
    Figure PCTCN2017078518-appb-100004
    式中E2为背面冲击的激光脉冲能量，τ为激光脉宽，d为光斑直径。
  7. 如权利要求3所述的一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于，根据圆形光斑高斯分布规律以及峰值压力计算公式，得到正面峰值压力
    Figure PCTCN2017078518-appb-100005
    式中α为等离子体–材料相互作用系数，Z为折合声阻抗，I1为激光功率密度，正面光斑边缘压力
    Figure PCTCN2017078518-appb-100006
    式中P1(t)为正面峰值压力，R为光斑直径；根据圆形光斑高斯分布规律以及峰值压力计算公式，得到背面峰值压力
    Figure PCTCN2017078518-appb-100007
    式中α为等离子体–材料相互作用系数，Z为折合声阻抗，I2为激光功率密度，背面光斑边缘压力
    Figure PCTCN2017078518-appb-100008
    式中P2(t)为背面峰值压力，R为光斑直径，其中
    Figure PCTCN2017078518-appb-100009
    E1为正面冲击的激光脉冲能量，E2为背面冲击的激光脉冲能量，P1为正面峰值压力。
  8. 如权利要求3所述的一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于，所述α为等离子体–材料相互作用系数，为经验系数，取0.1～0.25；
    Figure PCTCN2017078518-appb-100010
    其中Z1为靶材的声阻抗、Z2为约束层的声阻抗。
  9. 如权利要求1中所述的一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于：材料宏观变形所需的压力与材料厚度t0和动态屈服强度
    Figure PCTCN2017078518-appb-100011
    的关系：
    Figure PCTCN2017078518-appb-100012
    式中KF为系数，取1.1，t0为材料的厚度(mm)，
    Figure PCTCN2017078518-appb-100013
    为材料的动态屈服强度(GPa)，d为光斑直径。
  10. 如权利要求1中所述的一种用于涡轮叶片主导边双面同步激光冲击强化的方法，其特征在于：激光光强服从高斯分布，压力脉冲的时空分布情况用如下准高斯公式表示：
    Figure PCTCN2017078518-appb-100014
    式中x，y是表面坐标，R是光斑直径。
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