U.S. patent application number 13/922899 was filed with the patent office on 2013-12-12 for method for forming a protective coating against high-temperature oxidation on a refractory composite material based on silicon and niobium.
The applicant listed for this patent is ONERA (Office National d'Etudes et de Recherches Aerospatiales). Invention is credited to Marie-Pierre BACOS, Pierre JOSSO.
Application Number | 20130330540 13/922899 |
Document ID | / |
Family ID | 43587397 |
Filed Date | 2013-12-12 |
United States Patent
Application |
20130330540 |
Kind Code |
A1 |
BACOS; Marie-Pierre ; et
al. |
December 12, 2013 |
METHOD FOR FORMING A PROTECTIVE COATING AGAINST HIGH-TEMPERATURE
OXIDATION ON A REFRACTORY COMPOSITE MATERIAL BASED ON SILICON AND
NIOBIUM
Abstract
The invention relates to a method for forming a protective
coating against high-temperature oxidation on a surface of a
refractory composite material based on silicon and niobium, wherein
chromium present on the surface to be protected is reacted with a
reactive gas which contains silicon and oxygen in order to produce
a composite coating having two phases, a first phase of which is an
oxide phase based on silica which has viscoplastic properties and a
second phase of which is based on silicon, chromium and oxygen, and
wherein the first phase and second phase are coalesced at high
temperature, which allows a protective coating to be formed in
which the second phase acts as a reservoir to reform, during
operation, the first phase by means of reaction with an oxidising
gas. The invention is preferably used in the field of aeronautical
engines.
Inventors: |
BACOS; Marie-Pierre;
(Antony, FR) ; JOSSO; Pierre; (Erquy, FR) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
ONERA (Office National d'Etudes et de Recherches
Aerospatiales) |
Chatillon |
|
FR |
|
|
Family ID: |
43587397 |
Appl. No.: |
13/922899 |
Filed: |
June 20, 2013 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
13243364 |
Sep 23, 2011 |
|
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|
13922899 |
|
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Current U.S.
Class: |
428/336 ;
148/279; 205/220; 427/344; 427/580; 428/450 |
Current CPC
Class: |
C23C 10/02 20130101;
C23C 10/44 20130101; C30B 11/12 20130101; C23C 30/00 20130101; C23C
12/02 20130101; Y10T 428/265 20150115; F01D 25/005 20130101; C23C
10/08 20130101 |
Class at
Publication: |
428/336 ;
148/279; 427/344; 427/580; 428/450; 205/220 |
International
Class: |
F01D 25/00 20060101
F01D025/00; C23C 30/00 20060101 C23C030/00 |
Foreign Application Data
Date |
Code |
Application Number |
Sep 30, 2010 |
FR |
10/03882 |
Claims
1. A composite coating comprising a first phase and a second phase,
the first phase being an oxide phase and comprising silicon, the
second phase comprising silicon, chromium and oxygen, wherein the
first phase and the second phase are configured to coalesce at an
operating temperature in the presence of an oxidizing gas.
2. The composite coating according to claim 1, wherein the
operating temperature is 700.degree. C. or more.
3. The composite coating according to claim 1, wherein the first
phase further comprises at least one melting element selected from
a boron type melting element and a germanium type melting
element.
4. The composite coating according to claim 1, wherein the second
phase further comprises at least one element selected from boron,
aluminum, and iron.
5. The composite coating according to claim 1, wherein the second
phase is configured to reform the first phase by filling cracks
formed in the first phase, during operation.
6. A composite material comprising the composite coating according
to claim 1, coated thereon.
7. The composite material according to claim 6, wherein the
composite material comprises Nb and Si.
8. The composite material according to claim 7, further comprising
chromium.
9. A protective coating against high-temperature oxidation on a
surface of a composite material comprising silicon and niobium, the
protective coating obtainable by reacting chromium present on the
surface of the composite material with a reactive gas containing
silicon and oxygen, to produce a composite coating having two
phases, wherein: the first phase is an oxide phase and comprises
silicon, the second phase comprises silicon, chromium, and oxygen,
and the first phase and second phase are configured to coalesce at
a set temperature in the presence of an oxidizing gas.
10. The protective coating according to claim 9, wherein the
reactive gas comprises silicon monoxide (SiO) and is produced in
situ from a donor cement which comprises silica (SiO.sub.2) and is
subjected to a temperature greater than or equal to 1450.degree.
C.
11. The protective coating according to claim 10, wherein the donor
cement comprises silica (SiO.sub.2) and silicon carbide (SiC) in a
powder form.
