Transcript Document 7116607

NILPRP
Nanostructured, multifunctional films prepared
by thermionic vacuum arc technology
Cristian P. LUNGU
”Elementary Processes in Plasma and Applications” Group
NATIONAL INSTITUTE FOR LASERS, PLASMA AND
RADIATION PHYSICS
Magurele - Bucharest
Romania
NATIONAL INSTITUTE FOR LASERS, PLASMA AND RADIATION
PHYSICS
NILPRP
Group: “Elementary Processes in Plasma and Applications”
Contact person: Dr. C. P. Lungu
E-mail:[email protected]; Web:www.inflpr.ro
Group members: 1 Professor, 5 PhD Researchers, 3 Researchers,
1 Assist. Res., 4 Students, 3 Technical staff.
Team : 1. Prof. Dr. Musa Geavit, 2. Dr. Mustata Ion, 3. Dr. Lungu P. Cristian, 4. Dr. Popa Silviu Dan, 5.
Dr. Ciobotaru Luminita, 6.Dipl. Phys. Lungu Ana Mihaela, 7. Dipl. Eng. Phys. Chiru Petrica, 8. Dr. Surdu
Bob Cristina, 9. Dipl. Phys. Brinza Ovidiu, 10. Techn. Dragusin Vasile, 11. Techn. Balint Mihaela, 12.
Techn. Ilie Florian, 13. Techn. Zaroschi Valer, 14. Student Barbu Ionut, 15. Student Badulescu Marius, 16.
Student Vizitiu Cristina, 17. Student Budaca Radu.
Cooperation
•National Institute of Micro and Nanotechnologies,
•National Institute of Materials Physics,
•“Ovidius” University Constanta,
•“Politehnica” University, Bucharest,
•Bochum University,
•Commenius University, Bratislava
•Japan Ultra-high Temperature Materials Research Institute
NATIONAL INSTITUTE FOR LASERS, PLASMA AND RADIATION
PHYSICS
The group developed an original technology
called Thermionic Vacuum Arc (TVA), suitable
for nanostructured, multifunctional film preparation
Applications:
DLC coatings for MEMS applications
Tribological coatings
Giant magnetoresistive (GMR) films
High temperature resistant to oxidation coatings
NILPRP
The main advantages of the TVA method:
- Deposition of pure metal film in high or ultra - high vacuum conditions (<10-4torr);
- No gas consumption and gas incorporation in the growing film;
- The growing thin film is bombarded just during deposition with the ions of the depositing
material insuring the compactness of the film;
- The energy of bombarding ions can be controlled and can be even changed during
deposition;
-The film is nanostructured and the surface of the deposited film is smooth;
-The deposition rate can be easily controlled and can be greater than in the sputtering case
(0.1 – 10 nm/s).
TVA apparatus. Volume ~ 1m3; Base pressure:
<10-6 torr
DC Power supplies: 6kV, 5A; 5kV,1A; 3kV, 2A;
0.6kV, 20 A
TVA plasma during
deposition on turbine blade
THERMIONIC VACUUM ARC (TVA) PRINCIPLE
An intense
thermoelectronic emission
from an heated cathode (a
tungsten filament) is
focused by a Whenelt
cylinder on the anode.
Cathode
W crucible
Anode
The anode consists
of a crucible, filled
with the material
to be deposited.
This assembly is
mounted inside a
vacuum vessel.
Working parameters used in the TVA technology for DLC film
deposition
cathode- anode
(sizes)
Anode
diameter: 10 mm
TVA
Current
intensity:
0.3 - 1.25 A
Carbon depositions
Time:300-600 s
Anode length:
40 mm
Potential:
300 V2 kV
Rate:
0.5-10 nm/s
cathode-anode
distance:
4 mm
Working
pressure:
≤ 10-6 torr
Thickness:
>100 nm
Diamond like carbon films observed by High Resolution
Transmission Microscopy (HRTEM) and XPS
TEM equipment
•
•
•
•
•
•
•
•
Philips CM 120 ST
Max. HT = 120kV
Resolution 1.4 Ǻ
Magnification 1.2M
Compustage 5 axis
Remote control
Analysis Software
HP CD-Writer
HRTEM and SAED
XPS analysis
Sample Description: C1s
10 runs x 250 ms; smooth 3; cor.energii = 0.12
Counts
A
Composition Table
70000 89.3% A
10.7% C
60000
A 285.46 eV 2.73 eV 79822.7 cts
B 288.73 eV 2.73 eV 8241.26 cts
50000
C 284.47 eV 2.73 eV 9593.26 cts
Baseline: 291.78 to 280.64 eV
40000
Chi square: 3.41711
20000
C
B
30000
10000
296
Image of carbon thin film and electron diffraction.
