U.S. patent application number 16/379157 was filed with the patent office on 2019-08-01 for silicon-based materials containing indium and methods of forming the same.
The applicant listed for this patent is General Electric Company. Invention is credited to Glen Harold Kirby, Julin Wan.
Application Number | 20190233344 16/379157 |
Document ID | / |
Family ID | 61617872 |
Filed Date | 2019-08-01 |
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United States Patent
Application |
20190233344 |
Kind Code |
A1 |
Kirby; Glen Harold ; et
al. |
August 1, 2019 |
Silicon-Based Materials Containing Indium and Methods of Forming
the Same
Abstract
A ceramic component is generally provided that includes a
silicon-based layer comprising a silicon-containing material (e.g.,
a silicon metal and/or a silicide) and about 0.001% to about 85% of
an In-containing compound. For example, the silicon-based layer can
be a bond coating directly on the surface of the substrate.
Alternatively or additionally, the silicon-based layer can be an
outer layer defining a surface of the substrate, with an
environmental barrier coating on the surface of the substrate. Gas
turbine engines are also generally provided that include such a
ceramic component.
Inventors: |
Kirby; Glen Harold; (Liberty
Township, OH) ; Wan; Julin; (Rexford, NY) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Family ID: |
61617872 |
Appl. No.: |
16/379157 |
Filed: |
April 9, 2019 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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15919335 |
Mar 13, 2018 |
10301224 |
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16379157 |
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15267370 |
Sep 16, 2016 |
9944563 |
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15919335 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F01D 25/08 20130101;
F05D 2240/35 20130101; C04B 41/89 20130101; F05D 2300/222 20130101;
C04B 41/87 20130101; C04B 41/52 20130101; F05D 2300/611 20130101;
F05D 2300/6033 20130101; F01D 5/288 20130101; F01D 9/02 20130101;
F01D 5/282 20130101; Y02T 50/60 20130101; C04B 41/009 20130101;
F05D 2220/32 20130101; C04B 41/009 20130101; C04B 35/565 20130101;
C04B 35/806 20130101; C04B 41/009 20130101; C04B 35/584 20130101;
C04B 35/806 20130101; C04B 41/009 20130101; C04B 35/10 20130101;
C04B 35/803 20130101; C04B 41/009 20130101; C04B 35/14 20130101;
C04B 35/803 20130101; C04B 41/009 20130101; C04B 35/18 20130101;
C04B 35/803 20130101; C04B 41/52 20130101; C04B 41/5027 20130101;
C04B 41/5096 20130101; C04B 41/52 20130101; C04B 41/5027 20130101;
C04B 41/5071 20130101; C04B 41/522 20130101; C04B 41/52 20130101;
C04B 41/4558 20130101; C04B 41/5022 20130101; C04B 41/52 20130101;
C04B 41/5024 20130101; C04B 41/52 20130101; C04B 41/5042 20130101;
C04B 41/522 20130101 |
International
Class: |
C04B 41/87 20060101
C04B041/87; F01D 5/28 20060101 F01D005/28; F01D 9/02 20060101
F01D009/02; F01D 25/08 20060101 F01D025/08; C04B 41/00 20060101
C04B041/00; C04B 41/52 20060101 C04B041/52; C04B 41/89 20060101
C04B041/89 |
Claims
1. A ceramic component comprising: a silicon-based layer comprising
a silicon-containing material and about 0.001% to about 85% of an
In-containing compound.
2. The ceramic component as in claim 1, comprising: a substrate
defining a surface, wherein the silicon-based layer is a bond
coating directly on the surface of the substrate.
3. The ceramic component as in claim 2, wherein the
silicon-containing material is silicon metal.
4. The ceramic component as in claim 3, wherein a thermally grown
oxide is on the bond coating, and wherein the thermally grown oxide
layer remains amorphous up to an operating temperature of about
1415.degree. C. or less.
5. The ceramic component as in claim 2, wherein the
silicon-containing material comprises a silicide.
6. The ceramic component as in claim 5, wherein a thermally grown
oxide is on the bond coating, and wherein the thermally grown oxide
layer remains amorphous up to an operating temperature of about
1485.degree. C. or less.