12. The protective coating according to claim 9, wherein the first
phase further comprises at least one melting element selected from
a boron type melting element and a germanium type melting
element.
13. The protective coating according to claim 12, wherein the first
phase further comprises boron and wherein the reactive gas
comprises silicon monoxide (SiO) and boron monoxide (BO).
14. The protective coating according to claim 9, wherein the
reacting of chromium present on the surface of the composite
material with a reactive gas containing silicon and oxygen,
comprises: reacting a first reactive gas, the first reactive gas
comprising silicon monoxide (SiO) and being produced from a donor
cement which comprises silica (SiO.sub.2) and silicon carbide (SiC)
in powder form, and reacting a second reactive gas comprising
silicon monoxide (SiO) and boron monoxide (BO) produced from a
second donor cement which contains silica (SiO.sub.2) and boron
carbide (B.sub.4C) in powder form.
15. The protective coating according to claim 9, wherein all or
part of the chromium present on the surface of the composite
material is obtained by predepositing the chromium on the surface
of the composite material, the predepositing of the chromium
comprising forming a layer of chromium.
16. The protective coating according to claim 15, wherein the
predepositing comprises using an electrolytic depositing technique
or using cathode spraying, and wherein a thickness of the layer of
chromium is between 5 and 20 .mu.M.
17. The protective coating according to claim 16, wherein the
thickness of the layer of chromium is 15 .mu.M.
18. The protective coating according to claim 15, further
comprising one selected from: depositing tin on the surface of the
composite material before the predepositing of the chromium;
depositing a precious metal selected from platinum, palladium and
gold, on the surface of the composite material before the
predepositing of the chromium; and depositing titanium nitride on
the surface of the composite material before the predepositing of
the chromium.
19. The protective coating according to claim 18, wherein the
depositing of tin is followed by performing a thermal processing
operation at reduced pressure, and wherein the depositing of the
precious metal is followed by performing an interdiffusion
annealing operation.
20. A composite material comprising the protective coating
according to claim 9.
Description
[0001] The invention relates to a method for forming a protective
coating against high-temperature oxidation on a surface of a
refractory composite material based on silicon and niobium. It also
relates to components of composite material, in particular
aeronautical engine components, protected in this manner using this
method.
[0002] The mechanical strength and oxidation resistance of
materials used in turbines of aeronautical engines limit the
performance levels of the engines. Recent prospective studies show
that, for turbine blades, for which the wall temperature currently
reaches 1050-1100.degree. C., the optimisation of the compositions
of the metal alloys used (nickel-based superalloys) and the
production methods, the improvement of internal cooling circuits of
the components and the use of thermal insulation coatings will not
allow the intended wall temperatures in the order of 1300.degree.
C. to be reached. One method envisaged for operating at such
temperatures is the use of composite materials which are
constituted by two types of highly refractory phases, one of which
is metal Mss (in which Mss refers to a phase in solid solution and
M is an Nb base alloyed with numerous elements such as Si, Ti, Cr,
Hf, Al, etc.) conferring on the material adequate resistance at
ambient temperature, and the other of which is intermetallic
M.sub.5Si.sub.3 which provides the strength and creep resistance
desired at high temperature. These materials are referred to below
as "composite materials of the type Nb--Si". These are the
materials to which the invention relates.
[0003] The use of these composite materials of the type Nb--Si is
also envisaged at a medium temperature (700-1000.degree. C.) for
low-pressure turbines by replacing the blades currently in use,
which are cast from nickel-based superalloys and whose density
varies from 7.75 to 8.6. The use of these materials of the type
Nb--Si whose density varies between 6.6 and 7.2 allows the
structures to become lighter, which is an important strategic
factor for motorists, for example.
[0004] However, their development is slowed by their low level of
resistance to oxidation at medium or high temperature, in spite of
a large number of "favourable" elements which are added to their
initial composition (Hf, Si, Cr, B, C, Zr, Ti and Al). When such a
material is subjected to the operating conditions of gas turbines,
it is destroyed by oxidation in a time of between a few minutes and
some tens of hours, depending on the grade used.
[0005] It appears that generally above 800.degree. C. oxygen
penetrates into the metal phases in order to oxide them first,
initially leaving the silicide phases (M.sub.5Si.sub.3) virtually
non-attacked. It appears that the interfaces and the grain joints
assist the diffusion of oxygen. Then, the M.sub.5Si.sub.3 phases
become oxidised in turn.
