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2017 Vol. 60, No. 15
Published: 2017-08-01
FEATURE
FORUM
NEW VIEWPOINT
C0NTENTS
COVER STORY
AEROENGINE MATERIALS
SURFACE TREATMENT
 
       C0NTENTS
6 C0NTENTS
2017 Vol. 60 (15): 6-10 [Abstract] ( 98 ) HTMLNew PDF (2933 KB)  ( 363 )
       FEATURE
16 Applications of Laser Ultrasonic Technology on Composite Structure Testing
JI Hongli, ZHANG Chao, QIU Jinhao
DOI: 10.16080/j.issn1671-833x.2017.15.016
Laser ultrasonic technique employs pulse laser to generate the Lamb waves in the structures, achieving
long-distance and non-contact Lamb wave measurement. Aiming at the problems of the safety and reliability detection in
aviation composite structures, the research topics on laser ultrasonic based composite structure testing are carried out at
Nanjing University of Aeronautics and Astronautics. Novel signal processing methods have been developed to extract the
Lamb wave propagation characteristics, which can be used in damage imaging, stiffness reconstruction and fatigue property
evaluation. The theoretical and experimental results show that laser ultrasonic technique can provide a novel non-destructive
testing method for the composite structures in the aviation industry.
2017 Vol. 60 (15): 16-22 [Abstract] ( 282 ) HTMLNew PDF (2108 KB)  ( 731 )
       COVER STORY
28 Key Technologies and Problems of Thermal Barrier Coating Application on Aeroengine Turbine Vane and Blade
CHENG Yuxian, WANG Lu, YUAN Fuhe
DOI: 10.16080/j.issn1671-833x.2017.15.028
The thermal barrier coating system is one of key technologies to improve reliability and service life of
turbine vane and blade. Compatibility between the superalloy substrate and bond coat, damage of the TBCs subjected to
CMAS deposit and methods to improve its resistance to CMAS, process control of thickness distribution over the turbine
vane and blade, reduction in diameters of the cooling holes, in-situ nondestructive test of TBCs quality and refurbishment
of worn TBCs are described with respect to engineering application technologies and problems to be solved for the TBCs
on turbine vane and blade.
2017 Vol. 60 (15): 28-34 [Abstract] ( 382 ) HTMLNew PDF (3786 KB)  ( 2954 )
       FORUM
38 Performance Oriented Machining Error Analysis and Statistic of Compressor Blade
CONG Jingmei1,2, MO Rong1, WU Baohai1, HOU Yaohua1
DOI: 10.16080/j.issn1671-833x.2017.15.038
Aiming to improve the machining quality of compressor blade of aeroengine, the influencing factors of
blade machining are analyzed, including processing plan and geometric modeling before machining, the problems of deformation
and stability during machining, the residual stress after machining. For the inevitable existence of machining error,
the probability statistics method is presented in the paper. In detail, the statistical analysis method of contour error and
airfoil parameters error in the key region of blade is established. With the help of aerodynamic experiments, the error distribution
of the key parameters under stable condition is found to provide the theoretical basis for guiding the specific blade
processing.
2017 Vol. 60 (15): 38-44 [Abstract] ( 267 ) HTMLNew PDF (2128 KB)  ( 544 )
45 Experimental Research on Five-axis Coordinated Micromilling of Micro Integral Impeller
LIANG Zhiqiang, FANG Ya’nan, ZHOU Tianfeng, GAO Peng, ZHANG Suyan,LIU Zhibing, WANG Xibin
DOI: 10.16080/j.issn1671-833x.2017.15.045
As the key component of the micro engine, the machining quality of the micro integral impeller has a
direct effect on the performance of the micro engine. In view of the micro integral impeller characteristics of narrow flow
channel, large blade twist and long thick ratio of blade, a five axis micro milling method for machining micro complex and
twisted integral impeller is studied. Aiming at the problems of deformation, over cutting and collision interference in the
process of micro impeller machining, the machining process of micro impeller is planned. The constraint equation of the
tool diameter selection for channel cutting is established, and the maximum theoretical tool diameter is calculated. The cutting
process of the impeller is simulated by CAM software, thus, the correctness of tool selection and process planning is
verified. Through five-axis micro milling experiment, a high quality 7075 aluminum alloy impeller with diameter of 10mm,
6 blades, 0.15mm minimum blade thickness, and 0.58mm minimum distance between the adjacent blades is obtained.