7. The ceramic component as in claim 5, wherein the silicide
comprises molybdenum silicide, rhenium silicide, a rare earth
silicide, or a mixture thereof.
8. The ceramic component as in claim 1, wherein the ceramic
component comprising: a substrate, wherein the silicon-based layer
is an outer layer defining a surface of the substrate; and an
environmental barrier coating on the surface of the substrate.
9. The ceramic component as in claim 8, wherein the substrate
comprises the outer layer on a plurality of CMC plies, and wherein
the outer layer comprises silicon carbide.
10. The ceramic component as in claim 1, wherein the In-containing
compound comprises a compound having a formula:
Ln.sub.2-x-yGa.sub.xIn.sub.ySi.sub.2O.sub.7 where Ln is Sc, Y, La,
Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, or a
mixture thereof; x is 0 to about 1; and y is greater than 0 to
about 1.
11. The ceramic component as in claim 1, wherein the In-containing
compound comprises a compound having a formula:
Ln.sub.2-x-yGa.sub.xIn.sub.ySi.sub.2O.sub.5 where Ln is Sc, Y, La,
Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, or a
mixture thereof; x is 0 to about 1; and y is greater than 0 to
about 1.
12. The ceramic component as in claim 1, wherein the In-containing
compound comprises a compound having a formula:
Ln.sub.3In.sub.5-xM.sub.xO.sub.12 where Ln is Sc, Y, La, Ce, Pr,
Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, or a mixture
thereof, and M is Ga with 0.ltoreq.x<5, Al with 0.ltoreq.x<5,
Fe with 0.ltoreq.x<5, B with 0.ltoreq.x.ltoreq.2.5, or a
combination thereof.
13. The ceramic component as in claim 12, where x is 0.1 to about
2.
14. The ceramic component as in claim 12, where M is B; and x is
0.1 to about 2.
15. The ceramic component as in claim 1, wherein the In-containing
compound comprises InN.
16. A gas turbine engine comprising the ceramic component of claim
1.
Description
CROSS-REFERENCE TO RELATED APPLICATION
[0001] The application claims priority to and is a divisional of
U.S. application Ser. No. 15/919,335 filed on Mar. 13, 2018, and
claims priority to and is a divisional of U.S. application Ser. No.
15/267,370 filed on Sep. 16, 2016, both of which are hereby
incorporated herein by reference in its entirety.
FIELD OF THE INFORMATION
[0002] The present invention generally relates to including indium
(In) compounds within a silicone based coating. In particular,
silicon-based coatings (e.g., silicon bond coatings) that include
In are generally provided for use in environmental barrier coatings
for ceramic components.
BACKGROUND OF THE INVENTION
[0003] Higher operating temperatures for gas turbine engines are
continuously being sought in order to improve their efficiency.
However, as operating temperatures increase, the high temperature
durability of the components of the engine must correspondingly
increase. Significant advances in high temperature capabilities
have been achieved through the formulation of iron, nickel, and
cobalt-based superalloys. Still, with many hot gas path components
constructed from super alloys, thermal barrier coatings (TBCs) can
be utilized to insulate the components and can sustain an
appreciable temperature difference between the load-bearing alloys
and the coating surface, thus limiting the thermal exposure of the
structural component.
[0004] While superalloys have found wide use for components used
throughout gas turbine engines, and especially in the higher
temperature sections, alternative lighter-weight substrate
materials have been proposed, such as ceramic matrix composite
(CMC) materials. CMC and monolithic ceramic components can be
coated with environmental barrier coatings (EBCs) to protect them
from the harsh environment of high temperature engine sections.
EBCs can provide a dense, hermetic seal against the corrosive gases
in the hot combustion environment.
[0005] Silicon carbide and silicon nitride ceramics undergo
oxidation in dry, high temperature environments. This oxidation
produces a passive, silicon oxide scale on the surface of the
material. In moist, high temperature environments containing water
vapor, such as a turbine engine, both oxidation and recession
occurs due to the formation of a passive silicon oxide scale and
subsequent conversion of the silicon oxide to gaseous silicon
hydroxide. To prevent recession in moist, high temperature
environments, environmental barrier coatings (EBC's) are deposited
onto silicon carbide and silicon nitride materials.