[0006] Another problem is that, at low temperature, typically
between 500 and 800.degree. C., this type of material is incapable
of rapidly developing a layer of protective oxides owing to very
low diffusion kinetics in the metal phases Mss. This results in
preferential oxidation of the M.sub.5Si.sub.3 phases which form
crumbly non-protective oxides which brings about a destruction of
these phases and, gradually, of the material. This type of
oxidation is referred to as the "plague effect".
[0007] Solutions for protecting this family of alloys have already
been proposed. For example, in the U.S. Pat. No. 4,904,546 (M. R.
Jackson, 27 Feb. 1990), there is proposed a protection based on
ruthenium by means of physical deposition, of the plasma projection
type, corresponding to the formula:
(RU.sub.from (19-x) to (34-x)(.SIGMA.Fe+Ni+Co).sub.xAl.sub.from 22
to 28Cr.sub.from (5.6-y) to (44-y)Fe.sub.y
with the preferred composition:
Cr.sub.55Al.sub.20Ru.sub.14Fe.sub.11.
[0008] U.S. Pat. No. 4,980,244 by the same Applicant teaches a
variant of this coating in which yttrium is added at a level of 0.2
atomic % in place of ruthenium. In addition to the difficulty of
applying such a coating, it should be noted that the increasing
scarcity of resources means that the selection of ruthenium is not
tenable.
[0009] In another U.S. Pat. No. 5,019,334, M. R. Jackson proposes
using a compound MCrAlY (where M=Ni, Co and/or Fe) as a protective
coating for these alloys and accommodating the thermal expansion
differential by adding alumina to the coating. Optionally, use of
the alloys RuCrAl described above is suggested.
[0010] Another solution, proposed by M. R. Jackson et al. in U.S.
Pat. No. 5,932,033 involves increasing the intrinsic resistance of
the material to oxidation at high temperature owing to an increase
in its content of chromium. Consequently, new additional phases,
that is to say, the Laves phases, which are resistant to oxidation,
of composition Cr.sub.2M (where M=Nb+Ti+Hf) are created in this
composite. The material described in this manner can be used in its
existing state or as a coating. Another version of this material is
taught in the U.S. Pat. No. 6,419,765. These two materials are
supposed to function without a coating for at least 100 hours at a
temperature of between 1400 and 1600.degree. F. (745 and
856.degree. C.) However, Laves phases are well known for being very
brittle.
[0011] U.S. Pat. No. 6,521,356 (Zhao et al.) teaches that it is
possible to protect this type of material with a coating based on
niobium, silicon, titanium and chromium, this coating being
compatible with the addition of a thermal barrier. This coating
contains numerous elements and is deposited by means of a
dispersion (slurry): the component to be coated is immersed in a
dispersion of powders in a viscous organic binding agent. The
preferred composition contains 66% of silicon, 10% of titanium, 5%
of chromium and 19% of niobium (atomic %). This composition
complies with the more general following formula:
Nb.sub.1-x-yTi.sub.xCr.sub.ySi.sub.2 where 1>(x+y).gtoreq.0.
However, this phase is brittle and may generate cracks at the
interface. It is possible to find in the composition of this
protection elements such as boron, tin and iron as long as their
concentration does not exceed 5 atomic %. Finally, it should be
noted that this protection may be complemented by the deposit of a
conventional thermal barrier which is composed either of zirconium,
zirconium stabilised by yttrium, zirconium (zirconium silicate,
ZrSiO.sub.4) and/or mullite.
[0012] All the coatings created by the various techniques of
protection by means of physical deposition, plasma deposition etc.,
do not allow the composite material of the type Nb--Si to be
protected for the applications intended since the coating has a
thermal expansion coefficient which is different from that of the
material and any cracking brings about catastrophic oxidation of
the composite material of the Nb--Si type. It should be noted that
this material is destroyed after 1 cycle of one hour under air at
1200.degree. C. and 2 cycles of one hour under air at 1000.degree.
C.
[0013] According to Guo, X. P., Zhao, L. X., Guan, P., Kusabiraki,
K. 2007 Materials Science Forum 561-565 (PART 1), pp. 371-374, it
is possible to protect this type of material with a silicon based
coating which is deposited by means of pack cementation, but with a
halogenated activator, of the ammonium halide type, which when
decomposing forms a gaseous halogenated acid. Xiaoxia Li and
Chingen Zhou, 2007 Materials Science Forum 546-549 (PART 3), pp.
1721-1724, have applied siliconisation by means of pack cementation
using a halogenated activator to a niobium silicide alloy coated
with an MCrAlY deposited by means of plasma projection under air,
the coating obtained only by means of siliconisation not being
sufficiently protective.
