Home   |   About Journal   |   Editorial Board   |   Instruction   |   Publication Ethics Statement   |   Subscriptions   |   Contacts Us   |   Chinese
  Office Online  
    Submission Online
    Peer Review
    Editor Work
    Editor-in-chief
    Office Work
  Journal Online
    Accepted
    Current Issue
    Advanced Search
    Archive
    Read Articles
    Download Articles
    Email Alert
    
Quick Search  
  Adv Search
2017 Vol. 60, No. 8
Published: 2017-04-15
FEATURE
FIGURE
FORUM
NEW VIEWPOINT
RESEARCH
C0NTENTS
COVER STORY
 
       C0NTENTS
6 C0NTENTS
2017 Vol. 60 (8): 6-10 [Abstract] ( 96 ) HTMLNew PDF (2847 KB)  ( 147 )
       FEATURE
16 State-of-the-Art of Cryogenic Machining of Aeronautical Difficult-to-Machine Material
SUN Huibin
DOI: 10.16080/j.issn1671-833x.2017.08.016
The state-of-art of cryogenic machining is introduced. Effects of cryogenic machining on aeronautical
difficult-to-machine material machinability, cutting temperature, cutting tool wear condition, surface integrity, etc., are discussed.
Topics for further researches and applications are also addressed.
2017 Vol. 60 (8): 16-21 [Abstract] ( 207 ) HTMLNew PDF (1787 KB)  ( 648 )
       FIGURE
22 Unity of Science and Humanity
2017 Vol. 60 (8): 22-29 [Abstract] ( 352 ) HTMLNew PDF (1394 KB)  ( 853 )
       COVER STORY
24 Investigation of Ni-Based Brush Seal Coatings With Self-Lubricating Property at Elevated Temperature
ZHANG Tiantian1,2, HUANG Chuanbing1, LAN Hao1, FANG Shige1, ZHANG Weigang1
DOI: 10.16080/j.issn1671-833x.2017.08.024

In order to meet the requirement of self-lubricating and wear resistant properties of brush seal coatings for advanced aeroengines, two kinds of novel composite coatings, NiCoCrAlY-Cr2O3 and NiCoCrAlY-Cr2O3-AgMo, were prepared with plasma spray technology. Microstructures, phase compositions, mechanical properties, friction and wear performances of the above coatings were characterized and analyzed with scanning electron microscopy (SEM), X-ray diffraction (XRD), Raman spectroscopy and CSM high-temperature tribometer. The results show that both coatings exhibit very low porosity, high microhardness and tensile strength. The wear rates of two coatings are all at the order of 10-5 mm3· N-1·m-1, indicating the excellent wear resistance. The friction coefficient of the coating NiCoCrAlY-Cr2O3 decreases with temperature increasing, which shows a minimum value of 0.3 at 800℃ . NiCoCrAlY-Cr2O3-AgMo coating keeps a lower friction coefficient of about 0.23 from 400℃ to 800℃. Investigation of friction and wear mechanisms show that at 400℃, a lubricating film containing Ag is formed between the coating and the counterpart, while Ag2MoO4 formed above 600℃ effectively reduces the friction and wear at high temperatures.
2017 Vol. 60 (8): 24-29 [Abstract] ( 174 ) HTMLNew PDF (2502 KB)  ( 468 )
       FORUM
32 Hot Corrosion of Porous NiCr Alloy With NaCl Deposit at 750°C
CHEN Lingyun1,2, LAN Hao2, HUANG Chuanbing2, YANG Bin1,3, FANG Shige2, ZHANG Weigang2
DOI: 10.16080/j.issn1671-833x.2017.08.032
In order to elucidate NaCl-induced hot corrosion of NiCr-based abradable coatings in high-pressure compressor,
the porous 80Ni20Cr alloy was prepared by powder metallurgic process. The hot corrosion of porous NiCr alloy
with NaCl deposit at 750°C was investigated by SEM, EDS and XRD. Results show that NaCl accelerates the oxidation of
NiCr alloy by preventing the formation of continuous and compact Cr2O3. And cracks can be observed in the oxide scale
which consists of Cr2O3, NiO and NiCr2O4. Furthermore, the corrosion mechanism is also discussed by TG-DSC and thermodynamics
calculations. Cr could react with NaCl, accelerating the corrosion of NiCr porous alloy by chlorination and
oxidation.