[0006] Currently, EBC materials are made out of rare earth silicate
compounds. These materials seal out water vapor, preventing it from
reaching the silicon oxide scale on the silicon carbide or silicon
nitride surface, thereby preventing recession. Such materials
cannot prevent oxygen penetration, however, which results in
oxidation of the underlying substrate. Oxidation of the substrate
yields a passive silicon oxide scale, along with the release of
carbonaceous or nitrous oxide gas. The carbonaceous (i.e., CO,
CO.sub.2) or nitrous (i.e., NO, NO.sub.2, etc.) oxide gases cannot
escape out through the dense EBC and thus, blisters form. The use
of a silicon bond coat has been the solution to this blistering
problem to date. The silicon bond coat provides a layer that
oxidizes (forming a passive silicon oxide layer beneath the EBC)
without liberating a gaseous by-product.
[0007] However, the presence of a silicon bond coat limits the
upper temperature of operation for the EBC because the melting
point of silicon metal is relatively low. In use, a thermally grown
oxide (TGO) layer of silicon oxide forms on the top surface of the
silicon metal bond coat of a multilayer EBC system. This silicon
oxide scale remains amorphous at temperatures of 1200.degree. C. or
lower, sometimes even at temperatures of 1315.degree. C. or lower,
although this property is also dependent on the time the bond coat
is exposed to this temperature. At higher temperatures, or when
minor amounts of steam penetrate through the EBC to the bond coat,
the silicon oxide scale crystallizes (e.g., into cristoblate),
which undergoes phase transition accompanied by large volume change
on cooling. The volume change leads to EBC coating spall.
[0008] As such, it is desirable to improve the properties of a
silicon bond coat in the EBC to achieve a higher operational
temperature limit for the EBC.
BRIEF DESCRIPTION OF THE INVENTION
[0009] Aspects and advantages of the invention will be set forth in
part in the following description, or may be obvious from the
description, or may be learned through practice of the
invention.
[0010] A ceramic component is generally provided that includes a
silicon-based layer comprising a silicon-containing material (e.g.,
a silicon metal and/or a silicide) and about 0.001% to about 85% of
an In-containing compound. For example, the silicon-based layer can
be a bond coating directly on the surface of the substrate.
Alternatively or additionally, the silicon-based layer can be an
outer layer defining a surface of the substrate, with an
environmental barrier coating on the surface of the substrate. Gas
turbine engines are also generally provided that include such a
ceramic component.
[0011] These and other features, aspects and advantages of the
present invention will become better understood with reference to
the following description and appended claims. The accompanying
drawings, which are incorporated in and constitute a part of this
specification, illustrate embodiments of the invention and,
together with the description, serve to explain the principles of
the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] A full and enabling disclosure of the present invention,
including the best mode thereof, directed to one of ordinary skill
in the art, is set forth in the specification, which makes
reference to the appended Figs., in which:
[0013] FIG. 1 is a cross-sectional side view of an exemplary
ceramic component including a silicon-based layer;
[0014] FIG. 2 is a cross-sectional side view of the exemplary
ceramic component of FIG. 1 including a thermally grown oxide layer
on the silicon-based layer;
[0015] FIG. 3 is a cross-sectional side view of another exemplary
ceramic component including a silicon-based layer;
[0016] FIG. 4 is a cross-sectional side view of the exemplary
ceramic component of FIG. 3 including a thermally grown oxide layer
on the silicon-based layer; and
[0017] FIG. 5 is a schematic cross-sectional view of an exemplary
gas turbine engine according to various embodiments of the present
subject matter.
[0018] Repeat use of reference characters in the present
specification and drawings is intended to represent the same or
analogous features or elements of the present invention.
DETAILED DESCRIPTION OF THE INVENTION
[0019] Reference now will be made in detail to embodiments of the
invention, one or more examples of which are illustrated in the
drawings. Each example is provided by way of explanation of the
invention, not limitation of the invention. In fact, it will be
apparent to those skilled in the art that various modifications and
variations can be made in the present invention without departing
from the scope or spirit of the invention. For instance, features
illustrated or described as part of one embodiment can be used with
another embodiment to yield a still further embodiment. Thus, it is
intended that the present invention covers such modifications and
variations as come within the scope of the appended claims and
their equivalents.
