CN106893855A - A kind of turbo blade dominates the two-sided asynchronous excitation impact reinforcing method in side - Google Patents

A kind of turbo blade dominates the two-sided asynchronous excitation impact reinforcing method in side Download PDF

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CN106893855A
CN106893855A CN201710065831.0A CN201710065831A CN106893855A CN 106893855 A CN106893855 A CN 106893855A CN 201710065831 A CN201710065831 A CN 201710065831A CN 106893855 A CN106893855 A CN 106893855A
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laser
blade
shock
laser shock
double
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CN106893855B (en
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鲁金忠
段海峰
卢海飞
罗开玉
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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

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  • Engineering & Computer Science (AREA)
  • Optics & Photonics (AREA)
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Abstract

The two-sided asynchronous excitation impact reinforcing method in side is dominated the present invention relates to a kind of turbo blade.Asynchronous double-sided laser shock peening is carried out to the leading side of turbo blade using two beam laser beams of phase co-wavelength, pulsewidth, spot diameter, pulse energy, carried out along the leading side front of blade with one laser beam laser impact intensified, postpone a period of time overleaf carries out laser impact intensified, the laser impact intensified starting point of the leading side front and back of blade and to impact path identical in same position using the laser beam of another beam identical parameters；The time needed for frontal impact ripple travels to vacuum side of blade is less than for the time difference of the leading beam laser of side same position front and back two and front laser beam is first, continuously blade is carried out according to this two-sided asynchronous attack method it is laser impact intensified, until the leading side front and back whole shock zones impact of blade is completed.

