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2016 Vol. 59, No. 20
Published: 2016-10-15
FEATURE
FIGURE
FORUM
NEW VIEWPOINT
RESEARCH
C0NTENTS
COVER STORY
C0NTENTS
6
C0NTENTS
2016 Vol. 59 (20): 6-10 [
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FEATURE
16
Recent Situation and Development Trend of Shot Peening on Surface Integrity
GAI Pengtao1,2,3, CHEN Fulong1,2,3, SHANG Jianqin1,2,3, HAN Xiuquan1,2,3
DOI: 10.16080/j.issn1671-833x.2016.20.016
Shot peening is a kind of efficient, economical and effective surface peening technology and can improve
mechanical performance of material remarkably through controlling surface integrity of peened material. The influence of
shot peening on surface integrity are summarized, such as residual stress, microstructure, roughness and hardness and the
relationship is introduced between different kinds of shot peening technologies and surface integrity in this paper. The future
development prospects of shot peening research based on surface integrity control are summed up.
2016 Vol. 59 (20): 16-21 [
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300
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FIGURE
22
Dig a Well, the Spiritualist’s Guide to Research
2016 Vol. 59 (20): 22-23 [
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191
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COVER STORY
24
Study and Application of Digital Measurement Technology for Aircraft Assembly Precision
ZHAO Jianguo, GUO Hongjie
DOI: 10.16080/j.issn1671-833x.2016.20.024
To improve digital measurement technology for aircraft assembly, key digital measure factor design,
measure plan design, building measure system with multiform devices, measurement error analysis and compensation are
studied. Then measurement devices and system building are illustrated, assembly precision inspection used for surface and
inside framework factor, huge and kinetic components measuring are proved.
2016 Vol. 59 (20): 24-27 [
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239
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FIGURE
30
Development of Advanced Heat Treatment Technology for Aero-Engine Components
SUN Feng, HE Ruijun, JIANG Zhihua, WANG Lin, TONG Xiaojun, HAN Jin, ZHOU Ge
DOI: 10.16080/j.issn1671-833x.2016.20.030
Heat treatment, as the basis and generic technology in the research of advanced aero-engine, is a critical
factor in the serviceability of the aero-engine components. Based on the researches and practices of heat treatment in the
field in recent years, this paper first gives a general review of the status of advanced heat treatment, and then puts emphasis
on the analysis and discussion of the appliance of vacuum heat-treatment, chemical heat-treatment and special heattreatment
on the manufacturing of key components on blade, disk, gear, bearing and rotor. At the end of the paper, it looks
forward into the future research and development of heat treatment in the field of aero-engine in our country.
2016 Vol. 59 (20): 30-35 [
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311
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FORUM
36
Quenching Process Simulation and Deformation Prediction of ZL205A Aluminum Alloy Large Complicated Cylinder Workpiece
LU Chen1, ZHANG Chengsong2, FU Hongya1, YAN Mufu3
DOI: 10.16080/j.issn1671-833x.2016.20.036
The temperature field and stress field of quenching processes of ZL205A aluminum alloy large complicated
workpiece are simulated by finite element method based on ABAQUS software. The temperature field distribution of the
workpiece at different times is analyzed. Four key points based on the structure characteristic of the workpiece are chosen
for the cooling curves. The cooling curves of the thick-wall, strengthening rib and thin-wall of workpiece are investigated.
The maximum deformation and residual stress after quenching are predicted by finite element simulation. The maximum of
quenching deformation at radial direction of ZL205A aluminum alloy large complicated workpiece. The six components of
quenching residual stress are compared, the normal stress is greater than the shear stress. The quenching processes of thickwall
workpiece with different heat transfer coefficients are investigated. The cooling rate of thick-wall workpiece increase
with the increase of the heat transfer coefficient, but the amplitude isn’t obvious.
