U.S. patent application number 11/416430 was filed with the patent office on 2007-11-01 for methods and apparatus for assembling gas turbine engines.
This patent application is currently assigned to General Electric Company. Invention is credited to Joseph C. Albers, Christopher C. Glynn, William L. Herron.
Application Number | 20070253809 11/416430 |
Document ID | / |
Family ID | 38137546 |
Filed Date | 2007-11-01 |
United States Patent
Application |
20070253809 |
Kind Code |
A1 |
Glynn; Christopher C. ; et
al. |
November 1, 2007 |
Methods and apparatus for assembling gas turbine engines
Abstract
A method assembling a seal assembly within a gas turbine engine.
The method includes coupling a stationary stator member to a gas
turbine engine including a rotating member, and coupling a primary
seal assembly and a secondary seal assembly to the stationary
stator member wherein the primary seal assembly includes a moveable
stator member including at least one keyed slot, and at least one
biasing member including at least one key. Moreover, the at least
one key is slidably coupled within the at least one keyed slot to
facilitate aligning the primary seal assembly and the secondary
seal assembly with respect to the gas turbine engine, and the seal
assembly facilitates sealing between the stationary stator member
and the rotating member.
Inventors: |
Glynn; Christopher C.;
(Hamilton, OH) ; Herron; William L.; (Cincinnati,
OH) ; Albers; Joseph C.; (Ft. Wright, KY) |
Correspondence
Address: |
JOHN S. BEULICK (12729);C/O ARMSTRONG TEASDALE LLP
ONE METROPOLITAN SQUARE
SUITE 2600
ST. LOUIS
MO
63102-2740
US
|
Assignee: |
General Electric Company
|
Family ID: |
38137546 |
Appl. No.: |
11/416430 |
Filed: |
May 1, 2006 |
Current U.S.
Class: |
415/174.2 |
Current CPC
Class: |
F01D 11/04 20130101;
F01D 25/183 20130101 |
Class at
Publication: |
415/174.2 |
International
Class: |
F01D 11/00 20060101
F01D011/00 |
Claims
1. A method of assembling a seal assembly within a gas turbine
engine, said method comprising: coupling a stationary stator member
to a gas turbine engine comprising a rotating member; and coupling
a primary seal assembly and a secondary seal assembly to the
stationary stator member wherein the primary seal assembly
comprises a moveable stator member comprising at least one keyed
slot, and at least one biasing member comprising at least one key,
wherein the at least one key is slidably coupled within the at
least one keyed slot to facilitate aligning the primary seal
assembly and the secondary seal assembly with respect to the gas
turbine engine and wherein the seal assembly facilitates sealing
between the stationary stator member and the rotating member.
2. A method of assembling a seal assembly in accordance with claim
1 wherein the primary seal assembly comprises at least three
biasing members, the at least three biasing members each comprise a
biasing mechanism and a housing, said method further comprising
coupling the housing to the stationary stator member and coupling
the biasing mechanism within the housing.
3. A method of assembling a seal assembly in accordance with claim
2 wherein the moveable stator member comprises at least three keyed
slots and the housing comprises at least three keys, said method
further comprising slidably coupling the at least three keys within
the at least three keyed slots.
4. A method of assembling a seal assembly in accordance with claim
1 wherein the secondary seal assembly comprises a piston ring seal
and the moveable stator member comprises a yoke, said method
further comprising coupling the piston ring seal within the
yoke.
5. A method of assembling a seal assembly in accordance with claim
1 wherein said method further comprises facilitating limiting axial
movement of the moveable stator member with respect to the
stationary stator member and facilitating rotational alignment
between the primary and secondary seal assemblies.
6. A seal assembly for a gas turbine engine comprising a stationary
stator member and a rotating member, said seal assembly comprising:
a primary seal assembly; and a secondary seal assembly, said
primary seal assembly comprising: a moveable stator member
comprising at least one keyed slot; and at least one biasing member
comprising at least one key slidably coupled within said at least
one keyed slot to facilitate aligning said primary seal assembly
and said secondary seal assembly with respect to the gas turbine
engine.