Description

Double-sided asynchronous laser shock peening method for main guide edge of turbine blade
Technical Field
The invention relates to the field of laser processing, in particular to a method for realizing better strengthening effect of a main guide edge of a turbine blade by using a designed asynchronous double-sided laser shock strengthening method.
Technical Field
Laser Shock Peening (LSP) is a novel surface strengthening technology, and has the characteristics of three high and one fast: high energy (tens of J), high pressure (GPa-TPa), high strain rate (10)7S-1) And ultrafast (ns). The high-energy and ultra-fast laser penetrates through the transparent constraint layer to irradiate the surface of the metal material stuck with the absorption layer, the absorption layer absorbs the laser energy to quickly form explosive gasification evaporation to generate high-temperature and high-pressure plasma, the plasma absorbs the laser energy to form shock waves expanding outwards, the high-pressure shock waves are propagated to the inside of the material due to the constraint of the outer constraint layer, and the surface layer material is subjected to plastic deformation by utilizing the force effect of the shock waves, so that the microstructure of the surface layer material is changed, and meanwhile, residual compressive stress is introduced into an impact area, so that the strength, hardness, wear resistance, stress corrosion resistance and other properties of the material are improved, particularly, the fatigue fracture resistance of the material can be effectively improved, and the fatigue life of the material is prolonged.
When laser shock strengthening is carried out on the main guide edge of the turbine blade, the main guide edge of the turbine blade is thin, when laser energy is large, the pressure of shock waves generated by induction is too large, the main guide edge of the turbine blade is easy to generate macroscopic deformation, and the turbine blade is damaged, when the laser energy is small, the pressure of the shock waves generated by induction is too small, stable and maximum plastic deformation cannot be formed in the turbine blade, and the strengthening effect is not good. Therefore, how to generate the maximum plastic deformation inside the blade, obtain the best strengthening effect, and simultaneously not generate macroscopic deformation to cause blade damage becomes a problem which needs to be solved urgently.
Disclosure of Invention
Aiming at the problems, the invention provides a double-sided asynchronous laser shock strengthening method for a main guide edge of a turbine blade. Two laser beams with the same wavelength, pulse width, spot diameter and pulse energy are adopted to asynchronously carry out double-sided laser shock strengthening on the main guide edge of the turbine blade, namely one laser beam is used for carrying out laser shock strengthening along the front side of the main guide edge of the blade, the other laser beam with the same parameters is adopted to carry out laser shock strengthening on the back side at the same position after a period of time, and the starting point and the shock path of the laser shock strengthening on the front side and the back side of the main guide edge of the blade are the same; and for the time difference between the front laser beam and the back laser beam at the same position of the main guide edge, which is smaller than the time required by the front shock wave to propagate to the back of the blade, and the front laser beam is in advance, continuously carrying out laser shock strengthening on the blade according to the double-sided asynchronous shock method until the shock of all shock areas of the front and the back of the main guide edge of the blade is finished. Research shows that when the peak pressure P satisfies 2VHEL<P<2.5VHELWhen the method is used, the maximum plastic deformation can be obtained in the target material. According to the invention, the laser beam on the front side of the main guide edge of the blade is mainly used for generating plastic deformation, and the delayed laser beam on the back side is mainly used for offsetting shock wave pressure generating macroscopic deformation, so that the maximum plastic deformation is obtained, and meanwhile, the macroscopic deformation of the main guide edge of the blade caused by too large shock wave pressure on the front side of the main guide edge of the blade is avoided.
The specific implementation steps are as follows:
(1) determining the delay time t, t of the double-sided asynchronous laser shock peening of the leading edge of the turbine blade according to the material and the thickness of the turbine blade0For the time of propagation of a stress wave generated in the interior of the material to the bottom of the material, from t0＝L/C0，Calculated, wherein L is the thickness of the blade and C0The wave velocity of the stress wave, E is elastic modulus, upsilon is Poisson ratio, ρ is material density, and the delay time t of the double-sided asynchronous laser shock peening of the main guide edge of the turbine blade is 0<t<t0So that the shock waves induced by the laser on the front and back surfaces are spaced from the front surface of the blade inside the bladeAt a yield strength of the blade material under dynamic loading ofTo undergo permanent plastic deformation, the peak pressure generated by laser shock peening must be greater than the Hugoniot Elastic Limit (HEL) V of the materialHEL，VHELSatisfies the formula:where upsilon is a poisson ratio.
(2) Carrying out laser shock peening on the front surface of the main guide edge of the turbine blade by using laser beams, wherein the laser shock peening processing parameters are as follows: the laser pulse energy is 1-50J, the laser pulse width is 10-40ns, and the repetition frequency is 0.5-10 Hz; the diameter D of the light spot is 1-6mm, and the peak pressure of laser shock peening is controlled byThe distribution coefficient of the internal energy is shown as α, and is 0.1, I0In order to be the power density of the laser,e is laser energy (J), d is spot diameter (cm), τ is laser pulse width (ns), Z is reduced acoustic impedance, and Z is reduced acoustic impedancetargetIs the acoustic impedance of the target material, ZoverlayTo constrain the acoustic impedance of the layerThe laser intensity follows Gaussian distribution and the pressure pulse space-timeThe distribution is expressed by the following quasi-gaussian formula: p (x, y, t) ═ Pexp [ - (x)2+y2)/2R2]In the formula, x and y are surface coordinates, and R is a light spot radius; research shows that when the peak pressure P satisfies 2VHEL<P<2.5VHELDuring the process, the workpiece can obtain maximum plastic deformation, and the peak pressure of the shock wave can meet 2V for obtaining better laser shock strengthening effectHEL<P<2.5VHELAnd the pressure value P (R) of the light spot edge>VHELSo as to obtain the maximum plastic deformation of the blade, and the transverse and longitudinal lap joint rate of the laser shock strengthening is 50 percent.
(3) Starting timing after the starting point of the front laser shock peening of the main leading edge of the blade is impacted, and delaying for t seconds, and then starting laser shock peening on the same position of the back of the main leading edge of the blade by a second laser beam; the parameters of laser beams used for laser shock strengthening of the front side and the back side of the blade main guide edge are the same, the starting point and the shock path of the laser shock strengthening of the front side and the back side of the blade main guide edge are the same, and the transverse lapping rate and the longitudinal lapping rate are both 50%.
(4) And continuously carrying out laser shock strengthening on the main guide edge of the blade according to the double-sided asynchronous shock method until all shock areas on the front surface and the back surface of the main guide edge of the blade are shocked, and finishing the whole laser shock strengthening process.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the examples or the description of the prior art will be briefly described below.
FIG. 1 is a schematic diagram of double-sided asynchronous laser shock peening of a turbine blade leading edge.
FIG. 2 is a plan view of an aircraft turbine blade.
FIG. 3 is a schematic diagram showing the waveform of double-sided asynchronous laser shock peening of the leading edge of a turbine blade (in the figure, a laser beam 2 is emitted after a delay of t seconds after a laser beam 1 is emitted, and the laser beam is emittedThe shock wave induced by the beam 1 firstly propagates inside the main guide edge of the blade and then is separated from the front surface of the blade with the shock wave induced by the laser beam 2 inside the main guide edge of the bladeWhere L is the blade thickness, C0Shock waves of opposite directions cancel each other out at the wave velocity of the stress wave).
Table 1 shows the comparison of the residual stress of materials under different experimental parameters
The meanings of the reference symbols in the figures are as follows:
FIG. 1: 1. a laser beam; 2. a water injection system; 3. a second laser beam; 4. a blade.
FIG. 2: 4A, the front surface of the blade; 4B, blade back.
FIG. 3: 1. a laser beam; 3. a second laser beam; 4. a blade; 5. an absorbing layer; 6. a constraining layer; 7. a plasma shock wave.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings, but the present invention should not be limited to the embodiments.
The turbine blade double-sided asynchronous double-sided laser shock peening method adopted by the embodiment is shown in FIG. 1, and the sample material is TC 4.
A double-sided asynchronous laser shock peening method for a turbine blade main guide edge comprises the following specific steps:
(1) selecting TC4 as an example sample, wherein the blade thickness is 1mm, the elastic modulus of TC4 is 110GPa, the Poisson ratio is 0.34, and the density is 4.5g cm-3From the formulaCalculated to obtain C0Substituting 6132m/s into formula t0＝L/C0Get t016ns, where L is the blade thickness, C0And (3) regarding the wave velocity of the stress wave, wherein E is the elastic modulus, upsilon is the Poisson ratio, ρ is the material density, and the delay time t is 8ns, the shock waves induced by the laser at the front surface and the back surface meet at a position 3L/4 away from the front surface of the blade inside the blade, TC4 is the Poisson ratio upsilon is 0.34, the dynamic yield strength is 1.43GPa, and the Hugoniot elastic limit of TC4 is obtained:
(2) carrying out laser shock peening on the front surface of the main guide edge of the turbine blade by using a laser beam 1, wherein the laser shock peening processing parameters are as follows: the laser pulse energy is 7J, the laser pulse width is 10ns, and the repetition frequency is 1 Hz; the diameter d of the light spot is 3 mm; the laser shock peening peak power is given by:
wherein,substituting E ═ 10J, d ═ 3mm, τ ═ 10ns, α for 0.1, Zwater＝1.14×106g·cm-2·s-1，Ztarget＝2.75×106g·cm-2·s-1The value of the obtained P is 7.02GPa, and satisfies that 5.9GPa is 2VHEL<P<2.5VHEL＝7.375GPa。
Shock wave pressure P of the spot edge is 7.02 × exp (-R)2/2R2)＝4.26GPa＞2.95GPa＝VHELThe conditions are met, and the transverse and longitudinal lapping rate of laser shock strengthening is 50%.
(3) Timing is started after the starting point of the front laser shock peening of the blade leading edge is impacted, and after 10ns is delayed, the second laser beam 3 starts to carry out laser shock peening on the same position of the back of the blade leading edge; the parameters (such as wavelength, pulse width, spot diameter, laser energy and the like) of laser beams used for laser shock strengthening of the front surface and the back surface of the blade main guide edge are the same, the starting point and the shock path of the laser shock strengthening of the front surface and the back surface of the blade main guide edge are the same, and the transverse lapping rate and the longitudinal lapping rate are both 50%.
(4) And continuously carrying out laser shock strengthening on the main guide edge of the blade according to the double-sided asynchronous shock method until all shock areas on the front surface and the back surface of the main guide edge of the blade are shocked, and finishing the whole laser shock strengthening process.
Table 1 shows the comparison of residual stress under different experimental parameters, which are divided into single-sided laser shock peening, double-sided synchronous laser shock peening and double-sided asynchronous laser shock peening designed by the method, and all three parameters used for laser shock peening are as follows: the laser pulse energy is 7J, the laser pulse width is 10ns, and the repetition frequency is 1 Hz; the diameter d of the light spot is 3 mm; the delay time of the double-sided asynchronous laser shock peening is 8ns, residual stress tests are carried out after the laser shock peening, and the residual stress of 5 points of each sample is tested, namely the residual stress values of the surface and the positions L/4, L/2, 3L/4 and L from the surface.
As can be seen from the comparison of the residual stress in table 1, when the single-sided laser shock peening is performed, the residual compressive stress is at the surface, and the value of the residual compressive stress gradually decreases with the increase of the depth from the surface; when the double-sided laser shock peening is performed, the residual compressive stress at the surface and the depth L is the largest, the stress at the L/4 and the stress at the 3L/4 are approximately the same and are both smaller than the residual compressive stress value at the surface, and the residual tensile stress appears at the L/2, namely the residual tensile stress appears at the position where shock waves meet; when double-sided asynchronous laser shock peening is performed, the maximum residual compressive stress exists on the surface and at the depth L, and the residual compressive stress exists at the depth L/4, L/2 and 3L/4; compared with single-sided laser shock peening, the method generates larger residual compressive stress on the surface and the depth L, and compared with double-sided synchronous laser shock peening, the method does not generate residual tensile stress in the region where shock waves meet, so that the method can generate a better residual compressive stress field, and the residual compressive stress has a direct relation with the improvement of the fatigue life of the blade, so that the blade processed by the method can obtain better fatigue life.
TABLE 1
Status of state Surface of L/4 L/2 3L/4 L
Single side impact -703MPa -501MPa -201MPa -90MPa 12MPa
Simultaneous impact on both sides -712MPa -493MPa 73MPa -482MPa -707MPa
Double-sided asynchronous impact -709MPa -512MPa -287MPa -334MPa -720MPa