[0020] As used herein, the terms "first", "second", and "third" may
be used interchangeably to distinguish one component from another
and are not intended to signify location or importance of the
individual components.
[0021] Chemical elements are discussed in the present disclosure
using their common chemical abbreviation, such as commonly found on
a periodic table of elements. For example, hydrogen is represented
by its common chemical abbreviation H; helium is represented by its
common chemical abbreviation He; and so forth. As used herein, "Ln"
refers to a rare earth element or a mixture of rare earth elements.
More specifically, the "Ln" refers to the rare earth elements of
scandium (Sc), yttrium (Y), lanthanum (La), cerium (Ce),
praseodymium (Pr), neodymium (Nd), promethium (Pm), samarium (Sm),
europium (Eu), gadolinium (Gd), terbium (Tb), dysprosium (Dy),
holmium (Ho), erbium (Er), thulium (Tm), ytterbium (Yb), lutetium
(Lu), or mixtures thereof.
[0022] In the present disclosure, when a layer is being described
as "on" or "over" another layer or substrate, it is to be
understood that the layers can either be directly contacting each
other or have another layer or feature between the layers, unless
expressly stated to the contrary. Thus, these terms are simply
describing the relative position of the layers to each other and do
not necessarily mean "on top of" since the relative position above
or below depends upon the orientation of the device to the
viewer.
[0023] Silicon-based coatings that include In are generally
provided for use with environmental barrier coatings for ceramic
components, along with their methods of formation. In particular
embodiments, silicon-based bond coatings for environmental barrier
coatings (EBCs) are generally provided for high temperature ceramic
components, along with methods of its formation and use. In
particular, the silicon-based bond coating includes a component
containing In for preventing crystallization of a thermal growth
oxide ("TGO") on silicon-based bond coating in an EBC, which in
turn prevents spall of the coating caused by such crystallization
of the TGO. That is, the introduction of In within the
silicon-based bond coating keeps the TGO (i.e., the SiO) in an
amorphous phase. Accordingly, the operating temperature of the
silicon-based bond coating (and thus the TGO and EBC coating) can
be increased. Additionally, the inclusion of In can inhibit and
prevent crystallization of the TGO without greatly accelerating the
growth rate of the TGO. Additionally, In-containing components have
limited reaction with and/or solubility into in silicon oxide,
which can limit the rate of oxide scale growth.
[0024] FIGS. 1-4 show exemplary embodiments of a ceramic component
100 formed from a substrate 102 and a silicon-based layer 104a
(FIG. 1), 104b (FIG. 3), respectively. Each of the silicon-based
layers 104a, 104b includes a silicon-containing material and about
0.001% to about 85% of an In-containing compound, such as about 1%
to about 60% by weight of an In-containing compound (e.g., about 1%
to about 50% by weight, such as about 1% to about 25% by weight).
Generally, the In-containing compound is unreactive with the
composition of the silicon-based layer 104a (e.g., silicon
metal).
[0025] In one embodiment, the silicon-based layer 104a may include
the In-containing compound and a silicon-containing material (e.g.,
silicon metal, a silicide, etc.) in continuous phases that are
intertwined with each other. For example, the silicon-containing
material and the In-containing compound are intertwined continuous
phases having about 0.001% to about 85% by volume of the
In-containing compound, such as about 1% to about 60% by volume
(e.g., about 40% to about 60% by volume of the In-containing
compound). For example, the silicon-based layer 104a can include
the In-containing compound in about 15% by volume to about 85% by
volume, with the balance being the silicon containing compound.
[0026] In another embodiment, In-containing compound forms a
plurality of discrete phases dispersed within the
silicon-containing material (e.g., within a continuous phase of the
silicon-containing material), such as discrete particulate phases.
In such an embodiment, the silicon-based layer 104a can include
about 0.001% to about 40% by volume of the In-containing compound,
such as about 1% to about 25% by volume (e.g., about 1% to about
10% by volume of the In-containing compound).