292
288
284
Binding Energy, eV
280
XPS C1s peak deconvolution
sp3 bonds: 89.3%,
sp2bonds: 10.7%
Low friction coatings for plain bearings
Low friction coating materials are new classes of advanced materials, which exhibit a
reduced coefficient of friction in dry sliding and raised wear resistance.
Overlay
Bearing alloy
Demand properties for bearing
Back steel
The overlays that provide seizure, wear
resistance and conformability are usually
made by electroplating of 10 mm - 20 mm
thick Pb alloy.
•Seizure resistance
•Conformability
•Fatigue strength
•Wear resistance
•Corrosion resistance
The engine bearing
Piston
Connecting Rod
Main Bearing
Connecting Rod
Bearing
Crank shaft
Connecting Rod
Bearing
Main Bearing
1.0
Bronze substrate
0.9
Coefficient of friction
0.8
(b)
0.7
(b)
0.6
0.5
(a)
0.4
(a)
0.3
0.2
0.1
Load: 1N
0.0
0
50
Load: 5N
100
150
200
Sliding distance, m
Plain bearings for automotive
applications coated with
antifriction Ag/DLC overlay
Drastically decrease of the coefficient of
friction by increasing the graphite (DLC)
concentration in the overlay
sample (a): 44.82 mass%C;
sample (b): 19.27mass%C;
Ag concentration: balance
GRANULAR, MAGNETOREZISITIVE FILMS
Substrate
Screen
Catode 1
φ1
φ2
Catode 2
Cu
Co
•
•
•
Two independents TVA guns
Every gun: independent filament and dc supply
A metallic screen separates the two TVA discharges.
AFM images of the CoCu films
AFM Images of the FeCu films
Fe concentration of the Fe Cu films
FeCu films non-treated and thermally
treated
Magnetorezisitive effect of the FeCu film
NiCu films non treated and thermally
treated
FeCu
prob no. 5
dFe=32.5 cm
dCu=38.5 cm
non treated
thermal treated
0.00
-0.05
-0.10
-0.15
NiCu
prob no. 6
dNi=32.9 cm
dCu=38.2 cm
non treated
thermal treated
0.00
-0.02
-0.25
(Rh/R0)-1 (%)
(Rh/R0)-1 (%)
-0.20
-0.30
-0.35
-0.40
-0.45
-0.04
-0.06
-0.08
-0.50
-0.55
-0.10
-0.60
-0.8
-0.6
-0.4
-0.2
0.0
B(T)
0.2
0.4
0.6
0.8
-0.8
-0.6
-0.4
-0.2
0.0
B(T)
0.2
0.4
0.6
0.8
High-temperature oxidation resistant coatings
Refractory metals such as W, Mo, Ta and Nb are promising
candidates for the development of new kinds of heat resisting
materials (One of their most fatal shortcomings is low
resistance against oxidation at high temperatures)
60% Ni, 40%Al.
10-100m
60%Re, 30%Cr, 10%Ni
10-100m
Re
Superalloy
(Nb/W/Si/Hf)
5-10 m
This problem is
expected to be solved
by forming multilayered coatings:
•a barrier against coming and outgoing elements (Re),
•a reservoir supplying lost elements (Re-Ni-Cr) and
•a heat resistant layer (Ni-Al).