Claims (7)

1. A turbine blade leading edge double-sided asynchronous laser shock peening method is characterized in that: two laser beams with the same wavelength, pulse width, spot diameter and pulse energy are adopted to asynchronously carry out double-sided laser shock strengthening on the main guide edge of the turbine blade, namely one laser beam is used for carrying out laser shock strengthening along the front side of the main guide edge of the blade, another laser beam with the same parameters is adopted to carry out laser shock strengthening on the back side at the same position after a period of time t is delayed, and the starting point and the shock path of the laser shock strengthening on the front side and the back side of the main guide edge of the blade are the same; and for the time difference between the front laser beam and the back laser beam at the same position of the main guide edge, which is smaller than the time required by the front shock wave to propagate to the back of the blade, and the front laser beam is first, continuously carrying out laser shock strengthening on the blade according to the double-sided asynchronous shock method until the shock of all shock areas of the front and the back of the main guide edge of the blade is finished.
2. The turbine blade leading edge double-sided asynchronous laser shock peening method as recited in claim 1, comprising the steps of:
(1) determining the delay time t of the double-sided asynchronous laser shock peening of the main leading edge of the turbine blade according to the material and the thickness of the turbine blade;
(2) carrying out laser shock strengthening on the front surface of the main guide edge of the turbine blade by using laser beams;
(3) starting timing after the starting point of the front laser shock peening of the main leading edge of the blade is impacted, and delaying for t seconds, and then starting laser shock peening on the same position of the back of the main leading edge of the blade by a second laser beam;
(4) and continuously carrying out laser shock strengthening on the main guide edge of the blade according to the double-sided asynchronous shock method until all shock areas on the front surface and the back surface of the main guide edge of the blade are shocked, and finishing the whole laser shock strengthening process.
3. The turbine blade leading edge double-sided asynchronous laser shock peening method as recited in claim 2, wherein: in the step (1), the delay time t of the double-sided asynchronous laser shock peening of the main guide edge of the turbine blade is 0<t<t0So that the shock waves induced by the laser on the front and back surfaces are spaced from the front surface of the blade inside the bladeWhere L is the blade thickness, C0Is the wave velocity of the stress wave; t is t0The time for a stress wave generated in the material to propagate to the bottom of the material, t0＝L/C0，Wherein E is the elastic modulus, upsilon is the Poisson ratio, and rho is the density of the turbine blade material.
4. The turbine blade leading edge double-sided asynchronous laser shock peening method as recited in claim 2, wherein: in the step (2), the laser shock peening parameters are as follows: laser energy is 1-50J, laser pulse width is 10-40ns, and repetition frequency is 0.5-10 Hz; the diameter D of the light spot is 1-6 mm; the laser shock peening peak pressure P satisfies 2VHEL<P<2.5VHELDuring the process, the workpiece can obtain maximum plastic deformation, and the peak pressure of the shock wave can meet 2V for obtaining better laser shock strengthening effectHEL<P<2.5VHELAnd the pressure value P (R) of the light spot edge>VHELSo as to obtain maximum plastic deformation of the blade; vHELIs the Hugoniot Elastic Limit (HEL), V, of the blade materialHELSatisfies the formula:wherein upsilon is Poisson's ratio;is the yield strength of the blade material under dynamic loading.
5. The turbine blade leading edge double-sided asynchronous laser shock peening method of claim 4, wherein: the peak pressure of laser shock peening is obtained by
P ( G P a ) = 0.01 &alpha; 2 &alpha; + 3 Z ( g / cm 2 s - 1 ) I 0 ( G W / cm 2 )
Wherein α is distribution coefficient of internal energy, and is 0.1, I0In order to be the power density of the laser,e is laser energy (J), d is spot diameter (cm), τ is laser pulse width (ns), Z is reduced acoustic impedance, and Z is reduced acoustic impedancetargetIs the acoustic impedance of the target material, ZoverlayTo constrain the acoustic impedance of the layer
6. The turbine blade leading edge double-sided asynchronous laser shock peening method as recited in claim 1 or 2, wherein: the laser intensity follows Gaussian distribution, and the space-time distribution condition of the pressure pulse is represented by the following quasi-Gaussian formula: p (x, y, t) ═ Pexp [ - (x)2+y2)/2R2]In the formula, x and y are surface coordinates, and R is a spot radius.
7. The turbine blade leading edge double-sided asynchronous laser shock peening method as recited in claim 1 or 2, wherein: the transverse and longitudinal lap joint rates of laser shock strengthening of the front surface and the back surface of the main guide edge of the blade are both 50%.
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CN110205477A (en) * 2019-07-02 2019-09-06 哈尔滨工业大学 Using the laser shock peening method of timing bidifly light pulse improving laser induction shock strength
CN110369861A (en) * 2019-07-23 2019-10-25 广东工业大学 A method of preparing the pre-buried lamination defect of composite laminated plate
CN110704972A (en) * 2019-09-27 2020-01-17 华东理工大学 Blade surface bilateral ultrasonic rolling processing track coordination method
CN111310375A (en) * 2020-02-14 2020-06-19 广东工业大学 Machining method for optimizing shock wave pressure of laser double-sided simultaneous opposite impact titanium alloy blade
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CN110205477A (en) * 2019-07-02 2019-09-06 哈尔滨工业大学 Using the laser shock peening method of timing bidifly light pulse improving laser induction shock strength
CN110369861A (en) * 2019-07-23 2019-10-25 广东工业大学 A method of preparing the pre-buried lamination defect of composite laminated plate
CN110369861B (en) * 2019-07-23 2021-01-26 广东工业大学 Method for preparing composite laminated board pre-buried layering defect
CN110704972B (en) * 2019-09-27 2023-02-24 华东理工大学 Blade surface bilateral ultrasonic rolling processing track coordination method
CN110704972A (en) * 2019-09-27 2020-01-17 华东理工大学 Blade surface bilateral ultrasonic rolling processing track coordination method
CN111310375A (en) * 2020-02-14 2020-06-19 广东工业大学 Machining method for optimizing shock wave pressure of laser double-sided simultaneous opposite impact titanium alloy blade
CN111310375B (en) * 2020-02-14 2023-05-16 广东工业大学 Processing method for optimizing laser double-sided simultaneous opposite impact titanium alloy blade shock wave pressure
CN112760584A (en) * 2020-09-30 2021-05-07 中信戴卡股份有限公司 Laser shot peening strengthening method for aluminum alloy wheel
CN114318195A (en) * 2020-09-30 2022-04-12 中信戴卡股份有限公司 Laser shock service life prolonging method for aluminum alloy wheel without sacrificial layer
CN112593071A (en) * 2020-11-25 2021-04-02 中国科学院宁波材料技术与工程研究所 Energy-tunable single-sided and double-sided laser shock peening system
CN114277244B (en) * 2022-01-07 2023-01-06 北京航空航天大学 Deformation-controllable laser shock strengthening method and device for aero-engine blade
CN114277244A (en) * 2022-01-07 2022-04-05 北京航空航天大学 Deformation-controllable laser shock strengthening method and device for aero-engine blade
CN114406476A (en) * 2022-01-21 2022-04-29 南昌航空大学 Laser shock peening marking method

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