U.S. patent application number 11/830236 was filed with the patent office on 2009-02-05 for seal assembly.
Invention is credited to Joseph C. Albers, Peter Crudgington, William L. Herron, Kripa K. Varanasi.
Application Number | 20090033037 11/830236 |
Document ID | / |
Family ID | 40337380 |
Filed Date | 2009-02-05 |
United States Patent
Application |
20090033037 |
Kind Code |
A1 |
Varanasi; Kripa K. ; et
al. |
February 5, 2009 |
SEAL ASSEMBLY
Abstract
A seal assembly comprising a first movable stator member movable
between a sealing position and a non-sealing position, a second
fixed stator member, the first stator member being movable relative
to the second stator member, the seal assembly further comprising
at least one flexure member coupled to the second stator member,
and at least one biasing member coupled between the at least one
flexure and the movable stator for biasing the movable stator to a
non-sealing position.
Inventors: |
Varanasi; Kripa K.; (Clifton
Park, NY) ; Albers; Joseph C.; (Ft. Wright, KY)
; Herron; William L.; (Cincinnati, OH) ;
Crudgington; Peter; (Freshford, GB) |
Correspondence
Address: |
GENERAL ELECTRIC COMPANY
GE AVIATION, ONE NEUMANN WAY MD H17
CINCINNATI
OH
45215
US
|
Family ID: |
40337380 |
Appl. No.: |
11/830236 |
Filed: |
July 30, 2007 |
Current U.S.
Class: |
277/355 |
Current CPC
Class: |
F01D 11/10 20130101;
F01D 11/005 20130101; F01D 11/08 20130101; F05D 2240/50 20130101;
F01D 25/22 20130101 |
Class at
Publication: |
277/355 |
International
Class: |
F01D 11/08 20060101
F01D011/08 |
Claims
1. A seal assembly comprising: a first movable stator member
movable between a sealing position and a non-sealing position, a
second fixed stator member, the first stator member being movable
relative to the second stator member, the seal assembly further
comprising at least one flexure member coupled to the second stator
member, and at least one biasing member coupled between the at
least one flexure member and the movable stator for biasing the
movable stator to a non-sealing position.
2. The seal assembly of claim 1 having at least two flexure members
and two biasing members, each biasing member coupled to a flexure
member.
3. The seal assembly as claimed in claim 1, the second stator
comprising a base and a surface along the base, the first stator
comprising a sealing member that sealingly engages the contact
surface of said base.
4. The seal assembly of claim 3 wherein the first stator comprises
a yoke, said member being located in said yoke.
5. The seal assembly as claimed in claim 1 wherein the flexure
member is supported on a fastener member.
Description
FIELD OF THE INVENTION
[0001] The invention generally relates to gas turbine engines and
more specifically to seal assemblies used with gas turbine
engines.
BACKGROUND OF THE INVENTION
[0002] Gas turbine engines displace large volumes of pressurized
fluid, such as air through the engine fluid flowpath, during
operation. Seal assemblies prevent the fluid from leaking
undesirably by restricting fluid flow from areas of higher pressure
to areas of lower pressure. The seal assemblies may be positioned
between engine stationary and rotating members. The seals
compensate for transient variations in the gaps between adjacent
engine component parts.
[0003] Because of the working environment of the seal assemblies,
and/or the operating environment, at least some known seal
assemblies may deteriorate over time. If the seals do not provide
the required seal, fluid will leak past the seal detrimentally
affecting the operation of the engine. 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 engine components and
increase overall engine maintenance costs.
[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 discrete components comprising
such a seal assembly, such seal assemblies may be complex to
install in the engine, and the weight of such assemblies will
increase engine weight which has a direct negative impact on engine
performance. Moreover, because of the number of seal assembly
components, the operating efficiency of such seal assemblies may be
contingent on the tolerances between the rotating and stationary
members.
[0005] There is a need to develop a seal assembly that has
relatively few parts, effectively prevents leakage of fluid within
a turbine engine and does not deteriorate over time.