7. A seal assembly in accordance with claim 6 wherein said primary
seal assembly further comprises at least three biasing members,
said at least three biasing members each further comprise a biasing
mechanism and a housing, said biasing mechanism is contained within
said housing.
8. A seal assembly in accordance with claim 7 wherein said at least
one key extends substantially radially outward from said housing,
said at least one key facilitates rotational alignment between said
primary and secondary seal assemblies.
9. A seal assembly in accordance with claim 6 wherein said seal
assembly facilitates sealing between said stationary stator member
and said rotating member.
10. A seal assembly in accordance with claim 6 wherein said
moveable stator member further comprises at least three keyed
slots, said at least three keyed slots facilitate limiting axial
and rotational movement of said moveable stator member with respect
to the stationary stator member.
11. A seal assembly in accordance with claim 6 wherein said
moveable stator member further comprises a sealing face comprising
a plurality of teeth extending outward from said sealing face, and
said sealing face further comprises an opening extending
therethrough, said opening facilitates preventing contact between
said moveable stator member and the rotating member.
12. A seal assembly in accordance with claim 6 wherein said
secondary seal assembly comprises a piston ring seal, said moveable
stator member comprises a yoke, said yoke sized to receive said
piston ring seal therein.
13. A gas turbine engine comprising: a stationary stator member; a
rotating member; and a seal assembly comprising a primary seal
assembly and a secondary seal assembly, said primary seal assembly
comprising: a moveable stator member comprising at least one keyed
slot; and at least one biasing member comprising at least one key,
wherein said at least one key is slidably coupled within said at
least one keyed slot to facilitate aligning said primary seal
assembly and said secondary seal assembly with respect to said gas
turbine engine, said seal assembly facilitates sealing between said
stationary stator member and said rotating member.
14. A gas turbine engine in accordance with claim 13 wherein said
moveable stator member further comprises a sealing face and a
plurality of teeth extending outward from said sealing face.
15. A gas turbine engine in accordance with claim 13 wherein said
moveable stator member comprises an opening extending therethrough,
said opening facilitates preventing contact between said rotating
member and said stationary stator member.
16. A seal assembly in accordance with claim 13 wherein said
secondary seal assembly comprises a piston ring seal, said moveable
stator member comprises a yoke, said yoke sized to receive said
piston ring seal therein.
17. A gas turbine engine in accordance with claim 13 wherein said
primary seal assembly further comprises at least three biasing
members, said at least three biasing members each comprise a
biasing mechanism and a housing, said biasing mechanism is
contained within said housing.
18. A gas turbine engine in accordance with claim 13 wherein said
at least one key extends substantially radially outward from said
housing.
19. A gas turbine engine in accordance with claim 13 wherein said
moveable stator member further comprises at least three keyed
slots, said at least three keyed slots facilitate limiting axial
movement of said moveable stator member with respect to said
stationary stator member.
20. A gas turbine engine in accordance with claim 13 wherein said
at least one keyed slot facilitates limiting rotational movement of
said moveable stator member with respect to said stationary stator
member.
Description
BACKGROUND OF THE INVENTION
[0001] This invention relates generally to gas turbine engines and
more specifically to seal assemblies used with gas turbine
engines.
[0002] At least some known gas turbine engines have large amounts
of fluids flowing through the engine during operation. Seal
assemblies control fluid leakage in the engine by restricting fluid
flow from areas of higher pressure to areas of lower pressure. The
seal assemblies may be positioned between an engine stationary
member and a rotating member within the engine. In addition, seals
facilitate compensating for transient variations that may exist in
gaps defined between components.
[0003] Fluid leakage through gas turbine engine seal assemblies may
significantly increase fuel consumption and adversely affect engine
efficiency. Additionally, fluid leakage may cause damage to other
components and/or increase overall engine maintenance costs.