2016 Vol. 59 (20): 36-40 [
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211
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41
Research on Engineering Application for Vapor Aluminizing Process of Hollow Blade
LI Ke, ZHANG Li, Ding Zhimin
DOI: 10.16080/j.issn1671-833x.2016.20.041
Vapor aluminizing process and microstructure of hollow blade in aero-engine has been researched. The
mechanism of the coating has been analyzed. The results show that the depth of the surface coating is 20~60μm, by 30% Al
aluminizing powder. And the internal coating of turbine blade is 5~20μm. The depth increases with the extension of the aluminized
time. The coating mainly comprises two layers with the same depth. The surface layer is 32%~36% Al, with β-NiAl
phase. And the inner layer is 11%~17% Al, with β-NiAl phase, or β+γ' phase, or γ’ phase. There are needles which are arranged
disorderly and a small amount of foreign substance in the inner layer. The main reason of high-Al in the coating is
the rust of crucible. The crucible has been forced aluminized with high temperature and long time. The blade coating has
good microstructure and mechanical properties after been vapor aluminized at 980℃ for 4h, through the assessment of the
aero-engine 1000h lasting. The prospect of engineering application for vapor aluminizing process of hollow blade is very
good.
2016 Vol. 59 (20): 41-44 [
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274
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45
Effects of Aging Treatments on the Microstructure and Mechanical Properties of GH4169 Alloy
NIU Jing1, ZHANG Fanyun1, YANG Shulin2, WANG Man1, ZHAO Zhi1, LIU Jing1
DOI: 10.16080/j.issn1671-833x.2016.20.045
The microstructure and mechanical properties of GH4169 alloy are tested and analyzed following respective
aging treatments of GH907 and GH4169, to gain an insight into the effect of GH907 alloy aging treatment on GH4169
alloy. The results show that δ phases of GH4169 alloy during aging treatment at 775℃ increased in quantity, the γ' and γ''
phases grow slightly, but the crystal grain size do not change evidently as compared to those of GH4169 subjected to aging
treatment at 720℃ . The notched stress rupture life of the GH4169 alloy do not change significantly and is not notch sensitive
following aging treatment at 775℃ , however, the yield strength and ultimate strength at room-temperature and 650℃ ,
stress rupture life and hardness moderately diminished.
2016 Vol. 59 (20): 45-48 [
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NEW VIEWPOINT
50
Investigation to Civil Aircraft’s Fuselage Segmenting
WU Xiaoguang, ZHOU Bin, WANG Jianli
DOI: 10.16080/j.issn1671-833x.2016.20.050
The civil aircraft’s fuselage segmenting is the key principal in the conceptual design stage. There are
many problems due to the unpredicted economical reason will be met during the operation. After the real practice on the
Chinese civil aircraft, we want to provide a solution the fuselage segmenting based on the country industry policy and the
enter-prise’s industrial work division rule. the expected selling and the annual production are used to decide the fuselage
segmenting’s number, and the difficulty of the fabricating and assembling are used to judge the segmenting surfaces. This
method has be evaluated and accepted by the foreign aircrafts’ segmenting also.
2016 Vol. 59 (20): 50-56 [
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244
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RESEARCH
58
Experiment Study of an Aero-Engine Fuel Nozzle Spray Angle Commissioning
QIU Wei1, XIA Limin1, SUN Hui2, ZHAO Fanghui2, DENG Yuanhao1, XU Huasheng1
DOI: 10.16080/j.issn1671-833x.2016.20.058
In the first trial-manufacture of an aero-engine centrifugal fuel nozzle, the spray angle is smaller than design
requirements, through theoretical analysis, formulate measures for a variety of commissioning process, and has carried
out experimental study. Tests show that measures for reducing swirl angle, reducing spout length, increasing spout diameter,
reducing swirl chamber length and reducing swirl tank depth can increase the spray angle to a certain extent. Eventually,
we adopted double angle rubbing process, combined with the measures for decreasing the swirl tank depth, has reached the
design requirements of the spray angle.