2017 Vol. 60 (8): 32-36 [Abstract] ( 209 ) HTMLNew PDF (2496 KB)  ( 295 )
37 Thermal Cyclic Oxidation and Inter-Diffusion Behaviors of MCrAlY-Coated Single Crystal Superalloy DD6
LIU Jiuxiang, CUI Xiangzhong, GAO Wei, ZHOU Guodong, JIANG Chunzhu
DOI: 10.16080/j.issn1671-833x.2017.08.037
Two types of MCrAlY coatings NiCoCrAlY and NiCoCrAlYHfSi were deposited on DD6 specimens
by electron beam physical vapor deposition (EB-PVD) and low pressure plasma spray (LPPS) respectively. The coating
surface, cross-section morphologies and phase structures of the specimens were investigated by scanning electron microscopy
(SEM), energy dispersive spectroscopy (EDS), electron probe micro-analyzer (EPMA) and X ray diffraction (XRD)
after 1100℃ cyclic oxidation for different time. The utilization of NiCoCrAlY and NiCoCrAlYHfSi coatings prominently
enhance the oxidation resistance of DD6 alloy. After 100h oxidation, α-Al2O3 is still the major phase in the oxide scales
formed on the coated specimens. Inter-diffusion occurs between the coatings and the substrate, which leads to the formation
of the interdifusion zone (IDZ) and second reaction zone (SRZ). The rod-like TCP phase and the granular TCP phases precipitated
in the SRZ, which are rich in W, Re, Mo. Reactive elements (RE) Si, Hf have suppression action on the formation
of Cr-rich phase and the growth rate of TGO.
2017 Vol. 60 (8): 37-43 [Abstract] ( 248 ) HTMLNew PDF (4926 KB)  ( 607 )
44 Effect of Surface Treatment on Interface Morphology of Thermal Barrier Coating
YANG Wenhui, MU Rende
DOI: 10.16080/j.issn1671-833x.2017.08.044
The boat coating of HY5 prepared by arc ion plating was deposited on DD32 alloy substrate. The surface
were treated by vibratory polished (VS) and grit-blasted, and then YSZ was deposited on the bond coating by EB-PVD. The
microstructures of the bond coating by different surface treatments were investigated. The oxidation resistance of TBCs
was measured and compared. Furthermore, effects of surface on interface elementary composition and failure characteristic
were studied. The results indicate that both surface treatments can improve the bond coating surface and lead to better
oxidation resistance. Compared with TBCs treated by vibratory polished (VS) and grit-blasted, the scale morphology was
uniformon flat surfaces. After high temperature oxidation, wrinkling appeared on TGO with rough interface.
2017 Vol. 60 (8): 44-49 [Abstract] ( 261 ) HTMLNew PDF (2280 KB)  ( 504 )
       NEW VIEWPOINT
50 Control System of Combined Machining Machine Tool Based on Huazhong Numerical Control System
WANG Xiawang, SHEN Jianxin, TIAN Wei
DOI: 10.16080/j.issn1671-833x.2017.08.050
In order to improve the efficiency of drilling and riveting in the assembly process of large fuselage parts
and meet the requirement of high precision drilling, a collaborate control scheme of auto-drilling rivet system composed
of five-axis machine tool and end-effector is designed. The machine tool and high precision turntable are controlled by
Huazhong numerical controller and the end-effector is controlled by the PLC program of Beckhoof. After making clear the
drilling and riveting demands, the hardware configuration is designed based on industrial network and software configuration
is designed based on multi-software platform. And the integrated control software of the host computer is written using
Microsoft Visual Studio. The connection of the host computer control system with Huazhong NC system and Beckhoof
PLC employs the Ethernet and EtherCAT, respectively. The development of Ethernet interface in the integrated control
system uses Socket and some experiments on the combined machining machine tool are conducted. The control system has
many advantages as follows: good stability, high integration, fast response and high efficiency, which can meet the requirements
of drilling and riveting.