Because of the location of the seal assemblies, and/or the
operating environment, at least some known seal assemblies may
deteriorate over time.
[0004] To facilitate sealing gaps defined between regions of high
and low pressure; at least some known seal assemblies, such as the
seal assembly described in U.S. Pat. No. 5,284,347, for example,
use aspirating air to control leakage. The aspirating air prevents
the rotating member from contacting the stationary member to
facilitate accommodating transient variations in the gap defined
between the rotating and stationary members with little or no
deterioration of the seal over the life of the seal assembly.
However, because of the number of seal assembly components, such
seal assemblies may be complex to install in the engine, and the
weight of such assemblies may adversely affect engine performance.
Moreover, seal assemblies may be contingent on the tolerances
between the rotating and stationary members.
BRIEF DESCRIPTION OF THE INVENTION
[0005] In one aspect, a method of assembling a seal assembly within
a gas turbine engine is provided. The method includes coupling a
stationary stator member to a gas turbine engine comprising a
rotating member, and coupling a primary seal assembly and a
secondary seal assembly to the stationary stator member, wherein
the primary seal assembly includes a moveable stator member
including at least one keyed slot and at least one biasing member.
The biasing member includes at least one key that is slidably
coupled within the at least one keyed slot to facilitate aligning
the primary seal assembly and the secondary seal assembly with
respect to the gas turbine engine. The seal assembly facilitates
sealing between the stationary stator member and the rotating
member.
[0006] In another aspect, a seal assembly for a gas turbine engine
including a stationary stator member and a rotating member is
provided. The seal assembly includes a primary seal assembly and a
secondary seal assembly. The primary seal assembly includes a
moveable stator member including at least one keyed slot, and at
least one biasing member. The biasing member includes at least one
key slidably coupled within the at least one keyed slot to
facilitate aligning the primary seal assembly and the secondary
seal assembly with respect to the gas turbine engine.
[0007] In a further aspect, a gas turbine engine including a
stationary stator member, a rotating member, and a seal assembly is
provided. The seal assembly including a primary seal assembly and a
secondary seal assembly. The primary seal assembly includes a
moveable stator member including at least one keyed slot, and at
least one biasing member. The biasing member includes at least one
key. The at least one key is slidably coupled within the at least
one keyed slot to facilitate aligning the primary seal assembly and
the secondary seal assembly with respect to the gas turbine engine.
The seal assembly facilitates sealing between the stationary stator
member and the rotating member.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] FIG. 1 is a schematic illustration of an exemplary gas
turbine engine; and
[0009] FIG. 2 is a cross-sectional view of an exemplary seal
assembly that may be used with the gas turbine engine shown in FIG.
1.
DETAILED DESCRIPTION OF THE INVENTION
[0010] Although the invention is herein described and illustrated
in association with a compressor to turbine interface for a gas
turbine engine, it should be understood that the present invention
may be used to facilitate controlling leakage of any fluid between
any region of generally high pressure and any region of lower
pressure within a gas turbine engine.
[0011] FIG. 1 is a schematic illustration of a gas turbine engine
10 including a fan assembly 12, a compressor 14, and a combustor
16. In one embodiment, compressor 14 is a high-pressure compressor.
Engine 10 also includes a high-pressure turbine 18, and a
low-pressure turbine 20. In one embodiment, engine 10 is a CFM 56
engine commercially available from General Electric Company,
Cincinnati, Ohio.
[0012] In operation, air flows through fan assembly 12 and
compressed air is supplied to compressor 14. The compressed air is
delivered to combustor 16. Airflow from combustor 16 drives
turbines 18 and 20, and turbine 20 drives fan assembly 12.
[0013] FIG. 2 is a cross-sectional view of an exemplary seal
assembly 100 that may be used within gas turbine engine 10. In the
exemplary embodiment, gas turbine engine 10 includes stationary
stator member 102 coupled to frame 103 and a rotating member 104.