2016 Vol. 59 (20): 58-62 [
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282
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63
Research on the Springback of Composites C-Shape Ribs
HAN Xiaoyong, SU Jiazhi, XU Shaochen, CHEN Jiping, ZHENG Yizhu
DOI: 10.16080/j.issn1671-833x.2016.20.063
Composites C-shape ribs are made of carbon fiber fabric prepreg on the male moulds under certain curing
process. A coordinate measuring machine is used to measure the surface of the moulds, the inner surface of the ribs under
three conditions (three flanges closed, large end cut and three flanges trimmed after large end cut), and the outer surface of
the ribs when the large end is cut and the three flanges are trimmed. The springback of the ribs are measured and analyzed.
The results shows that the springback compensation of the two side flanges of the ribs is 1.35°, and the springback compensation
of the large end flange is 0.32° when the three flanges are closed. The springback results varied a lot before and after
the large end is cut, but varied little before and after the flanges are trimmed. The springback compensation is 1.69° for the
two side flanges, and 1.62° for the big end flange when the ribs are cut at the large end.
2016 Vol. 59 (20): 63-67 [
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247
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RESEARCH
68
Composites Aircraft Lightning Strike Protection Design
CHEN Wen, LIU Rui
DOI: 10.16080/j.issn1671-833x.2016.20.068
Aircraft lightning strike protection is a comprehensive technology involving many technical subjects. Specifically,
lightning strike protection must be considered in aircraft structure, flight control, fuel and avionic system design.
All composites aircrafts becomes more popular nowadays with the development of composites technology. However, lightning
strike protection for composites is evidently different from that for metal, because of material difference. This article
summarizes international developing trend, and provides some methods for composites aircraft lightning strike protection
design and airworthiness.
2016 Vol. 59 (20): 68-72 [
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291
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73
Application of PCD Cutting Tool in Aviation Hydraulic Housing Machining
SHI Xiaofei, LI Zhichao, LU Yongxiang
DOI: 10.16080/j.issn1671-833x.2016.20.073
In the processing of aviation hydraulic housing parts, the aperture size is often unstable and the roughness
cannot be guaranteed. By analyzing the actual processing technology and method, the reason of size variation is found and
PCD cutting tool is selected as finishing tools to replace hard alloy cutting tool. Taking hole processing as an example, the test
process and actual application of PCD reamer and PCD boring cutting tool in aviation hydraulic housing processing is introduced.
The results indicate that the PCD cutting tods are outstanding in the finish machining of aluminium alloy compared
with traditional cutting tool and can solve the problem of low machining efficiency and uncontrollable processing quality.
2016 Vol. 59 (20): 73-76 [
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198
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CFD Development and Application in Aviation
LUO Lei, GAO Zhenxun, JIANG Chongwen
DOI: 10.16080/j.issn1671-833x.2016.20.077
The recent developments of Computational Fluid Dynamics (CFD) as well as the applications that CFD
methods implement in aeronautics are both summarized. The summary of CFD developments is mainly focused on three
aspects: schemes, grid methods, and turbulence simulation methods. A perspective on CFD is subsequently presented. The
summary of CFD applications in aeronautics is detailed within the aspects as aircraft shape optimization, rotor/helicopter,
unsteady flow around crafts, moving-body separation and craft inlet.
2016 Vol. 59 (20): 77-81 [
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327
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Bending Experimental Study on the C-Shape Frame by Autoclave and RTM Forming
YE Jun, GONG Zhanfeng
DOI: 10.16080/j.issn1671-833x.2016.20.082
Bend experiments of two kind of the C-shape frame, processed respectively by using RTM and autoclave
forming have been carried out to investigate the influences of bearing capability and destroy mode. The results show that
the bearing capability of the frame by autoclave forming is 27.5 percent higher than the frame by RTM, and the dispersivity
of the bearing capability by autoclave forming is less than that by RTM. The position of destroy is the same, but the
delamination of the outside on transition section from line section to bend section by using RTM occurs firstly, whereas the
delamination by autoclave forming occurs until the outside destroyed. The conclusion is valuable for the engineering application
of the circumferential frame.