2017 Vol. 60 (15): 45-49 [Abstract] ( 210 ) HTMLNew PDF (2397 KB)  ( 355 )
50 Research Review of Deep Hole Machining Technology for Complex Shell Part
ZHANG Xiaodong1,2, HAN Ce1
DOI: 10.16080/j.issn1671-833x.2017.15.050
Deep hole machining is widespread in aerospace manufacturing industry and it is one of the most difficult
processes. Complex shell parts are the key parts of an aeroengine. The quality of the deep holes in shell parts has an immediate
im-pact on the service performance and life of an aeroengine. According to the technological characteristics and difficulties
of the deep hole machining for complex shell part, the existing method and key technologies of deep hole machining
in-cluding mechanical behavior, chip morphology and evacuation method, monitoring and equipment for deep hole machining
are summarized. At last, the research development of this field in the future is discussed.
2017 Vol. 60 (15): 50-57 [Abstract] ( 193 ) HTMLNew PDF (1971 KB)  ( 990 )
58 CNC Programming and Machining Technology for 5-Axis Milling of Turbine Blisk
ZHAO Wenming, SHEN Qi, WANG Bing, LIU Zhanqiang
DOI: 10.16080/j.issn1671-833x.2017.15.058
Turbine blisk has been widely applied in aero-engine due to its many advantages such as good structural
integrity, light weight, less assembling link and high assembling precision. Based on the machining characteristics of the
turbine blisk, it is simplified as a benchmark workpiece which can be investigated from two aspects of CNC programming
and cutting operation. Firstly, CNC programming of the benchmark workpiece was conducted with HyperMILL software.
The ideal tool path were obtained, which can be ensured high efficient and high quality machining of the workpiece. Then,
the benchmark workpiece material used TC4 titanium alloy which was milled with DMU-70V five-axis machining center.
During the finishing of the blades and the hub surfaces, the cutting forces were on-line measured for different end millingtools.
Finally, the surface morphology of the blades and hub machined surfaces were observed. The machining performance
of the different milling tools for the benchmark workpiece of TC4 titanium alloy is evaluated with the measured cutting
forces and surface morphology.
2017 Vol. 60 (15): 58-63 [Abstract] ( 186 ) HTMLNew PDF (3493 KB)  ( 595 )
64 Experimental Research on Five-axis Coordinated Micromilling of Micro Integral Impeller
LIANG Zhiqiang, FANG Ya’nan, ZHOU Tianfeng, GAO Peng, ZHANG Suyan,LIU Zhibing, WANG Xibin
DOI: 10.16080/j.issn1671-833x.2017.15.064
As the key component of the micro engine, the machining quality of the micro integral impeller has a
direct effect on the performance of the micro engine. In view of the micro integral impeller characteristics of narrow flow
channel, large blade twist and long thick ratio of blade, a five axis micro milling method for machining micro complex and
twisted integral impeller is studied. Aiming at the problems of deformation, over cutting and collision interference in the
process of micro impeller machining, the machining process of micro impeller is planned. The constraint equation of the
tool diameter selection for channel cutting is established, and the maximum theoretical tool diameter is calculated. The cutting
process of the impeller is simulated by CAM software, thus, the correctness of tool selection and process planning is
verified. Through five-axis micro milling experiment, a high quality 7075 aluminum alloy impeller with diameter of 10mm,
6 blades, 0.15mm minimum blade thickness, and 0.58mm minimum distance between the adjacent blades is obtained.
2017 Vol. 60 (15): 64-69 [Abstract] ( 236 ) HTMLNew PDF (2229 KB)  ( 594 )
       NEW VIEWPOINT
70 Summary of Variable Geometry Combustion Chamber
GAO Zhigang1, ZHAO Ming1, CHEN Yanghui2, JIANG Bozhou1
DOI: 10.16080/j.issn1671-833x.2017.15.070
The research status of variable geometry combustion chamber at home and abroad is summarized in this
article. The structure of variable geometry in combustion chamber includes air splitter, swirler, dilution hole and flame
stabilizer. The concept of variable geometry provides a flexible control of the possibility of internal airflow distribution in
the combustion chamber, providing new breakthroughs in reducing engine exhaust emissions, improving combustion efficiency,
and maintaining stable and reliable combustion chamber operation.