2017 Vol. 60 (8): 50-54 [Abstract] ( 267 ) HTMLNew PDF (1871 KB)  ( 1027 )
       RESEARCH
56 Flutter Suppression Technology on Automated Polishing of Blisk Blades
LI Xiaobiao, GU Xuehua, XU Xin
DOI: 10.16080/j.issn1671-833x.2017.08.056
Based on automated polishing machine of blisk, the geometric surface of fluttered blade was analysed.
Combined with the automated polishing system of blisk blade, the flutter mechanism was described. Based on the flutter
mechanism, the optimized programming technology, polishing parameters and improving system rigidity were determined
to solve the flutter problem. The optimized tool axis direction, polishing track, polishing parameters and filling method were
obtained. After experimental verification, the flutter is solved. And the waviness average error tends to decrease, surface
quality is improved greatly. The chatter marks are eliminated obviously.
2017 Vol. 60 (8): 56-58 [Abstract] ( 328 ) HTMLNew PDF (1367 KB)  ( 530 )
59 Experimental Investigation of Double-Side Laser Peening of Thin-Wall Parts With#br# Alternate Side Laser Scanning
WANG Dongyu, HU Yongxiang, YAO Zhenqiang
DOI: 10.16080/j.issn1671-833x.2017.08.059
Aeroengine compressor blade is a kind of typical thin-wall structure. Laser peening (LP) has been proved
to be an efficient surface treatment to improve the fatigue life of blades by inducing compressive residual stress. Laser
peening on blades at present is usually conducted in a double-side simultaneous scanning method to avoid deflection, which
brings the problem that shock waves from dual side meet at the center, resulting in spallation being at high risk to happen.
In this paper, a double-side alternate laser peening method is proposed. The results of the experiments show that with the
change of laser intensity, single-side laser peened thin-wall components can be made to bend toward or away from the laser
beam with single-side. The deflection would recover with the other side laser peened in the same parameters. With proper
laser peening parameters, similar distribution of residual compressive stress to the simultaneous method could be induced
on the components, and the final deflection would be within the scope of the accuracy requirement.
2017 Vol. 60 (8): 59-63 [Abstract] ( 255 ) HTMLNew PDF (1363 KB)  ( 433 )
64 Product Module Partition Method of Removable Design Based on#br# Improved Immune Clonal Algorithm
WEI Wei1, PENG Guanwei2, JI Jun3, YU Yong1
DOI: 10.16080/j.issn1671-833x.2017.08.064
Modularization design has advantages such as shortening the period of product development, improving
product performance. Removable design expands green design idea into the full life cycle of products. This paper integrates
modular design method and the removable design idea, and the removable design rules of modularity is proposed. Taking
removable degrees, internal polymerization degree, external coupling degree as optimization objective, the module partition
is done. According to the problem that ICA can’t get uniform Pareto optimal set when solving module partition problem,
an improved ICA is proposed, which deletes non dominated antibody from where antibody is crowded. This method get a
better Pareto optimal set. Then taking module division of the aircraft landing gear by the improved ICA as an example, the
result shows this method is feasible and applicability.
2017 Vol. 60 (8): 64-69 [Abstract] ( 186 ) HTMLNew PDF (1610 KB)  ( 479 )
70 Research on Self-Sealing Riveting Process by DEFORM-3D
LIANG Ying1，YAN Qiang2，LIU Gang3
DOI: 10.16080/j.issn1671-833x.2017.08.070
Riveting process parameters have an important effect on interference in self-sealing riveting. Based on
DEFORM-3D software, 4mm round head self-sealing rivets made of 2117-T4, and panels of 2024-T3 are discussed to analyze
the effect of three main process parameters, which are hole-diameter, iron shape and pressing force on riveting quality.
The simulation results show the riveting interference can be increased within 4.01-4.02mm hole-diameter, by using groove
iron and high-pressing force. Therefore, the sealing performance can be improved.