[0027] In one particular embodiment, the substrate 102 is formed
from a CMC material (e.g., a silicon based, non-oxide ceramic
matrix composite). As used herein, "CMCs" refers to
silicon-containing, or oxide-oxide, matrix and reinforcing
materials. As used herein, "monolithic ceramics" refers to
materials without fiber reinforcement (e.g., having he matrix
material only). Herein, CMCs and monolithic ceramics are
collectively referred to as "ceramics."
[0028] Some examples of CMCs acceptable for use herein can include,
but are not limited to, materials having a matrix and reinforcing
fibers comprising non-oxide silicon-based materials such as silicon
carbide, silicon nitride, silicon oxycarbides, silicon oxynitrides,
and mixtures thereof. Examples include, but are not limited to,
CMCs with silicon carbide matrix and silicon carbide fiber; silicon
nitride matrix and silicon carbide fiber; and silicon
carbide/silicon nitride matrix mixture and silicon carbide fiber.
Furthermore, CMCs can have a matrix and reinforcing fibers
comprised of oxide ceramics. Specifically, the oxide-oxide CMCs may
be comprised of a matrix and reinforcing fibers comprising
oxide-based materials such as aluminum oxide (Al.sub.2O.sub.3),
silicon dioxide (SiO.sub.2), aluminosilicates, and mixtures
thereof. Aluminosilicates can include crystalline materials such as
mullite (3Al.sub.2O.sub.3 2SiO.sub.2), as well as glassy
aluminosilicates.
[0029] In the embodiment of FIG. 1, the substrate 102 defines a
surface 103 having a coating 106 formed thereon. The coating 106
includes the silicon-based layer 104a and an environmental barrier
coating 108. In one particular embodiment, the silicon-based layer
104a is a bond coating, where the silicon containing material is
silicon metal, a silicide (e.g., a rare earth silicide, a
molybdenum silicide, a rhenium silicide, or mixtures thereof) or a
mixture thereof. In one embodiment, a composition is generally
provided that includes silicon metal and the In-containing
compound, such as in the relative amounts described above (e.g.,
about 0.01 to about 85% by volume). In an alternative embodiment, a
composition is generally provided that includes a silicide (e.g., a
rare earth silicide, a molybdenum silicide, a rhenium silicide, or
mixtures thereof) and the In-containing compound, such as in the
relative amounts described above (e.g., about 0.01 to about 85% by
volume).
[0030] During use, a thermally grown oxide ("TGO") layer forms on
the surface of the bond coating. For example, a layer of silicon
oxide (sometimes referred to as "silicon oxide scale" or "silica
scale") forms on a bond coating of silicon metal and/or a silicide.
Referring to FIG. 2, a thermally grown oxide layer 105 (e.g.,
silicon oxide) is shown directly on the silicon-based layer 104a
(e.g., a bond coating with the silicon containing material being
silicon metal and/or a silicide), as forms during exposure to
oxygen (e.g., during manufacturing and/or use) of the component
100. Due to the presence of the In-containing compound within the
silicon-based layer 104a, the thermally grown oxide layer 105
remains substantially amorphous at its operating temperature, with
the "operating temperature" referring to the temperature of the
thermally grown oxide layer 105. For example, for silicon metal
bond coatings, the TGO layer may remain amorphous at operating
temperatures of about 1415.degree. C. or less (e.g., about
1200.degree. C. to about 1410.degree. C.), which is just below the
melting point of the silicon-based bond coating (Si metal has a
melting point of about 1414.degree. C.). In another example, for
silicide bond coatings, the TGO layer may remain amorphous at
operating temperatures of about 1485.degree. C. or less (e.g.,
about 1200.degree. C. to about 1415.degree. C.), which is just
below the maximum use temperature of the CMC. Without wishing to be
bound by any particular theory, it is believed that indium in the
silicon-based layer 104a migrates into the thermally grown oxide
layer 105 and inhibits crystallization of the thermally grown oxide
layer (e.g., silicon oxide) that would otherwise occur at these
temperatures. Without wishing to be bound by any particular theory,
it is presently believed that In inhibits impurities such as Na
and/or K from causing crystallization of the amorphous
silicon-containing material.