Re
Mo
Photograph of the Re ingot during
deposition
Nb
superalloy
(Optical
micrograph
Re
Nb
superalloy
SAED
HRTEM
SEM
Selected area diffraction (SAED), high resolution
transmission microscopy (HRTEM) and scanning electron
microscopy (SEM) images of the nanostructured Rhenium
film deposited on Nb superalloy by TVA
DTA and TGA analysis of Re-Cr film
DTA
uV
TGA
mg
0.00
3.00
Temp
C
800.00
2.00
SEM analysis of Re-Cr film
600.00
1.00
-500.00
400.00
0.00
-1.00
200.00
-2.00
-1000.00
0.00
0.00
20.00
40.00
60.00
Time [min]
DTA
uV
TGA
mg
Temp
C
0
797.48x10
C
6.00
0
712.18x10
C
0.00
800.00
5.00
0
477.01x10
C
0
509.01x10
C
0
660.70x10
C
600.00
4.00
0
636.59x10
C
-500.00
400.00
3.00
0
587.68x10
C
2.00
200.00
1.00
-1000.00
0.00
0.00
20.00
40.00
Time [min]
60.00
CONCLUSIONS
TVA technology can be used for preparation of nanostructured
multifunctional films: Applications: DLC for MEMS and high
Emissivity, Tribological, GMR, and High Temperature Resistant
to Oxidation films.
Ag-DLC films with low coefficient of friction were prepared to be
applied at the plain bearing for automotive applications.
Were obtained granular films with GMR effect ([R(H)-R(0)]/R(0)) in
Co-Cu films in the range of 5% and 10 % without postdischarge treatment and about 33% with thermal treatment after
deposition. In the case of de Fe-Cu films the obtained maximum
effect was of 38%, leading to the possibility to use the films at
magnetoresistive sensors preparation.
The Re-Cr antioxidation, high temperature resistant films are used
for thermal barrier coatings of the turbine blades for more
efficient energy conversion.
REFERENCES
1.
C.P.Lungu, Nanostructure influence on DLC-Ag tribological coatings, Surf. and Coat. Techn, in print,
(2005).
2.
C. P. Lungu, I. Mustata, G. Musa, A. M. Lungu, V. Zaroschi, K. Iwasaki, R. Tanaka, Y. Matsumura, I.
Iwanaga, H. Tanaka, T. Oi, K. Fujita: Formation of nanostructureed Re-Cr-Ni diffusion barrier coatings
on Nb superalloys by TVA method, Surf and Coat. Techn, in print, (2005).
3.
V. Kuncser, I. Mustata, C. P. Lungu, A. M. Lungu, V. Zaroschi, W.Keune, B. Sahoo, F. Stromberg, M.
Walterfang, L. Ion and G. Filoti: Fe-Cu granular thin films with giant magnetoresistance by thermionic
vacuum arc method: Preparation and structural characterization, Surf and Coat. Techn, in print, (2005).
4.
C. P. Lungu, K. Iwasaki, K. Kishi, M. Yamamoto and R.Tanaka, Tribo-ecological coatings prepared by
ECR-DC sputtering, Vacuum, 76, Issues 2-3, (2004) 119-126.
5.
C. P. Lungu, I. Mustata, G. Musa, V. Zaroschi, Ana Mihaela Lungu and K. Iwasaki: Low friction
silver-DLC coatings prepared by thermionic vacuum arc method, Vacuum, 76, Issues 2-3, 127-130,
(2004).
6.
I. Mustata, C. P. Lungu, A. M. Lungu, V. Zaroski, M. Blideran and V. Ciupina: Giant magnetoersisitve
granular layers deposited by TVA method: Vacuum, 76, Issues 2-3, 131-134 (2004).
7.
C. P. Lungu, K. Iwasaki: Influence of surface morphology on the tribological properties of silvergraphite overlays, Vacuum, 66 (2002) 385-391
8.
S.Q. Xiao, K. Tsuzuki, C. P. Lungu, O. Takai, Structure and properties of CeN thin films deposited in
arc discharge, Vacuum, 51-4, pp.691-694, (1998).
9.
