U.S. patent application number 17/280924 was filed with the patent office on 2021-10-07 for laser shock peening method for additive manufactured component of double-phase titanium alloy.
This patent application is currently assigned to JIANGSU UNIVERSITY. The applicant listed for this patent is JIANGSU UNIVERSITY. Invention is credited to Haifei LU, Jinzhong LU, Kaiyu LUO, Guang YANG, Xiancheng ZHANG.
Application Number | 20210308767 17/280924 |
Document ID | / |
Family ID | 1000005707936 |
Filed Date | 2021-10-07 |
United States Patent
Application |
20210308767 |
Kind Code |
A1 |
LU; Jinzhong ; et
al. |
October 7, 2021 |
LASER SHOCK PEENING METHOD FOR ADDITIVE MANUFACTURED COMPONENT OF
DOUBLE-PHASE TITANIUM ALLOY
Abstract
A laser shock peening method for an additive manufactured
component of a double-phase titanium alloy is provided. First, a
three-dimensional digital model of a complex component is obtained,
and the model is divided into a plurality of slices; a forming
direction of a formed part in an additive manufacturing process is
determined according to a stress direction of the additive
manufactured component in an engineering application; then, the
component of the double-phase titanium alloy is formed and
manufactured by selective laser melting, and orientations of a
C-axis of an .alpha. phase is allowed to be consistent through
adjustment and control; and finally, laser shock peening is
performed on all outer surfaces of the high-performance additive
manufactured component of the double-phase titanium alloy by
inducing a high-intensity shock wave to act in an acting direction
which forms an angle in a predetermined range with the C-axis of
the as phase.
Inventors: |
LU; Jinzhong; (Zhenjiang,
CN) ; LU; Haifei; (Zhenjiang, CN) ; ZHANG;
Xiancheng; (Zhenjiang, CN) ; LUO; Kaiyu;
(Zhenjiang, CN) ; YANG; Guang; (Zhenjiang,
CN) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
JIANGSU UNIVERSITY |
Zhenjiang |
|
CN |
|
|
Assignee: |
JIANGSU UNIVERSITY
Zhenjiang
CN
|
Family ID: |
1000005707936 |
Appl. No.: |
17/280924 |
Filed: |
September 18, 2020 |
PCT Filed: |
September 18, 2020 |
PCT NO: |
PCT/CN2020/116028 |
371 Date: |
March 29, 2021 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B33Y 40/20 20200101;
B33Y 50/00 20141201; B22F 2301/205 20130101; B22F 10/64 20210101;
B22F 10/28 20210101; B22F 10/50 20210101; C21D 10/005 20130101 |
International
Class: |
B22F 10/64 20060101
B22F010/64; B33Y 40/20 20060101 B33Y040/20; C21D 10/00 20060101
C21D010/00; B33Y 50/00 20060101 B33Y050/00; B22F 10/28 20060101
B22F010/28; B22F 10/50 20060101 B22F010/50 |
Foreign Application Data
Date |
Code |
Application Number |
Sep 27, 2019 |
CN |
201910923611.6 |
Claims
1. A laser shock peening method for an additive manufactured
component of a double-phase titanium alloy, wherein, first, a
three-dimensional digital model of a complex component is obtained,
and the model is divided into a plurality of slices; a forming
direction of a formed part in an additive manufacturing process is
determined according to a stress direction of the additive
manufactured component in an engineering application; then, a
component of the double-phase titanium alloy is formed and
manufactured by selective laser melting, and orientations of a
C-axis of an .alpha. phase are allowed to be consistent through
adjustment and control; and finally, a laser shock peening is
performed on a high-performance additive manufactured component of
the double-phase titanium alloy by inducing a high-intensity shock
wave to act in an acting direction which forms an angle in a
predetermined range with the C-axis of the .alpha. phase, so as to
achieve an optimal strengthening effect, wherein the method
comprises the following specific steps: (1) obtaining the
three-dimensional digital model of the complex component through a
computer software, and dividing the model into the plurality of
slices; (2) determining the forming direction in the additive
manufacturing process according to the stress direction of the
additive manufactured component in the engineering application, and
then making an additive forming surface parallel to the stress
direction; (3) then, forming and manufacturing the component of the
double-phase titanium alloy by selective laser melting, and
allowing the orientations of the C-axis of the .alpha. phase to be
consistent through continuously applying a strong magnetic field
generated by a spiral superconducting coil to a metal melt; (4)
finally, performing the laser shock peening with a normal of the
C-axis as a symmetry axis by forming an incident angle, namely, an
angle .alpha., between an acting direction of a laser shock wave
and the C-axis of the .alpha. phase on each of left and right
sides; and (5) performing the laser shock peening on all outer
surfaces of the high-performance additive manufactured component of
the double-phase titanium alloy, so as to achieve the optimal
strengthening effect.