2017 Vol. 60 (8): 70-74 [Abstract] ( 264 ) HTMLNew PDF (1687 KB)  ( 315 )
75 Machining Clamping Process Visualization Document Generation of Aeroengine Parts
WU Quan, WEI Wei, ZHOU Laishui, HUANG Binda, LIU Wei
DOI: 10.16080/j.issn 1671-833x.2017.08.075
In the aeroengine manufacturing enterprises, part processing clamping is usually achieved by processing
personnel according to the technological procedures manual. It results in clamping information expression being not intuitive
and the fault packing and leakage phenomenon of work pieces because of the short of special processing clamping process
guidance document. The generation method of visualization document part processing clamping process is published
based on Tecnomatix and 3D PDF technology. Firstly, this method develops processing clamping process visualization
templates based on 3D PDF technology and develops module of part processing process information generation based on
Tecnomatix technology. And then generated XML documents by processing information generation module and generated
animation by Tecnomatix are implanted into the template. Finally, we can generate part processing clamping process visualization
document to achieve real-time interactive response of 2D information and 3D animation, and improve the efficiency
and accuracy of the clamping part processing.
2017 Vol. 60 (8): 75-78 [Abstract] ( 231 ) HTMLNew PDF (2659 KB)  ( 523 )
79 Study on Thermal Deep-Drawing Process of TC1 Titanium Alloy Cover Part
ZHANG Zhi1,2,3，LI Pengliang1,2,3，SUN Bin1,2,3，LI Junhong4
DOI: 10.16080/j.issn1671-833x.2017.08.079
According to the feature of TC1 titanium alloy cover part, the processing property of the part is analyzed.
The influence of some factors such as mould material, temperature, blank holder gap and drawing rate on the drawing formability
of TC1 titanium alloy cover part are discussed, meanwhile the appropriate parameters are optimized. The results
indicate that the proposed technological method is feasible for the integral forming of thin-walled TC1 titanium alloy with
large drawing ratios. Moreover, parts with high quality of flatness can be successfully formed by using air-demoulding
method. It provides a technical reference for picking off the similar parts.
2017 Vol. 60 (8): 79-83 [Abstract] ( 324 ) HTMLNew PDF (2118 KB)  ( 467 )
84 Research & Development of Management System on Mechanical Process Information for Aeroengine Parts
ZHOU Xingjing1, WEI Wei1,2, HUANG Binda1
DOI: 10.16080/j.issn1671-833x.2017.08.084
Aiming at difficult management and complicated changes of process information in traditional twodimension
machining process planning for aeroengine parts, through analyzing characteristics of the mechanical process
information, mechanical process information was divided into two types including static process information and dynamic
process information. Management system of mechanical process information for aeroengine parts was put forward and designed
under 3D environment. The structure and work flow of management system on mechanical processing information
were presented. The key technologies of the creation and searching of process repository, integration of process information
based on XML and visualization file generation of process planning were realized. Efficiency and quality of process planning
for aeroengine parts were improved and lead time of aeroengine parts was decreased effectively.
2017 Vol. 60 (8): 84-88 [Abstract] ( 197 ) HTMLNew PDF (2404 KB)  ( 430 )
89 Extracting the Centers of Dual Linear Structured Light Stripes for Seam Measurement
DING Zujiao1, LI Shuanggao1, ZHAI Jianjun1, LI Dong2
DOI: 10.16080/j.issn1671-833x.2017.08.089
Aiming at extracting the center position of light stripe in dual structured light seam measurement system,
a new method of sub-pixel center line abstraction from light strip based on adaptive threshold and Fourier fitting has been
proposed. According to the gray scale of optical cross section subjects to periodic distribution, in the first step, the proposed
approach gets the initial position of strip center by skeleton thinning approach. Then, the normal direction of each point on
skeleton lines is obtained by using the mean square of gray scale gradient. It uses adaptive threshold method to get the normal
width of each structured light strip. Finally, by doing Fourier fitting job using the gray scale within the normal width,
the peak value of the fitting curve could be obtained, and the center line as well. The experimental results show that the
average distance between the extracting corners and the line fitted by the extracting centers is only 0.1182 pixels and 0.1428
pixels, which is better than the skeleton thinning method and Gauss fitting method, meanwhile the method can improve the
accuracy of center line extraction from strip-structured light, the seam measurement precision can reach 0.04mm.