Shiqin Xiao, Cristian P. Lungu, Osamu Takai, Comparison of TiN deposition by rf magnetron
sputtering and electron beam sustained arc ion plating, Thin Solid Films, 334, 1-2, pp. 173-177, (1998)
10. O. Takai, M. Futsuhara, M. Shimizu, C. P. Lungu, J. Nozue, Nanostructure of ZnO Thin Films
Prepared by Reactive rf Magnetron Sputtering, Thin Solid Films, 318, 1-2, pp. 117-119, (1998)
R
INCAS
National Institute for Aerospace Researches
“Elie Carafoli” - INCAS SA, Bucharest
220, Iuliu Maniu, Sect 6, Bucharest, Phone:004.021.434.00.83, Fax:004.021.434.00.82
web: www.incas.ro, e-mail: [email protected]
3.4.2.2. TECHNOLOGIES ASSOCIATED WITH THE
PRODUCTION, TRANSFORMATION AND PROCESSING OF
KNOWLEDGE-BASED MULTIFUNCTIONAL MATERIALS
Dr.Ing V.Manoliu
[email protected]
PLASMA SPRAY PROCESSING
The fundamental characteristics of plasma process are represented by the assured flame temperature,
about 15000 Celsius degrees, jet speed about 300 m/s, layer porosity about 2%. The main parameters of
the plasma process are sketched as follows:
•Plasma parameters:
Air dilution
Gas composition
Plasma jet temperature
Speed
•Flame:
Flame speed
Spraying distance
•Nozzle:
Flow gas
Powder flow
 Powder:
Distribution,size, grain shape
Spray speed distribution
Staying time in plasma
 Under layer
Temperature
Residual tension control
Particle impact speed
Table no1
The potential application of the plasma coatings
Industry
Function of coatings
1
2
Chemical
•
•
Power
•
Space and aeronautical
•
3
4
5

7
8
9
10
11
•





o
o
•
6
o
•
•
o

Nuclear
o
Medicine
o
Metallurgy
Materials technology
•

•
•

•
o

 o
o
o
•
o
1 – anticorrosive protections; 2 – anti wear protections; 3 – electronic proprieties; 4 – radiation;
5 – chemical/biological proprieties; 6 – ended form; 7 – restore; 8 – powder processing;
9 – sensitive composite; 10 – unstable materials; 11 – amorphous coatings trough solidification
 - high potential
• - industrial
application
or in progress of
introducing
o - in progress of
development
Without symbol –
unexplored
potential
The process limits are specially determined by the reduced
adherence between metal support and
bonding layers, high porosity and partial oxidation of the
particles.
Fundamental problems to be solved in our opinion by the
research in the field are represents by the:
Plasma generator power increase;
Powder flow speed increase;
Comparable study of the condition by air pressure
environment about layers porosity, structure modification ,
deposition part;
Realisation
for
management
of
the
technological process, especial for ceramic layers
of a relax structure with deliberate accomplished
porosity and micro cracks;
Computerised metallography and electronic
microscopy investigations regarding the interface
aspects, support - adherence layer - external
layers and dynamic of the modifications induced
by different mechanic and thermal stresses.
Fig. 1 Plasma jet installation
3.4.2.2.3. MULTIFUNCTIONAL CERAMIC THIN FILMS
WITH RADICALLY NEW PROPRIETIES
INCAS have the experience to achieve some duplex, triplex layers, FGM - functionally graded
materials, ceramics for industrial proposed especial for “hot parts” of turbojet , for some
metallurgy parts, power industry, etc.
The aimed parts are stressed at erosive, corrosive wear, thermal shock, sliding friction,
which can work simultaneously at high values.
The ceramic layers unanimous utilized, generally partial stabilized zirconia base, have as main
servitude, the major difference between thermal expansion coefficients values of ceramic layers and
metallic support during thermal shock and associated induced internal stressed.
To decrease the thermal shock effect on the ceramic layers, multilayered structures, FGM, etc. are
utilized. Each intermediate layer composition is graded between external layers (internal and external).