2. The laser shock peening method for the additive manufactured
component of the double-phase titanium alloy according to claim 1,
wherein in step (3), an intensity of the strong magnetic field is
.gtoreq.6 T, and parameters of the selective laser melting
comprise: a spot diameter of 80 .mu.m, a laser wavelength of 1.06
to 1.10 .mu.m, a laser power of 200 to 1000 W, a scanning speed of
500 to 1000 mm/s, and a powder layer thickness of 0.02 to 0.5
mm.
3. The laser shock peening method for the additive manufactured
component of the double-phase titanium alloy according to claim 1,
wherein in step (4), 0.degree.<.alpha..ltoreq.30.degree..
4. The laser shock peening method for the additive manufactured
component of the double-phase titanium alloy according to claim 1,
wherein in step (5), ranges of process parameters of the laser
shock peening comprise: a laser pulse energy of 3 to 12 J, a pulse
width of 5 to 20 ns, a spot diameter of 1 to 3 mm, and an overlap
ratio in transverse and longitudinal directions each being 30% to
50%.
5. The laser shock peening method for the additive manufactured
component of the double-phase titanium alloy according to claim 1,
wherein a material of the high-performance component of the
double-phase titanium alloy comprises a near-.alpha. titanium alloy
such as TC1, TC4, and TC6.
Description
CROSS REFERENCE TO THE RELATED APPLICATIONS
[0001] This application is the national phase entry of
International Application No. PCT/CN2020/116028, filed on Sep. 18,
2020, Which is based upon and claims priority to Chinese Patent
Application No. 201910923611.6, filed on Sep. 27, 2019, the entire
contents of which are incorporated herein by reference.
TECHNICAL FIELD
[0002] The present invention relates to the fields of additive
manufacturing and laser shock peening, and in particular, to a
laser shock peening method for an additive manufactured component
of a double-phase titanium alloy.
BACKGROUND
[0003] Selective laser melting (SLM) technology is a latest rapid
forming technology emerging in recent years, which uses layered
manufacturing for additive manufacturing, and converts CAD models
into physical parts through powders. This technology uses a laser
to rapidly melt a metal powder in a selected area, and rapid
cooling and solidification, so that a nonequilibrium-state
supersaturated solid solution, and a uniform and fine
metallographic structure can be obtained, and a wide range of
forming materials can be used. Also, the manufacturing process is
not limited by the complex structure of metal parts, and does not
require any tooling, and has a simple process, to realize rapid
manufacturing of the metal parts and the cost reduction.
Additionally, the manufacturing of functionally gradient materials
with a continuously varying material composition can also be
realized. Although great progress has been made in laser additive
manufacturing in recent years, some difficulties remain in the
coordinated control of structure and performance, among which the
"structure control" problem that the residual stress causes
deformation and cracking of components and the "performance
control" problem that metallurgical defects cause poor mechanical
properties of components need to be solved. In addition, the
selective laser melting technology has been widely applied in
aerospace and other fields. However, components used in aerospace
engineering work under harsh conditions, and the components are
subjected to not only static load, dynamic load, and impact load
but also thermal effect of high temperature in all directions.
Thus, the properties of the material and whether the material has a
significant anisotropy are issues of great concern.
[0004] Laser shock peening (LSP) is a novel surface strengthening
technology, which uses an intense laser to act on a metal surface
to form ultra-strong shock waves which cause a severe plastic
deformation on the metal surface and induce a deep compressive
residual stress and refined grains, thereby significantly improving
mechanical properties of metal parts. Compared with the other
technologies, laser shock peening has four distinctive features of
high pressure (the shock wave pressure reaches a magnitude of (GPa
to TPa), high energy (the peak power reaches a magnitude of GW),
ultra-high speed (tens of nanoseconds), and ultra-high strain rate
(as high as 10.sup.7 s.sup.-1), and becomes one of the advanced
manufacturing methods tinder extreme conditions, and has
incomparable advantages over conventional processing methods, and
significant technical advantages. However, at present, a large
number of researches only focus on the condition of the sample
surface subjected to laser shock peening, and the problems of how
to induce deeper compressive residual stress, how to better realize
grain refinement, and so on.
