U.S. patent application number 13/803452 was filed with the patent office on 2014-01-02 for ceramic matrix composite component and a method of attaching a static seal to a ceramic matrix composite component.
This patent application is currently assigned to General Electric Company. The applicant listed for this patent is GENERAL ELECTRIC COMPANY. Invention is credited to Robert Alan Frederick, James Hamilton GROOMS, II, Charles Thomas McMillan, Darrell Glenn Senile.
Application Number | 20140004293 13/803452 |
Document ID | / |
Family ID | 49778446 |
Filed Date | 2014-01-02 |
United States Patent
Application |
20140004293 |
Kind Code |
A1 |
GROOMS, II; James Hamilton ;
et al. |
January 2, 2014 |
CERAMIC MATRIX COMPOSITE COMPONENT AND A METHOD OF ATTACHING A
STATIC SEAL TO A CERAMIC MATRIX COMPOSITE COMPONENT
Abstract
A ceramic matrix composite (CMC) component and a method of
attaching a static seal to a ceramic matrix composite component are
provided. The CMC component includes a first end and a second end.
A CMC metal interface member is attached to the second end. The CMC
metal interface member is operable to join to a static seal in a
gas turbine.
Inventors: |
GROOMS, II; James Hamilton;
(Hamilton, OH) ; Senile; Darrell Glenn; (Oxford,
OH) ; Frederick; Robert Alan; (Evendale, OH) ;
McMillan; Charles Thomas; (Liberty Township, OH) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
GENERAL ELECTRIC COMPANY |
Schenectady |
NY |
US |
|
|
Assignee: |
General Electric Company
Schenectady
NY
|
Family ID: |
49778446 |
Appl. No.: |
13/803452 |
Filed: |
March 14, 2013 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
61666815 |
Jun 30, 2012 |
|
|
|
Current U.S.
Class: |
428/99 ;
29/888.02 |
Current CPC
Class: |
Y10T 428/24008 20150115;
F01D 9/065 20130101; F01D 5/282 20130101; F01D 11/001 20130101;
F04D 29/60 20130101; F01D 5/284 20130101; Y10T 29/49236
20150115 |
Class at
Publication: |
428/99 ;
29/888.02 |
International
Class: |
F04D 29/60 20060101
F04D029/60 |
Claims
1. A ceramic matrix composite component comprising: a first end; a
second end; and a CMC metal interface member attached to the second
end; wherein the CMC metal interface member is operable to join to
a static seal in a gas turbine.
2. The ceramic matrix composite of claim 1, wherein the ceramic
matrix composite component is a static component.
3. The ceramic matrix composite of claim 1, wherein the ceramic
matrix composite component is a vane or a nozzle.
4. The ceramic matrix composite of claim 1, wherein the static seal
is a honeycomb seal.
5. The ceramic matrix composite of claim 1, wherein the static seal
is attached to the CMC metal interface member by brazing or
welding.
6. The ceramic matrix composite of claim 1, wherein the CMC metal
interface member is attached to the second end by a bolt.
7. A method of attaching a metal seal to a ceramic matrix composite
component comprising: providing a ceramic matrix composite
component having a first end and a second end; providing a CMC
metal interface member; attaching the CMC metal interface member to
the second end of the ceramic matrix composite component; providing
a static seal; and joining the static seal to the CMC metal
interface member; wherein the CMC metal interface member forms a
plenum for purging rotor air.
8. The method of claim 7, wherein the ceramic matrix composite
component is a static component.
9. The method of claim 7, wherein the ceramic matrix composite
component is a vane or a nozzle.
10. The method of claim 7, wherein the static seal is a honeycomb
seal.
11. The method of claim 7, wherein the static seal is joined to the
CMC metal interface member by brazing or welding.
12. The method of claim 7, wherein the CMC metal interface member
is attached to the second end of the ceramic matrix component by a
bolt.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This patent application claims the benefit of U.S.
Provisional Patent Application Ser. No. 61/666,815 filed on Jun.
30, 2012 and entitled "CERAMIC MATRIX COMPOSITE COMPONENT AND A
METHOD OF ATTACHING A STATIC SEAL TO A CERAMIC MATRIX COMPOSITE
COMPONENT," the disclosure of which is incorporated by reference as
if fully rewritten herein.
FIELD OF THE INVENTION
[0002] The present invention relates generally to turbines. More
specifically, to a ceramic matrix composite (CMC) component and a
method of attaching a metal seal to the ceramic matrix composite
component.