A progress in this domain, is represented by the recent experimental studies performed
by Lewis Research Center, Cleveland, Ohio, for plasma sprayed coatings.
An improved bond coat, incorporating metallic or ceramic and cermets layers has been
demonstrated to increase the thermal fatigue life of a plasma sprayed TBC by a factor
of two or more. Utilizing this system, the second layer of the bond coat incorporates a fine dispersion
of a particulate second phase in a MeCrAlY matrix. The second phase is required to have a coefficient
of thermal expansion as low as possible or preferable lower than yttrium zirconium layer and it must be
stable up to intended temperature, chemically inert with respect to the MeCrAlY matrix and must be
chemically compatible with the thermal grown alumina scale.
INCAS has in progress evaluation experiments of the triplex layer
type MeCrAlY/MeCrAlY 90% + Al2O3 10%/ZrO2. Y2O3
obtained by plasma spray technology .
Fig. 2 Ceramic and bonding layers, SEM imagine
Fig. 3 Zr associate distribution
Within the consortium, in this direction, INCAS is able to participate especially in the achievement
of some multifunctional layers , thermal shock stressed .
Quick thermal shock test installation for multifunctional ceramic coatings
Protection layers and especial ceramics have main servitude lower resistance at thermal shock.
For aeronautical application, rockets, metallurgical, power industries, is important the behavior of
this coatings in limited functional conditions - with additionally requests.
Thermal shock classical installation mentioned in literature have heating
cooling cycle with substantial low speed than extreme functional conditions. In the same
context are not testing methods in extreme condition, unanimous accepted.
The main characteristics of the proposed thermal shock installation:
• testing sample dimensions-rectangle LxWxH {mm} - 25x25x2;or circular 25x1÷2 mm
•the test specimen materials: metals, alloys, composite materials, ceramic materials, coatings
(enamel, multilayered, TBC, FGM, etc.)
• maximum testing temperature: +1400 degrees Celsius
•heating time from the environment temperature till the testing temperature:15÷150 sec
•cooling time from the testing temperature till the environment temperature:15 ÷250 sec
•temperature speed measurement : 150 ms
•sample view during the test
•temperatures measurement during all the time test
•samples photo in the heating and cooling areas
•samples lighting in the heating and cooling areas
•manual cycle
•automatic cycle
3.4.2.3. ENGINEERING SUPPORT FOR MATERIALS DEVELOPMENT
3.4.2.3.1. MATERIALS BY DESIGN: MULTIFUNCTIONAL ORGANIC MATERIALS
Nanocomposites epoxy-Montmorillonite
Nanocomposites are a new class of advanced, nanometer-scale multiphase polymer composites that often
display many enhanced physical properties: strength, hardness, thermal and viscoelastic properties.
Nanocomposites are synthesized by dispersing expholiated clays, nanometer particle and aggregates into a
polymer matrix (epoxy) or by infiltrating epoxy into the interlayer structure of layered silicates.
INCAS in cooperation with ICECHIM Bucharest develop researches regarding nanocomposites epoxyMontmorillonite (aluminum hydrate silicate), via second way. In the first stage some samples of epoxy resin
as such and epoxy-10% Montmorillonite (weight) are performed.
The mechanical testing results up to date are synthesized in table 2.
Table no. 2
Epoxy resin characteristics with and without Montmorillonite
Sample
No.
1
2
Epoxy LY 554
Epoxy LY
554+10%
Montmorillonite
Tensile
Strength
[MPa]
Young Module
E
[MPa]
Hardness
[Shore]
110
28 000
52 000
75
120-130
83
It is to notice the significant effect of the Montmorillonite addition upon the elasticity modulus.
The researches will be continued with complementary studies regard nanocomposites-epoxy-glass
fiber, nano epoxy-fibers composites and maybe nano epoxy-carbonnanotube, incorporated..