[0005] The double-phase titanium alloy has desirable comprehensive
properties, high structural stability, and good toughness,
plasticity, and high-temperature deformation properties. Thus, the
alloy can be desirably subjected to thermal pressure processing,
and can be subjected to quenching and aging to strengthen the
alloy. In addition, .alpha. and .beta. phases in the double-phase
titanium alloy have very important effects on physical and
mechanical properties of the material. The crystallography is
closely related to various properties of the material, and based on
the three-dimensional periodicity of a crystal structure in spatial
arrangement, each type of crystal can provide itself with a natural
and rational crystal axis system having three crystal axes. The
crystal has anisotropy, that is, the crystal has different physical
properties in different crystal orientations. In a similar way,
combined with the laser shock peening technology of the
two-dimensional additive manufacturing plane, high-performance
additive manufactured component with uniform strengthening of
microstructures can be achieved.
SUMMARY
[0006] In order to solve the aforementioned problems, the present
invention provides a laser shock peening method for an additive
manufactured component of a double-phase titanium alloy. That is,
for a high-performance additive manufactured component of a
double-phase titanium alloy in aerospace, first, a
three-dimensional digital model of a complex component is obtained,
and the model is divided into a plurality of slices; a forming
direction of a formed part in an additive manufacturing process is
determined according to a stress direction of the additive
manufactured component in an engineering application; then, the
component of the double-phase titanium alloy is formed and
manufactured by selective laser melting, and orientations of a
C-axis of an .alpha. phase are allowed to be consistent through
adjustment and control; and finally, laser shock peening is
performed on the high-performance additive manufactured component
of the double-phase titanium alloy by inducing a high-intensity
shock wave to act in an acting direction which forms an angle in a
predetermined range with the C-axis of the .alpha. phase, so as to
achieve an optimal strengthening effect. The present invention is a
continuation and expansion of a laser additive manufacturing
method. For a key component of the double-phase titanium alloy in
aerospace, the anisotropy of a crystal structure is considered, and
based on the mechanism of the laser shock peening, the stress state
of a high-performance additive manufactured component and the
interaction mechanism between a laser shock wave and the C-axis of
the .alpha. phase of the double-phase titanium alloy are considered
as a whole to perform microstructure strengthening of the additive
manufactured component, realizing the high-performance
manufacturing without deformation of the key component in
aerospace.
[0007] The specific steps are as follows:
[0008] 1) obtaining a three-dimensional digital model of a complex
component through a computer software, and dividing the model into
a plurality of slices;
[0009] 2) determining a forming direction in an additive
manufacturing process according to a stress direction of an
additive manufactured component in an engineering application, and
then making an additive forming surface parallel to the stress
direction;
[0010] 3) then, forming and manufacturing the component of the
double-phase titanium alloy by selective laser melting, and
allowing orientations of the C-axis of the .alpha. phase to be
consistent through continuously applying a strong magnetic field
generated by a spiral superconducting coil to a metal melt, wherein
an intensity of the strong magnetic field is .gtoreq.6 T, wherein
parameters of the selective laser melting include: a spot diameter
of 80 .mu.m, a laser wavelength of 1.06 to 1.10 .mu.m, a laser
power of 200 to 1000 W, a scanning speed of 500 to 1000 mm/s, and a
powder layer thickness of 0.02 to 0.5 mm;
[0011] 4) finally, performing laser shock peening with a normal of
the C-axis as a symmetry axis by forming an incident angle, namely,
an angle .alpha., between an acting direction of a laser shock wave
and the C-axis of the .alpha. phase on each of left and right
sides, wherein 0.degree..ltoreq..alpha..ltoreq.30.degree.; and
[0012] 5) performing laser shock peening on all outer surfaces of
the high-performance additive manufactured component of the
double-phase titanium alloy, so as to achieve an optimal
strengthening effect, wherein ranges of process parameters of the
laser shock peening include: a laser pulse energy of 3 to 12 J, a
pulse width of 5 to 20 ns, a spot diameter of 1 to 3 mm, and an
overlap ratio in transverse and longitudinal directions each being
30% to 50%.
[0013] A material of the high-performance component of the
double-phase titanium alloy includes: a near-.alpha. titanium alloy
such as TC1, TC4, or TC6.
[0014] The present invention has the following beneficial
effects:
[0015] 1) The "structure control" problem that the internal stress
causes deformation and cracking of the formed part and the
"preformance control" problem that metallurgical defects cause poor
fatigue properties in the additive manufacturing are effectively
solved, thereby improving the fatigue strength and mechanical
properties of the formed part.
[0016] 2) Based on microstructure strengthening, movement of basal
plane dislocations can be pinned more effectively through the
effect of laser shock peening, so that the high-performance
additive manufactured component of the double-phase titanium alloy
is provided with desirable mechanical properties.