[0014] Chen Chen et al. in Intermetallics, 15 (2007) 805-809 also
propose protecting a material of the type Nb--Si with a coating of
silicon also comprising chromium. The chromium is deposited by
means of pack cementation based on chromium powder and a
halogenated activator, of the ammonium halide type, which forms a
gaseous halogenated acid when decomposing. The silicon is deposited
either by means of pack cementation based on silicon powders and a
halogenated activator, or by molten salts.
[0015] Still using methods of pack cementation with a halogenated
activator, Tian et al. propose a coating based on silicon and
comprising either aluminium (Surface and Coating Technology, 203
(2009) 1161-1166) or yttrium (Surface and Coating Technology, 204
(2009) 313-318).
[0016] However, these techniques using halogenated activators form,
with the components of the niobium silicides, halogenated compounds
which are volatile, which locally degrades the microstructure. It
is therefore necessary to develop a technique which allows a
coating to be created by means of diffusion without using
halogenated gas.
[0017] Furthermore, the description of all of these techniques for
protection of materials of the type Nb--Si shows that effective
protection of niobium silicon alloys is very difficult to obtain,
both at the temperature referred to as "plague corrosion"
temperature and at high temperature. In order to avoid this "plague
effect", the silicide must be isolated from the atmosphere.
[0018] An object of the invention is in particular to overcome all
these disadvantages.
[0019] The work carried out by the Applicant has shown that the
protection of a silicide at high temperature cannot be ensured only
by a refractory and adhesive coating which is sealed or which slows
the diffusion of oxygen. This coating must further have good
viscoplastic properties in order to be able to fill the cracks
during operation and to be self-healing in the event of the oxide
becoming flaked or volatile.
[0020] The invention proposes to this end a method for forming a
protective coating against high-temperature oxidation on a surface
of a refractory composite material based on silicon and niobium, in
which chromium present on the surface to be protected is reacted
with a reactive gas which contains silicon and oxygen in order to
produce a composite coating having two phases, a first phase of
which is an oxide phase based on silica which has viscoplastic
properties and a second phase of which is based on silicon,
chromium and oxygen, and in which the first phase and second phase
are coalesced at high temperature, which allows a protective
coating to be formed in which the second phase acts as a reservoir
to reform, during operation, the first phase by means of reaction
with an oxidising gas.
[0021] In this manner, in order to protect that composite material
of the type Nb--Si, the method of the invention allows a composite
coating to be created which is constituted by two phases with
different expansion coefficients in order to accommodate the
thermomechanical constraints during operation.
[0022] The first phase is constituted by an oxide phase based on
silica, which is protective and viscoplastic at the temperature for
use. It may further contain melting elements of the boron and/or
germanium type in order to adjust its viscoplastic properties in
accordance with the desired temperature range.
[0023] The second phase substantially contains silicon, chromium
and oxygen. It may also contain other elements, for example, boron
and/or aluminium and/or iron. This second phase will act as a
reservoir in order to reform, during operation, the first phase by
means of reaction with oxygen or any other oxidising gas, for
example, water vapour.
[0024] In this manner, when a component of composite material of
the Nb--Si type, provided with a coating according to the
invention, is subjected to a gaseous oxidising atmosphere at high
temperature, the second phase will allow the first phase to be
reformed.
[0025] The technique currently preferred in order to allow all of
these "elements" to be obtained is a technique derived from the
technique referred to as "VLS" (Vapour Liquid Solid). This "VLS"
technique may be combined in this instance with a pre-deposit metal
phase if the element (typically chromium) is not present in
sufficient quantity in the composite material of the type
Nb--Si.
[0026] An object of the invention is therefore to develop a
technique which is suitable for this type of composite Nb--Si
material and which allows the formation of a coating which is also
composite based on silica/silicon, chromium, oxygen doped and/or
modified with a melting element, such as boron and/or
germanium.
[0027] The basic notion is to react the chromium element, either
from the composition of the alloy or added beforehand, with gases
containing silicon, oxygen and optionally other elements, such as
boron, germanium, etc. The techniques for adding chromium may be of
the wet type (electrolytic coating, molten salts, for example) or
physical (cathode spraying, PVD, magnetron, for example), or any
other chromium depositing technique which is well known to the
person skilled in the art. The gases which supply the silicon, the
oxygen and any other element of the type B, Ge, etc., are produced
in situ in the reactor from standard commercial powders.