Frame 103 is a stationary circumferential member positioned around
an axis of rotation (not shown in FIG. 2). In one embodiment, frame
103 is part of the casing of gas turbine engine 10. As air flows
through engine 10, frame 103 is configured to help contain flowpath
air. Additionally, stationary stator member 102 is a stationary
circumferential member positioned around the axis of rotation of
gas turbine engine 10. In one embodiment, stationary stator member
102 is bolted to frame 103. In one embodiment, rotating member 104
is a rotor that is rotatably coupled within engine 10 to rotate
about the axis of rotation.
[0014] In the exemplary embodiment, seal assembly 100 includes a
primary seal assembly 106 and a secondary seal assembly 108 that
are each substantially concentrically aligned with respect to the
axis of rotation of gas turbine engine 10. A moveable stator member
110 includes a primary seal assembly 106. Moveable stator member
110 also includes at least one keyed slot 118. In the exemplary
embodiment, moveable stator member 110 includes at least three
keyed slots 118. Moveable stator member 110 is also a
circumferential member positioned around the axis of rotation of
gas turbine engine 10. In the exemplary embodiment, moveable stator
member 110 is positioned within stationary stator member 102.
Primary seal assembly 106 also includes at least one biasing member
114. In the exemplary embodiment, primary seal assembly 106
includes at least three biasing members 114. Biasing member 114
includes at least one key 116, a biasing mechanism 120, and a
housing 122. In the exemplary embodiment, housing 122 is bolted to
stationary stator member 102 such that housing 122 is stationary.
Additionally, in the exemplary embodiment, stationary stator member
102 includes at least three housings 122 spaced along the
circumference of stationary stator member 102. Biasing mechanism
120 is contained within housing 122, and key 116 extends radially
outward from housing 122. Key 116 is integrally formed with housing
122. In the exemplary embodiment, biasing mechanism 120 is a spring
and housing 122 is a spring cartridge.
[0015] Moveable stator member 110 includes a keyed slot 118. In the
exemplary embodiment, keyed slot 118 is machined within moveable
stator member 110. Additionally, in the exemplary embodiment,
moveable stator member 110 includes a number of keyed slots 118
equal to the number of keys 116. Specifically, keyed slot 118
extends a distance and is sized to receive a portion of key 116
therein. More specifically, key 116 is slidably coupled within
keyed slot 118 such that during operation, key 116, as will be
described in more detail below, is moveable along a portion of the
distance of keyed slot 118. Key 116 moves within keyed slot 118
allowing moveable stator member 110 to move. Moreover, key 116
facilitates aligning primary seal assembly 106 and secondary seal
assembly 108 with respect to gas turbine engine 10.
[0016] Moveable stator member 110 also includes a sealing face 124
and a plurality of teeth 126 that extend outward from sealing face
124. In the exemplary embodiment, sealing face 124 is substantially
parallel to a rotating member surface 125 of rotating member 104.
More specifically, sealing face 124 is a distance 123 away from
rotating member 104. Moveable stator member 110 also includes an
opening 127 defined therein, and positioned within sealing face 124
such that opening 127 extends through sealing face 124. In the
exemplary embodiment, opening 127 is oriented substantially
perpendicular to rotating member surface 125. As described below in
more detail, opening 127 facilitates preventing contact between
plurality of teeth 126 and rotating member 104. Moveable stator
member 110 further includes a plurality of radial openings 134
extending through moveable stator member 110. In the exemplary
embodiment, radial openings 134 are substantially parallel to
rotating member surface 125. Additionally, in the exemplary
embodiment, radial openings 134 cross between openings 127.
[0017] Moveable stator member 110 also includes a yoke 130 that is
sized to receive at least a portion of secondary seal assembly 108
therein. More specifically, secondary seal assembly 108 includes a
seal 128 that is received within yoke 130. In the exemplary
embodiment, seal 128 is a piston ring seal. In an alternative
embodiment, seal 128 may be retained by stationary stator member
102.