[0017] 3) For the key component of the double-phase titanium alloy
in aerospace, the anisotropy of the crystal structure is
considered, and based on the mechanism of the laser shock peening,
the stress state of the high-performance additive manufactured
component, and the interaction mechanism at the angle in a
predetermined range between the acting direction of laser shock
wave and the C-axis of the .alpha. phase are considered as a whole
to perform shock peening on the additive manufactured component of
the double-phase titanium alloy, realizing the high-performance
manufacturing without deformation of the key component in
aerospace.
BRIEF DESCRIPTION OF THE DRAWINGS
[0018] In order to illustrate the technical solutions in the
embodiments of the present application or in the prior art more
clearly, the accompanying drawings to be used in the description of
the examples or the prior art will be introduced briefly below.
[0019] FIG. 1 is a schematic view of a C-axis of an .alpha. phase
of a double-phase titanium alloy.
[0020] FIG. 2 is a schematic view illustrating that the additive
forming surface is parallel to the stress direction in the additive
manufacturing process of the present invention.
[0021] FIG. 3 is a schematic view illustrating that the C-axis of
the .alpha. phase is subjected to laser shock peening in the
present invention.
[0022] FIG. 4 is a schematic view of the turbine blade in the
embodiments of the present invention.
[0023] Table 1 is a comparison of fatigue life of the turbine
blades at different states in the embodiments of the present
invention.
DETAILED DESCRIPTION OF THE EMBODIMENTS
[0024] The specific implementations of the present invention are
illustrated in detail below with reference to the accompanying
drawings and embodiments, but the present invention should not be
limited to the embodiments.
[0025] A turbine blade of double-phase TC4 titanium alloy is used
in these embodiments.
Embodiment 1
[0026] 1) Three-dimensional point cloud data on the turbine blade
surface is obtained through a three-dimensional laser scanner, and
then, a three-dimensional digital model of the turbine blade is
obtained through the computer software, and the model is divided
into a plurality of slices;
[0027] 2) simulation analysis is performed through a simulation
software to obtain the stress direction distribution of TC4 turbine
blade in the actual application, and the additive direction in the
additive manufacturing process is determined, so that the additive
forming surface is parallel to the stress direction;
[0028] 3) then, the turbine blade is formed and manufactured by
selective laser melting, where parameters of selective laser
melting include: a spot diameter of 80 .mu.m, a laser wavelength of
1.08 .mu.m, a laser power of 300 W, a scanning speed of 700 mm/s,
and a powder layer thickness of 0.3 mm. A vibration fatigue test is
performed on the formed turbine blade.
Embodiment 2
[0029] 1) Three-dimensional point cloud data on the turbine blade
surface is obtained through a three-dimensional laser scanner, and
then, a three-dimensional digital model of the turbine blade is
obtained through the computer software, and the model is divided
into a plurality of slices;
[0030] 2) simulation analysis is performed through a simulation
software to obtain the stress direction of TC4 turbine blade in the
actual application, and the additive direction in the additive
manufacturing process is determined, so that the additive forming
surface is parallel to the stress direction;
[0031] 3) then, the turbine blade is formed and manufactured by
selective laser melting, where parameters of selective laser
melting include: a spot diameter of 80 .mu.m, a laser wavelength of
1.08 .mu.m, a laser power of 300 W, a scanning speed of 700 mm/s,
and a powder layer thickness of 0.3 mm;
[0032] 4) finally, laser shock peening is directly performed on the
surface of the turbine blade, where ranges of process parameters of
laser shock peening include: a laser pulse energy of 10 J, a pulse
width of 10 ns, a spot diameter of 3 mm, and an overlap ratio in
the transverse and longitudinal directions each being 50%. A
vibration fatigue test is performed on the strengthened turbine
blade.
Embodiment 3
[0033] 1) Three-dimensional point cloud data on the turbine blade
surface is obtained through a three-dimensional laser scanner, and
then, a three-dimensional digital model of the turbine blade is
obtained through the computer software, and the model is divided
into a plurality of slices;
[0034] 2) simulation analysis is performed through a simulation
software to obtain the stress direction of TC4 turbine blade in the
actual application, and the additive direction in the additive
manufacturing process is determined, so that the additive forming
surface is parallel to the stress direction;
[0035] 3) then, the turbine blade is formed and manufactured by
selective laser melting, and the orientations of a C-axis of an
.alpha. phase is allowed to be consistent through continuously
applying a strong magnetic field of 9 T generated by a spiral
superconducting coil to a metal melt, where parameters of selective
laser melting include: a spot diameter of 80 .mu.m, a laser
wavelength of 1.08 .mu.m, a laser power of 300 W, a scanning speed
of 700 mm/s, and a powder layer thickness of 0.3 mm;
[0036] 4) as shown in FIG. 3, finally, laser shock peening is
performed with the normal of the C-axis as a symmetry axis by
forming an angle .alpha. of 30.degree.<.alpha..ltoreq.60.degree.