[0028] Other complementary features of the invention are set out
below: [0029] The first phase is based on silica (SiO.sub.2) and
the second phase based on silicon, chromium and oxygen (CrSiO);
[0030] the reactive gas contains silicon monoxide (SiO) and is
produced in situ, for example, from a donor cement which contains
silica (SiO.sub.2) subjected to a temperature greater than or equal
to 1450.degree. C.; the silicon monoxide may be obtained by
activating a mixture of silicon powder and silica; [0031] the donor
cement contains, for example, a mixture of silica (SiO.sub.2) and
silicon carbide (SiC) in the form of powder; this cement may be
replaced with a powdered SiO whose evaporation temperature is
between 1100 and 1400.degree. C.; [0032] the first phase further
contains melting elements of the boron and/or germanium type, which
allows the viscoplastic properties of this phase to be adjusted in
accordance with the operating temperature range; [0033] the first
phase further contains boron and the reactive gas contains silicon
monoxide (SiO) and boron monoxide (BO); [0034] there is first
reacted on the composite material a first reactive gas containing
silicon monoxide (SiO) produced from the donor cement which
contains a mixture of silica (SiO.sub.2) and silicon carbide (SiC)
in the form of powder, then a second reactive gas which contains
silicon monoxide (SiO) and boron monoxide (BO) produced from a
second donor cement which contains a mixture of silica (SiO.sub.2)
and boron carbide (B.sub.4C) in the form of powder; [0035] the
chromium present on the surface to be protected is completely or
partially a component of the composite material based on silicon
and niobium; [0036] the chromium present on the surface to be
protected is obtained completely or partially by means of a
predeposit on the surface to be protected in order to form a layer
of the desired thickness; [0037] the thickness of the chromium
layer is between 5 and 20 .mu.m, the preferred thickness being 15
.mu.m; [0038] the predeposit of chromium is obtained by means of a
depositing technique selected from the following group:
electrolytic depositing, depositing by means of cathode spraying;
[0039] there is formed beforehand on the surface to be protected a
deposit of tin, preferably followed by a thermal processing
operation at reduced pressure; [0040] there is formed beforehand on
the surface to be protected a deposit of a precious metal which is
selected from platinum, palladium and gold, preferably followed by
an interdiffusion annealing operation; [0041] there is formed
beforehand on the surface to be protected a deposit of titanium
nitride; and [0042] the composite material based on silicon and
niobium has the general composition Nb 47%, Si 16%, Ti 25%, Al 2%,
Cr 2% and Hf 8% (atomic %).
[0043] Another aspect of the invention relates to the coating
itself obtained by implementing the method above and a component of
composite material based on silicon and niobium, one surface of
which is provided with a protective coating, such as that obtained
by implementing the method above.
[0044] In the following detailed description, given purely by way
of example, reference is made to the appended drawings, in
which:
[0045] FIG. 1 is a graph illustrating the formation of a protective
coating according to the invention as a function of time;
[0046] FIG. 2 is a surface view, drawn to an enlarged scale, of a
composite material of the Nb--Si type protected by a deposit of
chromium followed by a processing operation using an SiO gas;
[0047] FIG. 3 is a corresponding micrographic sectioned view, drawn
to an enlarged scale, of the composite material of FIG. 2; and
[0048] FIG. 4 is a surface view, drawn to an enlarged scale, of a
composite material of the Nb--Si type protected by a deposit of
chromium followed by a processing operation using the SiO gas and a
processing operation using the SiO/BO gas.
[0049] Reference is first made to the graph of FIG. 1. As mentioned
above, the technique currently preferred for producing a protective
deposit according to the invention is derived from the technique
known as "VLS". It should be noted that this technique involves
placing a material in a chamber containing a specific gas. Liquid
drops are formed, either from a reaction between the gas and
"elements or impurities" of the material, or from a reaction
between the gas and a generally nanometric predeposit.
[0050] By means of catalytic effect, the gas is adsorbed in the
droplet and, when there is oversaturation of the gas in the
droplet, a nucleation is produced and a growth of an equiaxed
crystal.
[0051] This technique is used currently in various technical fields
in order to form nanowires, whiskers, nanostructures of
semi-conductors, etc., for electronics or catalysts.
[0052] In the case of FIG. 1, a pre-deposit of chromium is formed
on a surface of a composite material 1 of the type Nb--Si with a
thickness of 15-20 .mu.m and the whole is placed in a chamber where
SiO gas is produced in situ.
[0053] "Droplets" or bubbles 2 of CrSiO are formed in which the SiO
is adsorbed. When the composition Cr.sub.40Si.sub.35O.sub.25 is
obtained, there is nucleation of SiO.sub.2 which grows in the form
of rods 3. At the testing temperature (1450.degree. C.), the silica
is plastic and there is therefore coalescence of the phases and
collapse of the bubbles of CrSiO which coalesce. The rod/bubble
structure typical of a VLS growth is found only at the surface.