[0031] In the embodiment shown in FIGS. 1 and 2, the silicon-based
layer 104a is directly on the surface 103 without any layer
therebetween. However, in other embodiments, one or more layers can
be positioned between the silicon-based layer 104a and the surface
103.
[0032] FIG. 3 shows another embodiment of a ceramic component 100
with the substrate 102 having an outer layer 104b that defines a
surface 103 of the substrate 102. That is, the outer layer 104b is
integral with the substrate 102. In this embodiment, the outer
layer 104b is the silicon-based layer, and a coating 106 is on the
surface 105. The coating 106 may include an environmental barrier
coating 108 and/or other layers (e.g., a bond coating, etc.). In
one embodiment, the outer layer 104b can be a silicon-containing
monolithic ceramic layer. For example, the outer layer 104b may
include silicon carbide. In one embodiment, the substrate 102 may
include the outer layer 104b (e.g., including silicon carbide as a
monolithic ceramic layer) on a plurality of CMC plies forming the
remaining portion of the substrate.
[0033] FIG. 4 shows a thermally grown oxide layer 105 (e.g.,
silicon oxide) directly on the silicon-based layer 104b (e.g., a
bond coating with the silicon containing material being silicon
metal), as forms during exposure to oxygen (e.g., during
manufacturing and/or use) of the component 100. Due to the presence
of the In-containing compound within the silicon-based layer 104b,
the thermally grown oxide layer 105 remains substantially amorphous
at the operating temperature of the thermally grown oxide layer
105. Without wishing to be bound by any particular theory, it is
believed that indium in the silicon-based layer 104b migrates into
the thermally grown oxide layer 105 and inhibits crystallization of
the thermally grown oxide layer (e.g., silicon oxide) that would
otherwise occur at these temperatures.
[0034] As stated, an In-containing compound is included within the
silicon-based layer 104a, 104b, no matter the particular
positioning of the silicon-based layer 104 in the ceramic component
100. In particular embodiments, the In-containing compound is in
the form of an oxide or a nitride. For example, the In-containing
compound can be indium nitride (InN), indium oxide
(In.sub.2O.sub.3), or a mixture thereof. In the embodiment where
the In-containing compound includes indium oxide, the indium oxide
can be doped within another oxide. For example, the In-containing
compound can be zirconium oxide (ZrO.sub.2), hafnium oxide
(HfO.sub.2), or a combination thereof doped with up to about 10
mole % of In.sub.2O.sub.3.
[0035] In one embodiment, the In-containing compound can be an
indium-metal-oxide. For example, the In-containing compound can
have, in one embodiment, a formula of:
In.sub.2-xM.sub.xO.sub.3
where M is Ga with x being 0 to less than 2, Al with x being 0 to
about 1.4, B with x being 0 to about 1.4, Fe with x being 0 to
about 1.4, or a mixture thereof. In one embodiment, M is Ga with x
being greater than 0 to less than 2, Al with x being greater than 0
to about 1.4, B with x being greater than 0 to about 1.4, Fe with x
being greater than 0 to about 1.4, or a mixture thereof, such that
at least one other metal (Ga, Al, B, and/or Fe) is present in the
indium-metal-oxide.
[0036] In one embodiment, the In-containing compound can have a
formula of:
Ln.sub.3In.sub.5-xM.sub.xO.sub.12
where Ln is Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er,
Tm, Yb, Lu, or a mixture thereof; and M is Ga with x being 0 to
less than 5 (e.g., 0.ltoreq.x<5, such as 0<x.ltoreq.2.5), Al
with x being 0 to less than 5 (e.g., 0.ltoreq.x<5, such as
0<x.ltoreq.2.5), Fe with x being 0 to less than 5 (e.g.,
0.ltoreq.x<5, such as 0<x.ltoreq.2.5), B with x being 0 to
about 2.5 (e.g., 0.ltoreq.x.ltoreq.2.5), or a combination thereof.