2017 Vol. 60 (8): 89-94 [Abstract] ( 379 ) HTMLNew PDF (1754 KB)  ( 552 )
95 Research on the Digitial Manufacturing Technology of Aircraft Welding Tube
HAN Zhiren1,2,Lü Yanying2,LIU Baoming1, LI Guangjun3
DOI: 10.16080/j.issn1671-833x.2017.08.095
According to the problems existing in the production of aircraft tube, the key technologies of digital assembly
tooling and automatic welding on the aircraft welding tube are researched, which can shorten the design cycle of tube
tooling, improve the accuracy of tube fixed position and the tube manufacturing precision. The establishment of mathematical
model of welding tooling using digital design method, the positioning and clamping of the tube welding are realized by
the method of hole location, the automatic welding is completed through coordinate conversion, seam tracking and modification,
and digital manufacturing of the welding tube is realized.
2017 Vol. 60 (8): 95-98 [Abstract] ( 259 ) HTMLNew PDF (1376 KB)  ( 554 )
99 Resin Flow Guiding Application of Lightning-Strike-Protection Copper Mesh in the VARI Process for Aviation Composite Parts
LI Peixu，CHEN Ping， SU Jiazhi，CHEN Jiping，HAN Xiaoyong，GAO Longfei，LIU Weiping
DOI: 10.16080/j.issn1671-833x.2017.08.099
With the widespread application of composite materials in aircraft structure, new demands on the lightning-
strike-protection for aviation composite parts have been raised. Meanwhile, represented by VARI process, the liquid
composite molding technology has caused more and more research attention. But the commonly used flow mesh will cause
material waste and quality problems. Combined with the two demands above, this article introduced the lightning-strikeprotection
copper mesh as flow media in the VARI manufacture process for aircraft composite parts in the surface application.
We integrated the resin flow guide and lightning-strike-protection functions of copper mesh and investigated its influence
on the resin flow, the relationship between the copper mesh layers and the resin permeability and the surface quality
of the cured composite parts. Our research has positive significance for enriching the technical means of VARI process,
improving the economical efficiency and the development of the application of VARI technology in aircraft structure.
2017 Vol. 60 (8): 99-103 [Abstract] ( 268 ) HTMLNew PDF (2795 KB)  ( 399 )
104 Applied Research of Carbon Fiber Composite in Launcher
LIN Shaoling, ZHANG Shiwei, ZHANG Yunlu, LUO Chuyang
DOI: 10.16080/j.issn1671-833x.2017.08.104
Currently, lightweight design of launcher is an important and challenging topic in airborne weapons system.
Carbon fiber composite materials are widely used in manufacturing load-bearing components with complicated shapes.
Therefore, such material is important in the lightweight design of airborne weapon systems. This paper studies a typical
structure of airborne launcher. After structural optimization, the component made of carbon fiber composite material is
manufactured using resin transfer molding (RTM). Experimental studies were performed on the component alone as well
as the whole assembly. This paper studies the manufacturing of load-bearing component using composite materials, and is
intended to provide theoretical guidelines for the applications of carbon fiber composite material in related area.
2017 Vol. 60 (8): 104-109 [Abstract] ( 324 ) HTMLNew PDF (2527 KB)  ( 670 )
  Notices
· 'Aeronautical Manufacturing technology ' is included in EI database
· China Science Citation Database (CSCD)
· Chinese S&T Journal Citation Reports (CJCR)
· World Journal Clout Index (WJCI) Report of Scientific and Technological Periodicals
· Supported in China Science and Technology Journal Excellence Action Plan
· Aeronautical Manufacturing Technology ranked No. 3 in Chinese S&T Journal Citation Reports (CJCR)
· High Quality Sci-tech Journal Classification Catalogue in Aerospace Field （2023）
· A Guide to the Core Journals of China (hosted by Peking University Library)
  Download
Copyright Transfer Agreement
  Links
22 AVIC Manufacturing Technology Institute
22 AVIC
Copyright © Editorial Board of Aeronautical Manufacturing Technology
Supported by: Beijing Magtech