Part of the chromium has also diffused in the subjacent composite
material based on Nb--Si and has therefore ensured the anchoring of
the coating (diffusion zone).
[0054] FIG. 1 illustrates from left to right the formation of the
droplet or bubble 2 of CrSiO by reacting SiO gas on the surface of
a sample in the presence of chromium, then the formation of rods 3
during the VLS growth phase, in accordance with the duration. This
phase is followed by a lateral growth phase of SiO.sub.2 as seen in
the right-hand portion of FIG. 1.
[0055] In the specific case of FIG. 1, chromium is supplied by
means of a predepositing operation. However, in a variant, it could
also be supplied directly from the alloy, of which it forms one of
the components. It is also possible to supply the chromium both
from a component of the alloy and from a predeposit on the surface
to be protected.
[0056] FIG. 2 illustrates a surface view, drawn to an enlarged
scale (enlargement factor .times.2000 with scale 10 .mu.m
illustrated), where the typical rod/bubble structure of a VLS
growth can be seen. However, this structure is found only at the
surface.
[0057] The section of FIG. 3 (enlargement factor .times.1000 with
scale 20 .mu.m illustrated) shows that the composite material 1 is
found to be surmounted by an anchoring zone 4 and then surmounted
by the coating with the phases SiO.sub.2 and CrSiO which have
coalesced together.
[0058] The SiO gas is produced in situ in an oven from an admixture
SiO.sub.2/SiC well known for making this gas. It cannot be obtained
below 1450.degree. C. It is used in the protection of carbon-carbon
composites in order to convert the carbon into silicon carbide in
accordance with the formula 2C+SiO=SiC+CO.
[0059] This gas has never been produced in order to be included in
a coating by a growth of the VLS type.
[0060] It is also possible to incorporate boron. To this end, the
powder mixture has been modified by a new mixture
SiO.sub.2/B.sub.4C which has never been used before.
[0061] When there is deposited on a composite material of the
Nb--Si type a deposit of chromium and it is placed in a chamber
where SiO gas is produced from SiO/SiC, then in a chamber where
SiO/BO gas is created from a powder SiO.sub.2/B.sub.4C, boron is
incorporated, which allows a borosilicate glass to be obtained at
the surface which is more plastic than silica. An example is given
by the micrography of FIG. 4 (enlargement factor .times.1000 with
scale 200 .mu.m illustrated). This shows a composite material of
the type Nb--Si first protected by a predeposit of chromium
followed by a processing operation using SiO gas and a processing
operation using SiO/BO gas. The appearance of the coating is more
glazed at the surface compared with FIG. 2.
[0062] The invention will be further described with reference to
the following non-limiting examples:
EXAMPLE 1
[0063] A protective coating is constructed on an alloy of niobium
and silicon referred to as MASC (Metal And Silicide Composite)
having the general composition Nb 47%, Si 16%, Ti 25%, Al 2%, Cr 2%
and Hf 8% (atomic %). This alloy was developed by General Electric
(B. P. Bewlay, M. R. Jackson, and H. A. Lipsitt "The Balance of
Mechanical and Environmental Properties of a Multielement
Niobium-Niobium Silicide-Based In Situ Composite", Metall. Mater.
Trans. 27A (1996) 3801-3808; U.S. Pat. No. 5,833,773). It is
composed of a plurality of refractory phases, a metal one (rich
solid solution based on niobium designated M.sub.ss) and a
plurality of niobium silicide phases (of the type Nb.sub.3Si and
Nb.sub.5Si.sub.3).
[0064] The sample is placed in or above a silicon donor cement
having the composition:
TABLE-US-00001 SiO.sub.2 75% SiC 25% (percentages by mass)
[0065] These percentages correspond to the stoichiometric
composition.
[0066] Once brought to the temperature of 1450.degree. C. under a
flow of argon, this cement allows silicon to be transported to the
surface of the substrate. Following this operation, a coating is
obtained based on SiO.sub.2+CrSiO whose properties of oxidation at
high temperature are exceptional.
[0067] At 1200.degree. C. under air with cyclical oxidation, the
service-life of the MASC alloy protected in this manner is 16 times
greater than that of the same non-protected alloy.
EXAMPLE 2
[0068] A protective coating is constructed on an alloy of niobium
and silicon referred to as MASC (Metal And Silicide Composite) as
described in example 1.