BACKGROUND OF THE INVENTION
[0003] A number of techniques have been used in the past to
manufacture turbine engine components, such as turbine blades or
nozzles using ceramic matrix composites (CMC). One method of
manufacturing CMC components relates to the production of silicon
carbide matrix composites containing fibrous material that is
infiltrated with molten silicon, herein referred to as the Silcomp
process. The fibers generally have diameters of about 140
micrometers or greater, which prevents intricate, complex shapes,
such as turbine blade components, to be manufactured by the Silcomp
process.
[0004] Another technique of manufacturing CMC turbine blades is the
method known as the slurry cast melt infiltration (MI) process. In
one method of manufacturing using the slurry cast MI method, CMCs
are produced by initially providing plies of balanced
two-dimensional (2D) woven cloth comprising silicon carbide
(SiC)-containing fibers, having two weave directions at
substantially 90.degree. angles to each other, with substantially
the same number of fibers running in both directions of the
weave.
[0005] Generally, such turbine components require attachment to
adjoining metallic hardware and/or metallic surfaces. Two
disadvantages associated with attaching a CMC to metallic hardware
are the wear of the metallic hardware by the hard, abrasive ceramic
material surface, and the lack of load distribution in the CMC.
Load distribution is critical in the interfaces between the CMC
components and metal surfaces, such as shrouds. Typically, metallic
shims or ceramic cloths have been interposed between the CMC and
metallic surfaces to improve load distribution. Wear is typically
reduced by the application of coatings to the metallic hardware or
coatings to the nozzle attachment surfaces.
[0006] Therefore, a ceramic matrix composite (CMC) component and a
method of attaching a metal seal to a CMC component that do not
suffer from the above drawbacks is desirable in the art.
SUMMARY OF THE INVENTION
[0007] According to an exemplary embodiment of the present
disclosure, a ceramic matrix composite component is provided. The
ceramic matrix composite component includes a first end and a
second end. The ceramic matrix composite component includes a CMC
metal interface member attached to the second end. The CMC metal
interface member is operable to join to a static seal in a gas
turbine.
[0008] According to another exemplary embodiment of the present
disclosure, a method of attaching a static seal to a ceramic matrix
composite component is provided. The method includes providing a
ceramic matrix composite component having a first end and a second
end. The method includes providing a CMC metal interface member.
The method includes attaching the CMC metal interface member to the
second end of the ceramic matrix composite component. The method
includes providing a static seal and joining the static seal to the
CMC metal interface member. The CMC metal interface member forms a
plenum for purging rotor air.
[0009] Other features and advantages of the present invention will
be apparent from the following more detailed description of the
preferred embodiment, taken in conjunction with the accompanying
drawings which illustrate, by way of example, the principles of the
invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0010] FIG. 1 is a perspective schematic section view of a CMC
component of the present disclosure.
[0011] FIG. 2 is a perspective schematic section view of a CMC
component of the present disclosure.
[0012] FIG. 3 is a schematic top partial view of a CMC component of
the present disclosure.
[0013] FIG. 4 is a flow chart of the method of attaching a static
seal to a CMC component of the present disclosure.
[0014] Wherever possible, the same reference numbers will be used
throughout the drawings to represent the same parts.
DETAILED DESCRIPTION OF THE INVENTION
[0015] Provided is a ceramic matrix composite (CMC) component and a
method of attaching a metal seal to the CMC component.
[0016] One aspect of an embodiment of the present disclosure
includes providing a honeycomb seal attachment for a CMC component.
Another aspect of the present disclosure is that the system allows
for different thermal growth of the CMC component and the CMC metal
interface member. Yet another aspect of the present disclosure is
that the system provides airfoil cavity sealing. Another aspect of
the present disclosure is that the system provides a plenum to feed
rotor purge air.
[0017] FIGS. 1 and 2 are perspective schematic section views of a
CMC component 10. CMC component may include a first end 14 and a
second end 16 opposite the first end. CMC component 10 may include
an impingement baffle cavity surrounded by outer layers 12. CMC
component 10 may be a non-rotating component, such as, but not
limited to, vanes or nozzles. For example, as depicted in the
figures CMC component 10 may be a nozzle. In one embodiment, CMC
component 10 may be attached to a nozzle hanger 80. Nozzle hanger
80 may be attached by any suitable means to a case 90 of a gas
turbine. CMC component 10 may be adjacent to rotating blades 100 in
gas turbine.