BRIEF DESCRIPTION OF THE INVENTION
[0006] A seal assembly comprising a first movable stator member
movable between a sealing position and a non-sealing position, a
second fixed stator member, the first stator member being movable
relative to the second stator member, the seal assembly further
comprising at least one flexure member coupled to the second stator
member, and at least one biasing member coupled between the at
least one flexure and the movable stator for biasing the movable
stator to a non-sealing position.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] While the specification concludes with claims particularly
pointing out and distinctly claiming the invention, it is believed
that the embodiments set forth herein will be better understood
from the following description in conjunction with the accompanying
figures, in which like reference numerals identify like elements,
and in which:
[0008] FIG. 1 is a schematic illustration of an exemplary gas
turbine engine;
[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, with a movable sealing member in a first position;
[0010] FIG. 3 is a cross-sectional view of the exemplary seal
assembly of FIG. 2 with the movable sealing member in a second
sealing position;
[0011] FIG. 4 is a cross-sectional view of an exemplary seal
assembly that may be used with the gas turbine engine shown in FIG.
1, with a movable sealing member in a first open position;
[0012] FIG. 5 is a cross-sectional view of the exemplary seal
assembly of FIG. 4 with the movable sealing member in a second
sealing position;
[0013] FIG. 6 is a front view of a flexure member useful with the
seal assembly;
[0014] FIG. 7 is an alternate embodiment flexure member useful with
the seal assembly;
[0015] FIG. 8 is a side view of the exemplary seal of FIG. 2, in a
first position;
[0016] FIG. 9 is an isometric view of the exemplary seal of FIG. 2,
in the first position;
[0017] FIG. 10 is an isometric view of the seal of FIG. 2 in the
second sealing position, similar to the cross-sectional view shown
in FIG. 3;
[0018] FIG. 11 is an isometric view of the second stator member
(102 of FIG. 2); and
[0019] FIG. 12 is an illustration of a possible alternate flexure
member.
DETAILED DESCRIPTION OF THE SPECIFICATION
[0020] 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.
[0021] Herein, the present invention seal assembly provides a
simplified seal with a reduced part count relative to prior art
seals thereby simplifying the seal assembly, and reducing the
weight of the seal assembly. For example, spring assemblies used in
related seal assemblies have been replaced by one or more flexure
members. As will be described herein the flexure member is attached
between a non-contact seal slide and a stator. Also, secondary seal
assemblies of prior art sealing devices have been replaced with a
single piston ring seal. The single ring seal may be retained
within either a fixed or sliding stators. The design may
incorporate one or more flexure members, the number thereof
depending upon the design requirement.
[0022] FIG. 1 is a schematic illustration of an exemplary gas
turbine engine 10 including a fan assembly 12 and a core engine 13
including a high pressure compressor 14, and a combustor 16. Engine
10 also includes a high pressure turbine 18, a low pressure turbine
20, and a booster 22. Fan assembly 12 includes an array of fan
blades 24 extending radially outward from a rotor disc 26. Engine
10 has an intake side 27 and an exhaust side 29. In one embodiment,
the gas turbine engine is a GE90-115B that is available from
General Electric Company, Cincinnati, Ohio. Fan assembly 12 and
turbine 20 are coupled by a first rotor shaft 31, and compressor 14
and turbine 18 are coupled by a second rotor shaft 33.
[0023] During operation, air flows axially through fan assembly 12,
in a direction that is substantially parallel to a central axis 34
extending through engine 10, and compressed air is supplied to high
pressure compressor 14. The highly compressed air is delivered to
combustor 16. Airflow (not shown in FIG. 1) from combustor 16
drives turbines 18 and 20, and turbine 20 drives fan assembly 12 by
way of shaft 31.
[0024] 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.
In one embodiment, rotating member 104 is a rotor that is rotatably
coupled within engine 10 to rotate about the axis of rotation 34.
Frame 103 is a stationary circumferential member positioned around
an axis of rotation 34 (not shown in FIG. 2). Frame member 103
includes an attachment flange 108 that extends outwardly away from
the frame. In one embodiment, frame 103 may be comprised of the
casing of gas turbine engine 10. As air flows through engine 10,
frame 103 is configured to help contain flowpath air.