[0069] To this end, the substrate is first coated with a deposit of
electrolytic chromium produced under the following conditions:
Chromium trioxide referred to as chromic acid (CrO.sub.2): 250
gL.sup.-1 Sulphuric acid (H.sub.2SO.sub.4): 2.5 gL.sup.-1 Current
density: 50 A/dm.sup.2
T: 60-65.degree. C.
[0070] The electrolysis lasts between 0.5 and 3 hours, depending on
the thickness desired. A layer of between 5 and 20 .mu.m is
deposited, the preferred thickness being 15 .mu.m.
[0071] Optionally, the substrate coated with chromium may then be
subjected to a thermal diffusion processing operation, for example,
of 2 hours at 900.degree. C. at reduced pressure greater than
10.sup.-3 Pa. Following this operation, the sample is placed in or
above a silicon donor cement having the composition
TABLE-US-00002 SiO.sub.2 75% SiC 25% (percentages by mass)
[0072] Once brought to the temperature of 1450.degree. C. under a
flow of argon, this cement allows silicon to be transported to the
surface of the substrate. Following this operation, a coating is
obtained based on SiO.sub.2+CrSiO whose properties of oxidation at
high temperature are exceptional. The sample has a mass gain of 1
mg/cm.sup.2 after 45 cycles of oxidation of one hour at
1200.degree. C., whilst a non-protected sample is destroyed in less
than one hour.
EXAMPLE 3
[0073] A protective coating is constructed on an alloy of niobium
and silicon referred to as MASC (Metal And Silicide Composite) as
described in example 1.
[0074] To this end, the substrate is first coated with a deposit of
chromium by means of triode cathode spraying. The deposited layer
has a thickness of between 5 and 20 .mu.m, the preferred thickness
being 15 .mu.m. The sample is placed in or above a silicon donor
cement having the composition:
TABLE-US-00003 SiO.sub.2 75% SiC 25% (percentages by mass)
[0075] Once brought to the temperature of 1450.degree. C. under a
flow of argon, this cement allows silicon to be transported to the
surface of the substrate. Following this operation, a coating is
obtained based on SiO.sub.2+CrSiO whose properties of oxidation at
high temperature are exceptional.
[0076] By way of example, a sample protected with this coating was
oxidised for 45 cycles of one hour at a temperature of 1200.degree.
C. Following the test, it had a mass loss of 1.63 mg/cm.sup.2
whilst the same non-protected sample is completely destroyed in
less than one hour.
EXAMPLE 4
[0077] The procedure is as in the example above, apart from the
fact that the cement is a donor of both silicon and boron. The
cement has the following composition:
TABLE-US-00004 SiO.sub.2 50% B.sub.4C 50% (percentages by mass)
[0078] Also in this instance, the results obtained are exceptional:
the substrate MASC is coated with a deposit of silicon dioxide,
chromium oxide, chromium boride and chromium oxysilicide whose
properties of oxidation at high temperature are exceptional.
[0079] For example, the sample oxidised for 20 cycles of one hour
at 1000.degree. C. had a mass loss of 0.14 mg/cm.sup.2 whilst the
same non-protected sample is completely destroyed at the same
temperature in one hour.
EXAMPLE 5
[0080] The procedure is as in the example above, apart from the
fact that the cement which is a donor of both silicon and boron is
richer in boron than in the preceding case. The cement has the
following composition:
TABLE-US-00005 SiO.sub.2 16% B.sub.4C 84% (percentages by mass)
[0081] In this instance also, the coating obtained has exceptional
resistance to oxidation at high temperature.
EXAMPLE 6
[0082] The procedure is as in Example 3, then a second processing
operation is carried out in which the sample is placed in or above
a cement which donates both silicon and boron. The second cement
has the following composition:
TABLE-US-00006 SiO.sub.2 50% B.sub.4C 50% (percentages by mass)
[0083] The sample is subjected to an oxidation test of 50 cycles of
one hour at 1000.degree. C. Following this test, it has a mass gain
of 0.74 mg/cm.sup.2 whilst the same non-protected sample is
completely destroyed at this temperature in one hour.
EXAMPLE 7
[0084] The procedure is as in Example 3, then a second processing
operation is carried out in which the sample is placed in or above
a cement which donates both silicon and boron but is richer in
boron than that of example 6. The second cement has the following
composition:
TABLE-US-00007 SiO.sub.2 16% B.sub.4C 84% (percentages by mass)
[0085] The sample is subjected to an oxidation test of 300 cycles
of one hour at 1000.degree. C. Following this test, it has a mass
loss of 1.09 mg/cm.sup.2 whilst the same non-protected sample is
completely destroyed at this temperature in one hour.