[0018] According to one embodiment, CMC component may include a CMC
metal interface member attached to second end of CMC component
creating a plenum underneath CMC component to distribute air when
needed for rotor purge. For example, as shown in FIGS. 1 and 2, CMC
component 10 may include a CMC metal interface member 50 or seal
box attached to second end 16 of CMC component 10. CMC metal
interface member 50 may create a plenum underneath CMC component 10
to distribute air when needed for rotor purge. As shown in FIG. 2,
the air used to purge the rotor is the arrow labeled 120. In one
embodiment, as shown, CMC metal interface member 50 may span a
single CMC component 10. In an alternative embodiment, CMC metal
interface member 50 may span a number of CMC components 10 and may
span up to a full 360 degree ring around CMC component 10. Material
for CMC metal interface member 50 may include, but is not limited
to, metals, metal alloys, and combinations thereof, for example the
alloys may include nickel-based superalloys, cobalt-based
superalloys, and combinations thereof. CMC metal interface 50 may
include a feed tube 64 that exits into a channel 54 adjacent to
static seal 40. For example, as shown in FIGS. 1 and 2, feed tube
60 may protrude from CMC metal interface 50 into impingement baffle
cavity 30. In an alternative embodiment, feed tube 64 may extend
down from impingement baffle cavity 30 into CMC metal interface 50.
In another embodiment, instead of using feed tube 64, to create
plenum, attachment member 70 may include a channel or aperture (not
shown) to receive rotor purge air 120. In an alternative
embodiment, CMC metal interface 50 may be unpressurized.
[0019] According to one embodiment, CMC metal interface member may
include an attachment member. For example, as shown in FIGS. 1 and
2, CMC metal interface member 50 includes an attachment member 70.
Attachment member 70 may be attached to CMC metal interface member
50 by any suitable means, such as, but not limited to, tapping
attachment member 70 into CMC metal interface member 50, using a
nut to secure attachment member 70 to CMC metal interface member
50, using an insert to secure attachment member 70 to CMC metal
interface member 50. Material for attachment member 70 may include,
but is not limited to, metals, metal alloys, and combinations
thereof, for example the alloys may include nickel-based
superalloys, cobalt-based superalloys, and combinations
thereof.
[0020] According to one embodiment, CMC metal interface member may
attach to CMC component by attachment member. For example, as shown
in FIGS. 1 and 2, CMC metal interface member 50 may attach to CMC
component 10 by attachment member 70. As shown in FIG. 3,
attachment member 70 may attach to impingement baffle cavity 30 of
CMC component 10. In one embodiment, attachment member 70 may be a
bolt of any desired length. In one embodiment, impingement baffle
cavity 30 may include an aperture (not shown) for receiving
attachment member, where the aperture may be threaded to receive
attachment member 70. In another embodiment, attachment member 70
may not be secured in impingement baffle cavity 30, instead a nut
or other stopping member may be used to hold attachment member 70
securely in place at second end 16 of CMC component 10.
[0021] According to one embodiment, CMC metal interface member may
provide a surface to join static seal to CMC component. For
example, as shown in FIGS. 1 and 2, CMC metal interface member 50
may provide a surface to join a static seal 40 to CMC component 10.
Static seal 40 may be attached to CMC metal interface member 50 by
any suitable joining means, such as, but not limited to, brazing
and welding. Joint 46 between CMC metal interface 50 and static
seal 40 is shown in FIGS. 1 and 2. In one embodiment, static seal
40 may be a honeycomb seal. Material for static seal 40 may be
selected from, but not limited to, metals, metal alloys, and
combinations thereof, for example, the alloys may include
nickel-based superalloys, cobalt-based superalloys, and
combinations thereof. Static seal 40 may be adjacent rotating seals
110 in gas turbine.
[0022] According to one embodiment, a method of attaching a metal
seal to a ceramic matrix component may include using a CMC
interface member and a static seal. For example, FIG. 4 depicts a
flow chart of a method 400 of attaching metal seal 40 to ceramic
matrix composite component 10. Method 400 may include providing
ceramic matrix composite component 10 having first end 14 and
second end 16, step 401 (see FIGS. 1 and 2). Method 400 may include
providing CMC metal interface member 50, step 403 (see FIGS. 1 and
2). Method 400 may include attaching CMC metal interface member 50
to second end 16 of ceramic matrix composite component 10, step 405
(see FIGS. 1 and 2). Method 400 may include providing static seal
40, step 407 (see FIGS. 1 and 2). Method 400 may include joining
static seal 40 to CMC metal interface member 50, step 409 (see
FIGS. 1 and 2). CMC metal interface member 50 may form a plenum for
purging rotor air and may provide a surface to attach static seal
40, which may be metal, to CMC component 10.
[0023] While the invention has been described with reference to a
preferred embodiment, it will be understood by those skilled in the
art that various changes may be made and equivalents may be
substituted for elements thereof without departing from the scope
of the invention. In addition, many modifications may be made to
adapt a particular situation or material to the teachings of the
invention without departing from the essential scope thereof.
Therefore, it is intended that the invention not be limited to the
particular embodiment disclosed as the best mode contemplated for
carrying out this invention, but that the invention will include
all embodiments falling within the scope of the appended
claims.
* * * * *