In one particular embodiment, M is B, with x being greater than 0
to about 2.5 (e.g., 0<x.ltoreq.2.5), such as about 0.1 to about
2 (e.g., 0.1.ltoreq.x.ltoreq.2). In one embodiment, x is greater
than 0 (e.g., 0.1 to about 2) such that at least one of M (e.g.,
Ga, Al, Fe, and/or B) is present in the In-containing compound.
[0037] In one embodiment, the In-containing compound can have a
formula of:
Ln.sub.2-x-yGa.sub.xIn.sub.ySi.sub.2O.sub.7
where Ln is Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er,
Tm, Yb, Lu, or a mixture thereof; x is 0 to about 1; and y is
greater than 0 to about 1. In one embodiment, the sum of x and y is
greater than 0 up to about 1 (i.e., 0<(x+y).ltoreq.about 1),
such as about greater than 0 up to about 0.5 (i.e.,
0<(x+y).ltoreq.about 0.5). In one embodiment, x is 0.
[0038] In one embodiment, the Ga-containing compound, the
In-containing compound, or the mixture thereof can have a formula
of:
Ln.sub.2-x-yGa.sub.xIn.sub.ySi.sub.2O.sub.5
[0039] where Ln is Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy,
Ho, Er, Tm, Yb, Lu, or a mixture thereof; x is 0 to about 1; and y
is greater than 0 to about 1. In one embodiment, the sum of x and y
is greater than 0 up to about 1 (i.e., 0<(x+y).ltoreq.about 1),
such as about greater than 0 up to about 0.5 (i.e.,
0<(x+y).ltoreq.about 0.5). In one embodiment, x is 0.
[0040] The environmental barrier coating 108 of FIGS. 1-4 can
include any combination of one or more layers formed from materials
selected from typical EBC or TBC layer chemistries, including but
not limited to rare earth silicates (mono- and di-silicates),
mullite, barium strontium aluminosilicate (BSAS), hafnia, zirconia,
stabilized hafnia, stabilized zirconia, rare earth hafnates, rare
earth zirconates, rare earth gallates, etc.
[0041] The ceramic component 100 of FIGS. 1-4 is particularly
suitable for use as a component found in high temperature
environments, such as those present in gas turbine engines, for
example, combustor components, turbine blades, shrouds, nozzles,
heat shields, and vanes. In particular, the turbine component can
be a CMC component positioned within a hot gas flow path of the gas
turbine such that the coating forms an environmental barrier
coating on the component to protect the component within the gas
turbine when exposed to the hot gas flow path.
[0042] FIG. 5 is a schematic cross-sectional view of a gas turbine
engine in accordance with an exemplary embodiment of the present
disclosure. More particularly, for the embodiment of FIG. 5, the
gas turbine engine is a high-bypass turbofan jet engine 10,
referred to herein as "turbofan engine 10." As shown in FIG. 5, the
turbofan engine 10 defines an axial direction A (extending parallel
to a longitudinal centerline 12 provided for reference) and a
radial direction R. In general, the turbofan 10 includes a fan
section 14 and a core turbine engine 16 disposed downstream from
the fan section 14. Although described below with reference to a
turbofan engine 10, the present disclosure is applicable to
turbomachinery in general, including turbojet, turboprop and
turboshaft gas turbine engines, including industrial and marine gas
turbine engines and auxiliary power units.
[0043] The exemplary core turbine engine 16 depicted generally
includes a substantially tubular outer casing 18 that defines an
annular inlet 20. The outer casing 18 encases, in serial flow
relationship, a compressor section including a booster or low
pressure (LP) compressor 22 and a high pressure (HP) compressor 24;
a combustion section 26; a turbine section including a high
pressure (HP) turbine 28 and a low pressure (LP) turbine 30; and a
jet exhaust nozzle section 32. A high pressure (HP) shaft or spool
34 drivingly connects the HP turbine 28 to the HP compressor 24. A
low pressure (LP) shaft or spool 36 drivingly connects the LP
turbine 30 to the LP compressor 22.