[0086] However, it should be noted that, in the event of total
destruction of the coating, by means of accidental cracking, for
example, and taking into account the low level of resistance to
oxidation of materials of the Nb--Si type, there is oxidation of
the subjacent substrate which brings about flaking of the coating
and the destruction of the material.
[0087] In order to overcome this, it has been proposed, before
producing the coating as described above, that the surface of the
alloy which will be in contact with the coating be modified locally
either by an element which is known to improve the oxidation
resistance of solid substrates such as tin or a precious metal
(platinum, gold) [Geng et al Intermetallics 15 (2007) 270-281] or
by depositing an oxygen diffusion barrier such as, for example,
titanium nitride whose properties as a diffusion barrier are well
known to the person skilled in the art.
EXAMPLE 8
[0088] A protective coating is constructed on an alloy of niobium
and silicon referred to as MASC. To this end, the substrate is
first coated with a deposit of tin of from 4 to 7 .mu.m followed by
a thermal processing operation at reduced pressure at 700.degree.
C. for a duration of from 12 to 32 hours. Then, the procedure is as
in example 1.
[0089] In this instance also, the results obtained are exceptional:
the MASC substrate is coated by a deposit whose oxidation
properties at high temperature are exceptional.
EXAMPLE 9
[0090] A protective coating is constructed on an alloy of niobium
and silicon referred to as MASC. To this end, the substrate is
first coated with a deposit of tin of from 4 to 7 .mu.m followed by
a thermal processing operation at reduced pressure at 700.degree.
C. for a duration of from 12 to 32 hours. Then, the procedure is as
in example 2.
[0091] In this instance also, the results obtained are exceptional:
the MASC substrate is coated by a deposit whose oxidation
properties at high temperature are exceptional.
EXAMPLE 10
[0092] A protective coating is constructed on an alloy of niobium
and silicon referred to as MASC. To this end, the substrate is
first coated with a deposit of tin of from 4 to 7 .mu.m followed by
a thermal processing operation at reduced pressure at 700.degree.
C. for a duration of from 12 to 32 hours. Then, the procedure is as
in examples 3 to 7 in accordance with the properties desired for
the coating.
[0093] In this instance also, the results obtained are exceptional:
the MASC substrate is coated by a deposit whose oxidation
properties at high temperature are exceptional.
EXAMPLE 11
[0094] Examples 8 to 10 are repeated, with the deposit of tin being
replaced by a deposit of platinum obtained using one of the
techniques well known to the person skilled in the art, optionally
followed by an interdiffusion annealing operation.
[0095] In all cases, a coating is obtained with good oxidation
properties at high and medium temperature.
EXAMPLE 12
[0096] Examples 8 to 10 are repeated, with the deposit of tin being
replaced by a deposit of palladium obtained using one of the
techniques well known to the person skilled in the art, optionally
followed by an interdiffusion annealing operation.
[0097] In all cases, a coating is obtained with good oxidation
properties at high and medium temperature.
EXAMPLE 13
[0098] Examples 8 to 10 are repeated, with the deposit of tin being
replaced by a deposit of gold obtained using one of the techniques
well known to the person skilled in the art, optionally followed by
an interdiffusion annealing operation.
[0099] In all cases, a coating is obtained with good oxidation
properties at high and medium temperature.
EXAMPLE 14
[0100] Examples 8 to 10 are repeated, with the deposit of tin being
replaced by a deposit of titanium nitride obtained using one of the
techniques well known to the person skilled in the art.
[0101] In all cases, a coating is obtained with good oxidation
properties at high and medium temperature.
EXAMPLE 15
[0102] The above examples 1, 2, 3, 6 to 14 are repeated with the
SiO.sub.2/SiC cement (silica/silicon carbide) being replaced with a
commercial SiO powder which by heating evaporates into SiO gas as
mentioned in the U.S. Pat. No. 6,313,015.
EXAMPLE 16
[0103] The above examples 1, 2, 3, 6 to 14 are repeated with the
only difference that the source of silicon monoxide gas (SiO) is
obtained by activation of the mixture of powders of silicon (Si)
and silica (SiO.sub.2), which activation is carried out by means of
thermal processing, laser heating, magnetron or triode cathode
plasma, as mentioned in the U.S. Pat. No. 6,313,015. Also in this
instance, the coating obtained has exceptional resistance to
oxidation at high temperature. The same result can be obtained by
means of activation of targets obtained by means of compacting the
powders mentioned or from targets which are cut from solid material
of the same composition as the powders mentioned.
[0104] The invention is preferably used in the field of
aeronautical engines.
* * * * *