3.4.3.1. DEVELOPMENT OF NEW PROCESSES AND FLEXIBLE, INTELLIGENT
MANUFACTURING SYSTEMS
3.4.3.1.1. NEW PRODUCTION TECHNOLOGIES FOR NEW MICRO-DEVICES USING ULTRA PRECISION
ENGINEERING TECHNIQUES
Carbon – carbon composites nano-ceramic matrix
Carbon fiber and carbon-carbon was first developed for aerospace technology (component in missiles,
reentry vehicles, in space shuttles as structural parts and as brake lining and brake disc material for
civil and military aircraft).
Materials and Tribology Department of INCAS realized performing carbon fiber (PAN precursor) and
carbon-carbon composites, phenolic matrix.
In fig. 4 and Fig. 5 the Debyegram of PAN precursor and thermooxidate PAN are presented. Intensity
diminution of peak diffraction points out adequate PAN stabilization.
Fig. 4
PAN Debyegram
Fig. 5
Debyegram of the thermooxidate PAN
Some characteristics of FC obtained are synthesized in table 3.
Table 3
Tensile strength
[MPa]
3,1x103
Characteristics of FC
E, Young
modulus
[MPa]
2.4x105
Table 4
No.
1
2
3
4
Fibre diametre
[milimicroni]
%C
Process out put
7
98.5
50%
Mechanical and tribologies characteristics
Material
CF – 2D tissue composite
CF – Uni directional composite
Chopped FC (3.5 mm)
composites
C-C composites 2D tissue
Tensile stregth
[MPa]
750
850
300÷350
Friction
coefficient
0.13
0.13
0.13
200÷250
0.13
In fig. 8 and fig. 9 are point out the effects of thermal treatment upon density and mechanical
characteristics of the C-C composites.
Fig.8 Tensile strength variation during
Fig.9 Density variation during thermal
thermal treatment of C-C composites
treatment of C-C composites
Recently researches report on C-C composites and nano C-C composites as brake materials.
The main features of C-C as friction materials for aircraft brakes are:
•a great ablation heat (20.000 Kcal/Kg)
•specific weight 1,7 ÷ 1,9 Kg/dm3
•friction coefficient 0,3
•dimensional stability at high temperatures (small dilatation coefficient, max 2x10-6 v.s.10-5 for steel)
For concordance in tribological and antioxidant properties of C-C composites distinct solutions was
developed:
•
FC - fiber (unidirectional 2D tissue, chopped, felt preform) and phenolic matrix with 25% CSi
(reported
to phenolic resin)
•
Nanocomposites C-C ceramic matrix via so called LSI (Liquid Silicon Infiltration).
The sol gel SiO2 (50% weight reported to phenolic resin) infiltrated in a C-C by thermal treatment
at 1600°C generate ceramic matrix (CSi). The results of tribological testing are presented in table no 5:
Friction coefficients for C-C composites
Table no 5
Material
Friction
coefficient
1
C-C composite
0,13÷0,14
2
C-C+25% C-Si composite
0,3÷0,35
3
C-C+50% SiO2 colloidal composite
0,3÷0,35
No.
In the future INCAS- Material and Tribology Laboratory aims to achieve carbon fiber
composites ceramic matrix, via nanosilicium carbide-mesophase, or to use polymeric
precursor (policarbosilane) for CSi matrix.
NILPRP
NATIONAL INSTITUTE FOR LASER, PLASMA AND
RADIATION PHYSICS, BUCHAREST, ROMANIA
COMBINED MAGNETRON SPUTTERING AND ION
IMPLANTATION – A NEW HIGH ENERGY ION
ASSISTED DEPOSITION METHOD TO PRODUCE HARD
NANOCOMPOSITE COATINGS
Dr. Cristian Ruset,
Head of Plasma Physics and Nuclear Fusion Department
[email protected]
THE CONCEPT AND SPECIFIC ASPECTS OF THE METHOD
•
A high voltage pulse discharge is superposed over the magnetron sputtering deposition
and this is CMSII process.
• The components to be coated are positioned into the deposition chamber on a special
jigging system, insulated to 100 kV, and they are connected to a high voltage pulse
generator. The plasma ions from the magnetron discharge are accelerated during the
high voltage pulses and strike initially the substrate and then the layer itself during its
growing with energies of tens of keV. Typical parameters of the high voltage pulse
discharge are: U = 50kV,  = 20 s, f = 25 Hz.