or 60.degree.<.alpha..ltoreq.90.degree. between the laser shock
wave and the C-axis of the .alpha. phase on each of left and right
sides, where ranges of process parameters of laser shock peening
include: a laser pulse energy of 10 J, a pulse width of 10 ns, a
spot diameter of 3 mm, and an overlap ratio in the transverse and
longitudinal directions each being 50%. A vibration fatigue test is
performed on the strengthened turbine blade.
Embodiment 4
[0037] The technical solution of the present invention: referring
to FIG. 1, FIG. 2, FIG. 3, and FIG. 4, this embodiment relates to a
laser shock peening method for additive manufactured component of
the double-phase titanium alloy, which includes the following
steps:
[0038] 1) obtaining three-dimensional point cloud data on the
turbine blade surface through a three-dimensional laser scanner,
and then, obtaining a three-dimensional digital model of the
turbine blade through the computer software, and dividing the model
into a plurality of slices;
[0039] 2) performing simulation analysis through a simulation
software to obtain the stress direction of TC4 turbine blade in the
actual application, and determining the additive direction in the
additive manufacturing process, so that the additive forming
surface is parallel to the stress direction;
[0040] 3) then, forming and manufacturing the turbine blade by
selective laser melting, and allowing the orientations of the
C-axis of the .alpha. phase to be consistent through continuously
applying a strong magnetic field of 9 T generated by a spiral
superconducting coil to a metal melt, where parameters of selective
laser melting include: a spot diameter of 80 .mu.m, a laser
wavelength of 1.08 .mu.m, a laser power of 300 W, a scanning speed
of 700 mm/s, and a powder layer thickness of 0.3 mm;
[0041] 4) as shown in FIG. 3, finally, performing laser shock
peening with the normal of the C-axis as a symmetry axis by forming
an angle .alpha. of 0.degree.<.alpha..ltoreq.30.degree. between
the laser shock wave and the C-axis of the .alpha. phase on each of
left and right sides, where ranges of process parameters of laser
shock peening include: a laser pulse energy of 10 J, a pulse width
of 10 ns, a spot diameter of 3 mm, and an overlap ratio in the
transverse and longitudinal directions each being 50%. A vibration
fatigue test is performed on the strengthened turbine blade.
[0042] It can be seen from Table 1 that in vibration fatigue life
tests at four different states of Embodiment 1 (1-1, 1-2),
Embodiment 2 (2-1, 2-2), Embodiment 3 (3-1
(30.degree.<.alpha..ltoreq.60.degree.), 3-2
(30.degree.<.alpha..ltoreq.60.degree.), 3-3
(60.degree.<.alpha..ltoreq.90.degree.), 3-4
(60.degree.<.alpha..ltoreq.90.degree.), and Embodiment 4 (4-1,
4-2), under different stress conditions of 430 MPa and 560 MPa, the
results show that the turbine blade processed using the technical
solution of the present invention has significantly improved
fatigue life, thereby achieving the optimal strengthening
effect.
[0043] The above disclosure is merely a preferred embodiment of the
present invention, and certainly cannot be used to limit the scope
of the present invention. Therefore, equivalent changes made
according to the claims of the present invention shall still belong
to the scope of the present invention.
TABLE-US-00001 TABLE 1 State Stress/MPa Fatigue life 1-1
(Embodiment 1) 430 2.49 .times. 10.sup.7 1-2 (Embodiment 1) 560
1.23 .times. 10.sup.7 2-1 (Embodiment 2) 430 3 .times. 10.sup.7 2-2
(Embodiment 2) 560 2.49 .times. 10.sup.7 3-1 (30.degree. <
.alpha. .ltoreq. 60.degree.) (Embodiment 3) 430 3.26 .times.
10.sup.7 3-2 (30.degree. < .alpha. .ltoreq. 60.degree.)
(Embodiment 3) 560 2.86 .times. 10.sup.7 3-3 (60.degree. <
.alpha. .ltoreq. 90.degree.) (Embodiment 3) 430 3.41 .times.
10.sup.7 3-4 (60.degree. < .alpha. .ltoreq. 90.degree.)
(Embodiment 3) 560 2.95 .times. 10.sup.7 4-1 (Embodiment 4) 430
3.71 .times. 10.sup.7 4-2 (Embodiment 4) 560 3.38 .times.
10.sup.7
* * * * *