[0025] Stationary stator member 102 of seal assembly 100 is a
stationary member that extends circumferentially around the axis of
rotation 34 of gas turbine engine 10. The stator is comprised of a
base 112 and a flange member 109. The base includes a base sealing
surface 90 and a stop surface 113. The flange and base are
perpendicular. As shown in FIG. 2, stationary stator member 102 is
fixed to frame 103 by fastener 107. The fastener may be comprised
of a conventional bolt member or other suitable fastening means.
The stator flange 109 and frame flange 108 are coupled by the
fastener member 107. A flexure member 150, which will be disclosed
in greater detail below is sandwiched between the head 190 of
fastener 107 and a surface 114 of flange 109 of fixed stator
102.
[0026] Seal assembly 100 also is comprised of moveable stator
member 110 includes a sealing face 124 and a plurality of sealing
teeth 127, 128 that extend outward from a portion of the sealing
face 124. The stator 110 is movable axially, in direction generally
represented by direction arrow 200 in FIG. 2. In the exemplary
embodiment, sealing face 124 is substantially parallel to a
rotating member surface 125 of rotating member 104. In a first
position shown in FIG. 2, the sealing face 124 is located at a
distance 123 away from rotating member 104. The movable stator 110
of seal assembly 100 is located in the first position when the
turbine engine is not in use with no fluid flowing through the
engine flowpath.
[0027] Moveable stator member 110 also includes an opening 135
defined therein. The opening extends in the axial direction 200
when the movable stator is correctly coupled with flange 108. As
shown in FIG. 2, the opening extends through the movable stator
surfaces 124 and contact surface 118. When the movable stator is in
the first, retracted position, surfaces 118 and 113 are in contact.
This contact between movable stator 110 and flange 108 controls the
displacement of the stator 110 to the first position.
[0028] In the exemplary embodiment, openings 135 are oriented
substantially perpendicular to rotating member surface 125. As
described below in more detail, openings 135 help to prevent
contact between the movable member 110, and specifically the
plurality of teeth 127, 128; and rotating member 104. The movable
stator may include any number of openings 135 but for purposes of
disclosing the exemplary embodiment, one or more openings 135 may
be included in movable stator 110. Moveable stator member 110
further includes at least one radially extending opening 134. For
purposes of disclosing the exemplary embodiment, a plurality of
openings 134 are illustrated. However, any suitable number of
radial openings 134 may be provided in stator 110. The opening 134
extends through surfaces 119 and 121 of the moveable stator member
110. In the exemplary embodiment, each opening 135 is located
adjacent openings 134.
[0029] Moveable stator member 110 also includes yoke 130. The yoke
extends radially and defines an opening 131 that receives a seal
member 132. The seal member may be made from any suitable sealing
material. As shown in FIGS. 2 and 3, when seated in opening 131, a
portion of the seal member extends beyond the free end 129 of the
yoke. When the movable and fixed stators are coupled as shown in
the figures, the end of the seal that extends beyond free end 129
is in sealing contact with contact surface 90 of the fixed stator
102. The seal member may be a piston ring seal, for example. Note
that in an alternate embodiment, the seal may be supported by
stator 102 and engage a sealing surface along the movable
member.
[0030] FIG. 3 shows the moveable stator member 110 in a second
position, also referred to herein as a sealing position. When air
is supplied to the gas turbine flowpath, the pressure of the air
causes the movable stator to be displaced in direction 200. As the
stator member is displaced, seal 132 remains in contact with
sealing surface 90. As the moveable stator moves toward member 104,
the magnitude of distance 123 is reduced from its maximum value
when the movable stator member is in the first position shown in
FIG. 2. As shown in FIG. 3, when the movable stator reaches the end
of travel and is in the second position, the sealing face 124 and
the rotating member surface 125 are proximate each other.
[0031] Seal assembly 100 also comprises at least one flexure member
150. The flexure member is substantially flat. As assembled, one
end of flexure member is located proximate the flange member 109.
This end is identified as 157 in FIGS. 2 and 3. Ends 157 and 152
are joined by biasing member 151. Member 151 is extendible from its
retracted length shown in FIG. 2 to an extended length as shown in
the sealing position of FIG. 3.