• As a result of this periodical ion bombardment the following effects occur:
- A significant enlargement (up to 5 – 7 m) of the layer-substrate interface resulting into
a strong adhesion between the layer and the substrate. For conventional magnetron
sputtering this interface is of ~ 1m.
- A featureless, extremely dense, pore free nano-structure is produced. The typical
columnar structure of TiN does not exist any more. TEM analyses have shown
crystallites with a size of less than 10 nm.
- A high densification of the layer. Using a titanium magnetron target, nc-Ti2N/nc-TiN
nanocomposite layers with a hardness of 25  40 GPa have been obtained.
- A stress relief at the interface and within the layer. Due to this effect, layers with a
thickness of 10 – 50 m have been produced.
- Increase by a factor of ~ 4 of the deposition rate comparing with standard magnetron
sputtering. The actual deposition rate for nc-Ti2N/nc-TiN coating is 4 – 5 m/h.
SEM micrograph of the
nc-Ti2N/nc-TiN coating deposited by CMSII
demonstrating its featureless and extremely
dense structure
Cross-sectional TEM microstructure (a) and plane
view TEM microstructure with corresponding SAED
pattern (b) of the
nc-Ti2N/nc-TiN coating deposited by CMSII
(a)
(b)
DEPTH PROFILES OF THE CONSTITUENTS FOR THE
COATINGS DEPOSITED BY SMS AND CMSII
100
10
9
8
Nitrogen
70
Iron
7
60
6
Carbon
50
5
40
4
30
3
Titanium
20
2
10
0
0,0
1
2,5
5,0
7,5 10,0 12,5 15,0 17,5
Depth below surface [m]
20,0
22,5
100
Ti, N and Fe Concentration [at.%]
0
25,0
10
90
(b)
9
Titanium
80
70
8
7
Iron
Carbon
60
50
6
5
Nitrogen
40
4
30
3
20
2
10
1
0
0,0
C Concentration [at. %]
80
2,5
5,0
7,5 10,0 12,5 15,0 17,5
Depth below surface [m]
20,0
22,5
0
25,0
C Concentration [at.%]
(a)
Ti, N and Fe Concentration [at. %]
90
OPTICAL MICROGRAPH OF A nc-Ti2N/nc-TiN
COATING
25 m
POTENTIAL APPLICATION AREA FOR
nc-Ti2N/nc-TiN NANOCOMPOSITE COATINGS
•
•
•
•
•
Cutting tools
Forming tools (plastic injection dies)
Calibration tools
Drawing shafts and extrusion dies in pipe industry
Automotive industry (piston rings, fuel injection pumps, various
shafts, etc.)
• Hydraulics
• Medical instrumentation
• Orthopedic prostheses, etc.
END MILLS COATED WITH
nc-Ti2N/nc-TiN NANOCOMPOSITE LAYER
WEAR TEST RESULTS FOR END MILLS
0.8
0.7
Uncoated mill
Flank wear (mm)
0.6
Coated mill 1
0.5
0.4
0.3
0.2
Coated mill 2
0.1
0.0
0
3
6
9
12
15
18
Time (min)
21
24
27
30
WEAR TEST RESULTS OF THE TURNING
CUTTERS ON BRONZE B11G21
No.
Surface treatment
Number of grooves made with
one cutter before re-
sharpening
1
No treatment; just standard cutter
2
Plasma nitriding
3
Plasma nitriding + nc-Ti2N/nc-TiN coating
1
3
12
CEMENTED CARBIDE INSERTS COATED WITH
nc-Ti2N/nc-TiN
WEAR TEST RESULTS FOR CEMENTED CARBIDE
INSERTS COATED WITH nc-Ti2N/nc-TiN
0.30
0.27
Flank wear (VB) [mm]
0.24
Uncoated WC insert
0.21
0.18
0.15
0.12
Coated WC insert
0.09
0.06
0.03
0.00
0
4
8
12
16
20
24
Cutting time [min.]
28
32
36
40