[0018] During operation, cooling air and/or fluids flow through gas
turbine engine 10. When engine 10 is in operation, high pressure
air flows forward to aft through engine 10. A portion of the highly
compressed air discharged from high pressure compressor 14 is
directed towards seal assembly 100 for use as cooling fluid. Seal
assembly 100 facilitates substantially controlling fluid flow from
a region of higher pressure 137 to a region of lower pressure 140
within gas turbine engine 10. The pressure differential between
higher pressure region 137 and lower pressure region 140 initiates
flow through seal assembly 100.
[0019] Biasing mechanism 120 biases moveable stator member 110 away
from rotating member 104. Moveable stator member 110 slides forward
and aft relative to housing 122, stationary stator member 102, and
frame 103. During operation of gas turbine engine 10, a portion of
the high pressure air will flow into a region 138 defined between
stationary stator member 102 and moveable stator member 110. The
high pressure air exerts a pressure on moveable stator member 110
causing moveable stator member 110 to move, against and to overcome
biasing force exerted by biasing mechanism 120, within keyed slot
118, and towards rotating member 104. Specifically, during
operation, key 116 translates within keyed slot 118 such that keyed
slot 118 limits the amount of travel of moveable stator member 110
and prevents rotational, circumferential and/or radial, movement of
moveable stator member 110 with respect to stationary stator member
102, housing 122, and frame 103. Keyed slot 118 also facilitates
aligning primary seal and secondary seal assemblies 106 and 108
with respect to gas turbine engine 10.
[0020] Additionally, during operation, a portion of the high
pressure air flows through opening 127. In the exemplary
embodiment, opening 127 is a plurality of feed openings. Opening
127 forms a high pressure film or air bearing between opening 127
and rotating member surface 125. The air bearing prevents moveable
stator member 110 from contacting rotating member 104.
[0021] After air flows through opening 127, the air exits to the
region of lower pressure 140. Also, a portion of air may leak past
seal teeth 126. Air that leaks past seal teeth 126 and air that has
exited opening 127 flows through radial openings 134 to the region
of lower pressure 140. Moreover, secondary seal assembly 108
creates a second seal to prevent leakage of high pressure air
between moveable stator member 110 and stationary stator member
102.
[0022] When gas turbine engine 10 is not in operation, the biasing
force of biasing mechanism 120 pushes against moveable stator
member 110 moving moveable stator member 110 and holding moveable
stator member 110 away from rotating member 104 to prevent contact
between members 104 and 110.
[0023] During assembly of gas turbine engine 10, stationary stator
member 102 is coupled to frame 103 of gas turbine engine 10 near
rotating member 104. Housing 122 is coupled to stationary stator
member 102. Moveable stator member 110 is coupled to and positioned
within stationary stator member 102. Keyed slot 118 is positioned
at least partially within key 116 and moves within keyed slot 118.
Biasing mechanism 120 is coupled and positioned within housing
122.
[0024] The above-described seal assembly includes a primary seal
assembly that includes a moveable stator member and a secondary
seal assembly. The moveable stator member facilitates reducing
leakage between the rotating member and the stationary engine
frame. As a result, the engine operates more efficiently.
Furthermore, the above-described seal assembly includes
significantly fewer components than some known seal assemblies.
With fewer components, such a seal is less expensive to install, is
easier to produce than known seal assemblies, reduces the amount
and cost of maintenance, is more reliable than known seal
assemblies, and is lighter weight. Weight of seal assemblies may
adversely affect engine performance.
[0025] Exemplary embodiments of a seal assembly are described above
in detail. The seal assembly is not limited to use with the
specific embodiments described herein, but rather, the seal
assembly can be utilized independently and separately from other
components described herein. Moreover, the invention is not limited
to the embodiments of the seal assembly described above in detail.
Rather, other variations of a seal assembly may be utilized within
the spirit and scope of the claims.
[0026] While the invention has been described in terms of various
specific embodiments, those skilled in the art will recognize that
the invention can be practiced with modification within the spirit
and scope of the claims.
* * * * *