2017 Vol. 60 (15): 70-74 [Abstract] ( 235 ) HTMLNew PDF (1106 KB)  ( 367 )
       AEROENGINE MATERIALS
76 Development Situation and Application of SiC/SiC Ceramic Matrix Composites in Aeroengine
ZOU Hao, WANG Yu, LIU Gang, ZHAO Long, BAO Jianwen
DOI: 10.16080/j.issn1671-833x.2017.15.076
SiC/SiC ceramic matrix composites (CMC) have great potential to be utilized as structure material in gas
turbines, due to their excellent properties such as low density, high strength and toughness, superior temperature oxidation
and creep resistances, high thermal shock and corrosion resistances, low thermal expansion coefficient. In the present paper,
development situation of the domestic and foreign SiC/SiC CMC is systematically reviewed from the fileds of silicon carbide
fibers, preparation, interphase and coating. Moreover, the application of CMC on hot-structural parts of gas turbines,
such as combustor liner, mixer, turbine shroud/wane/blade and nozzle flap, are introduced based on its property characteristic.
2017 Vol. 60 (15): 76-84 [Abstract] ( 441 ) HTMLNew PDF (2403 KB)  ( 1436 )
85 Research and Application of Polyimide Composites for Aeroengine
WANG Jing, LIAN Yilong, HAN Xiufeng
DOI: 10.16080/j.issn1671-833x.2017.15.085
Research progress and application of polyimide based composites in aeroengine were reviewed. The performance
of PMR polyimide composites and its application in areoengine were introduced, and the preparation process, characteristic
products and research advance of polyimide composite bushing were discussed. It is pointed out that the trends of
polyimide composites for aeroengine in the future are of lower cost, higher heat-resistance, improved processing stability,
and the establishment of polyimide database.
2017 Vol. 60 (15): 85-91 [Abstract] ( 319 ) HTMLNew PDF (912 KB)  ( 957 )
       SURFACE TREATMENT
92 Optimization of a Pulse Electorplating Copper Process for Improving Carburization Resistance
LI Hanye, SUN Huiyan, YUAN Fuhe
DOI: 10.16080/j.issn1671-833x.2017.15.092
A copper electroplating process is optimized to realize an effective local protection of non-carburization
areas of aeroengine components. The primary, minor parameters of a pulse electroplating copper process are identified and
optimized in the present work through orthogonal experiment and range analysis. The copper plating deposited using the
optimized pulse process demonstrates an excellent interface adhesion state, with surface morphology, porosity and carburization
resistance better than that electroplated using a direct current. The thickness of the copper plating might be decreased
to 20μm from 50-70μm using the optimized pulse electroplating copper process, thereby saves the cost and enhance the efficiency
of copper electroplating production.
2017 Vol. 60 (15): 92-96 [Abstract] ( 175 ) HTMLNew PDF (3103 KB)  ( 487 )
97 Research on Engineering Application for Carburizing-Quenching Process of the Thin-Wall Hollow Shaft for 9310-Stell
LI Ke, ZHANG Li, LUO Qiang
DOI: 10.16080/j.issn1671-833x.2017.15.097
Carburization-quenching process of aerongine has been researched. Vacuum-carburizing process parameters
has been adjusted. The results showed that the depth of the surface coating was 0.5 mm. Step quenching, loading mode, and
stress-relief method has been improved. The part has high hardness and small deformation after carburizing and quenching,
through the assessment of the aeroengine 150h lasting. The prospect of engineering application for carburization-quenching
process of thin-wall hollow shaft was very good.
2017 Vol. 60 (15): 97-100 [Abstract] ( 224 ) HTMLNew PDF (1995 KB)  ( 491 )
101 Effect of Surface Condition and Electrolyte on Electrochemical Jet Machining (EJM) of Ti6Al4V
SONG Yongwei, TUO Zhanyu
DOI: 10.16080/j.issn1671-833x.2017.15.101
Ti-alloy is widely used in aeroengine, sodium nitrate solution (NaNO3) and sodium chloride solution
(NaCl) are widely used in electrochemical jet machining (EJM). This paper Focused on the machining performance of Tialloy
with the use of EJM. At first, the two kinds of electrolytes were tested on Ti-alloy with different surfaces. Then the
processing quality was explored by analyzing the channel aspect ratio (depth/width), channel surface roughness (Sa), oxide
percentage and surface topography. At last the two kinds of electrolytes were used in EJM in different orders again, and the
excellent order was confirmed. Those two tests provided academic and experimental basis for the improvement of EJM on
Ti6Al4V.
2017 Vol. 60 (15): 101-107 [Abstract] ( 244 ) HTMLNew PDF (3571 KB)  ( 413 )
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· '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)
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