[0044] For the embodiment depicted, the fan section 14 includes a
variable pitch fan 38 having a plurality of fan blades 40 coupled
to a disk 42 in a spaced apart manner. As depicted, the fan blades
40 extend outwardly from disk 42 generally along the radial
direction R. Each fan blade 40 is rotatable relative to the disk 42
about a pitch axis P by virtue of the fan blades 40 being
operatively coupled to a suitable actuation member 44 configured to
collectively vary the pitch of the fan blades 40 in unison. The fan
blades 40, disk 42, and actuation member 44 are together rotatable
about the longitudinal axis 12 by LP shaft 36 across an optional
power gear box 46. The power gear box 46 includes a plurality of
gears for stepping down the rotational speed of the LP shaft 36 to
a more efficient rotational fan speed.
[0045] Referring still to the exemplary embodiment of FIG. 5, the
disk 42 is covered by rotatable front nacelle 48 aerodynamically
contoured to promote an airflow through the plurality of fan blades
40. Additionally, the exemplary fan section 14 includes an annular
fan casing or outer nacelle 50 that circumferentially surrounds the
fan 38 and/or at least a portion of the core turbine engine 16. It
should be appreciated that the nacelle 50 may be configured to be
supported relative to the core turbine engine 16 by a plurality of
circumferentially-spaced outlet guide vanes 52. Moreover, a
downstream section 54 of the nacelle 50 may extend over an outer
portion of the core turbine engine 16 so as to define a bypass
airflow passage 56 therebetween.
[0046] During operation of the turbofan engine 10, a volume of air
58 enters the turbofan 10 through an associated inlet 60 of the
nacelle 50 and/or fan section 14. As the volume of air 58 passes
across the fan blades 40, a first portion of the air 58 as
indicated by arrows 62 is directed or routed into the bypass
airflow passage 56 and a second portion of the air 58 as indicated
by arrow 64 is directed or routed into the LP compressor 22. The
ratio between the first portion of air 62 and the second portion of
air 64 is commonly known as a bypass ratio. The pressure of the
second portion of air 64 is then increased as it is routed through
the high pressure (HP) compressor 24 and into the combustion
section 26, where it is mixed with fuel and burned to provide
combustion gases 66.
[0047] The combustion gases 66 are routed through the HP turbine 28
where a portion of thermal and/or kinetic energy from the
combustion gases 66 is extracted via sequential stages of HP
turbine stator vanes 68 that are coupled to the outer casing 18 and
HP turbine rotor blades 70 that are coupled to the HP shaft or
spool 34, thus causing the HP shaft or spool 34 to rotate, thereby
supporting operation of the HP compressor 24. The combustion gases
66 are then routed through the LP turbine 30 where a second portion
of thermal and kinetic energy is extracted from the combustion
gases 66 via sequential stages of LP turbine stator vanes 72 that
are coupled to the outer casing 18 and LP turbine rotor blades 74
that are coupled to the LP shaft or spool 36, thus causing the LP
shaft or spool 36 to rotate, thereby supporting operation of the LP
compressor 22 and/or rotation of the fan 38.
[0048] The combustion gases 66 are subsequently routed through the
jet exhaust nozzle section 32 of the core turbine engine 16 to
provide propulsive thrust. Simultaneously, the pressure of the
first portion of air 62 is substantially increased as the first
portion of air 62 is routed through the bypass airflow passage 56
before it is exhausted from a fan nozzle exhaust section 76 of the
turbofan 10, also providing propulsive thrust. The HP turbine 28,
the LP turbine 30, and the jet exhaust nozzle section 32 at least
partially define a hot gas path 78 for routing the combustion gases
66 through the core turbine engine 16.
[0049] Methods are also generally provided for coating a ceramic
component. In one embodiment, the method includes applying a bond
coating directly on a surface of the ceramic component, where the
bond coating comprises a silicon-containing material (e.g., silicon
metal and/or a silicide) and an In-containing compound, such as
described above.
[0050] This written description uses examples to disclose the
invention, including the best mode, and also to enable any person
skilled in the art to practice the invention, including making and
using any devices or systems and performing any incorporated
methods. The patentable scope of the invention is defined by the
claims, and may include other examples that occur to those skilled
in the art. Such other examples are intended to be within the scope
of the claims if they include structural elements that do not
differ from the literal language of the claims, or if they include
equivalent structural elements with insubstantial differences from
the literal languages of the claims.
* * * * *