2016 Vol. 59 (20): 82-84 [
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Application of Spherical Localization in Turbine Vane’s Manufacturing
NIE Dongbing1, Zhang Tao1, DUAN Pengguo2
DOI: 10.16080/j.issn1671-833x.2016.20.085
In order to solve problems such as complex localization transform, deviation accumulation, inefficiency
drilling in turbine vane manufacture, spherical localization methods are applied in blade design. The contradiction of hole
and fixture, the low drilling efficiency is solved. According to a batch of vane manufacture, it is proved that the spherical
localization can be successfully applied in the blade production.
2016 Vol. 59 (20): 85-87 [
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Research on Microstructure of Ordered Porous Alumina Ceramic
CHEN Jingzhe, TONG Jianfeng, YI Xiaosu
DOI: 10.16080/j.issn1671-833x.2016.20.088
The microstructure, pore structure and grain growth of porous alumina ceramics by template method are
studied by SEM. It is found that the pore structure of porous alumina ceramics by template method is uniform, interconnected
and controllable. With the increase of the solid volume fraction, the porosity of porous ceramic decreases. The wall
of hole doesn’t appeared abnormal grain growth, and the relative density of porous ceramic is much higher compare with
foaming method.
2016 Vol. 59 (20): 88-91 [
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Application of Helium Leak Detection in a Certain Type of Wing Assembly
ZHOU Da， ZHANG Jinhai， ZHU Zhikun
DOI: 10.16080/j.issn1671-833x.2016.20.092
By researching engineering application of helium leakage detection technology on a certain type wing
integral fuel tank leak detection to locate the leaking resource accurately and in advance, to remove the trouble preciously,
to avoid the hysteresis of problem finding caused by the delay of traditional airtight and oil tightness test procedure, and to
reduce rework and time cost, which has obvious benefits. The research result can be generated and applied in other sealing
components assembly test, and it is a beneficial exploration on application of digital detection technology in aircraft sealing
assembly as well.
2016 Vol. 59 (20): 92-96 [
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Study on Virtual Monitoring System for Digital Workshop
JIANG Kang1, KE Rong1, ZHAO Xiaoyong1, HE Qichang2
DOI: 10.16080/j.issn1671-833x.2016.20.097
In order to solve the shortage of information exchange between managements and executions in the current
workshop with traditional monitoring system, this paper developed a workshop state monitoring system based on virtual
reality technology and information integration technology, which can monitor the personnel, materials, equipment, et
al at whole workplace in real-time. It built up a logical data model based on 3D model, a data interface between subsystems
with XML specification, and model motion driven by real-time state data. Finally, the effectiveness of the system was verified
by an application example.
2016 Vol. 59 (20): 97-100 [
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269
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Information Expression for Aerospace Fasteners Based on Full 3D Design
GUO Jianye, XIN Yujuan, QU Ligang, YANG Yeguang
DOI: 10.16080/j.issn1671-833x.2016.20.101
During full 3D design process, MBD model has become a accurate and real-time single data source,
which integrate into all kinds of information about design, inspection, manufacture and assembly. MBD model realizes
digital manufacturing and assembly, without two dimensional drawings. Fasteners have various types and the number of
fasteners is more than half of the total number of parts. Based on the characteristics of low design & assembly efficiency
and low accuracy of fasteners, this article introduces a new expression for fasteners, analyses the organization of the relative
information about the fasteners to establish standardized design & assembly expression. To consider all factors, such
as the position of the components, the load demand and the degree of deformation, designners decide the specifications of
fastenerand use 3D point-line to express the fasteners under the relative assembly file, which makes design & assembly expression
for fasteners standardized.
2016 Vol. 59 (20): 101-104 [
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268
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Research Progress of Predictive Models for Surface Integrity
LI Wenhui1,2, GAO Jianhong1,2, GAO Wei1,2, YANG Shengqiang1,2, LI Xiuhong1,2, WU Fengfeng1,2
DOI: 10.16080/j.issn1671-833x.2016.20.105
The types and applications of predictive models for surface integrity are reviewed comprehensively. Analysis
model and numerical model used to predict surface integrity parameters on workpiece surface in material removal processes
are introduced in detail, including microstructure and residual stress. Some factors influencing the accuracy of the
prediction model are pointed out.
2016 Vol. 59 (20): 105-108 [
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