[0032] The flexure member 150 comprises a weak spring which flexes
out of plane to allow axial translation of the moveable stator
member 110 relative to the stationary stator member 102. The
connection of the flexure member 150 to the moveable stator member
110 is shown in these figures for simplicity as being bolted to the
frame 103, but integral with the moveable stator 110. It could
alternatively be a separate piece, but such a configuration may
increase weight, complexity, and part count.
[0033] FIGS. 9 and 10 show in isometric view (comparable to the
views of FIGS. 3 and 4) the bending of the flexure member (150
series of numbers). The flexure member is fixed to stationary
stator 108 by bolt connection 107. The flexure member also includes
a biasing portion 151 that is made integral with the movable stator
member 110 at flange 152. The flexure member 150 may be integral
with moveable stator member 110 and thereby cast with that member
110.
[0034] The flexure member 150 serves as a biasing mechanism for
moving the moveable stator member 110. The member 150 biases the
movable stator member toward the first position of FIG. 2. The
flexure member 150 returns the movable member to the first
non-sealing position when the air flow through the engine is
reduced to a minimum level or the engine is shut off. The flexure
member 150 also controls the translation of movable member 110 to
account for relative axial motion between the rotor 104 and the
stator 103 during engine operation. A flexure member 150 may be
pre-loaded against a stop (surface 113) such that in an
un-pressurized state the sealing face 124 is held in an open
position, e.g., when the turbine engine 10 has been disengaged into
the off position. This condition prevents slide contact of the
moveable stator member 110 with the rotor 104 at low or no
activation pressures, such contact, when unintended, operating to
damage the seal assembly 100 and thus hinder its performance.
[0035] FIG. 6 provides an exemplary flexure member 150. Flexure
member 150 may be made from one or more of known metals in the art
including steel, titanium, iron and nickel. As shown, the flexure
member 150 includes a central opening 183 that centers the moveable
stator member 110 about the engine axis 34, and seams 160 which are
openings that extend through the thickness of the flexure member
150. The seams 160 permit the flexure member 150 to flex or
displace in the desired manner, out of the plane of the Figure.
Such movement of the flexure member 150 biases a moveable stator
member 110 in the required direction for example to either open or
close the seal assembly 100 as directed or required.
[0036] As shown in FIG. 6, the flexure member includes three seam
segments 160, however any number of seams in may be provided. In
the present embodiment, each of the seams comprises two arcuate
segments 190, 191 that are joined by a non-arcuate segment 192. The
non-arcuate portion is oriented radially. As shown in FIG. 6, for a
single seam, one of the arcuate segments of each adjacent seam in
the clockwise and counterclockwise directions relative to the
single seam, is located in parallel to the arcuate segments of the
single seam, and are separated by a radial distance approximately
equal to the length of the radial segment 192. The flexure member
150 may be configured to be an annular member as shown in FIG. 6
with central opening 183 that receives the moveable stator member
110. Additionally the flexure member may have any suitable seam
arrangement. Alternative designs for the seams are illustrated in
FIGS. 7 and 12.
[0037] The seams 160 are openings within each flexure member 150
that have been cut therein into a pattern determined beforehand as
suitable to enable the flexure member 150 to flex and therefore
bias as required. A suitable method for cutting the seams 160 into
the flexure member 150 is by electro discharge machining which
process is well known by persons of skill in the art. It is noted
herein, though, that the methodology for cutting the seams 160 into
the flexure member 150 forms no part of the invention herein. In
another embodiment herein, a flexure member 150 may be cast such
that the seams 160 are a byproduct of the casting process; i.e.,
cast such that the openings are part of the process.
[0038] FIG. 7 provides a cut-out of a portion of an alternate
configuration of the flexure member 150 of FIG. 6. In particular, a
portion of a seam 160 is shown enlarged. Herein, each darkened line
of the seam 160 represents an opening through the flexure member
150. FIG. 6 illustrates a possible configuration of a flexure
member 150(spring). Taking a sheet of material and cutting the
indicated slots in it allows a small force to displace the center
of the sheet (feature 152 of FIG. 2) out of plane from the
periphery of the sheet (feature 150 of FIG. 2). FIG. 7 shows an
alternative configuration of these cuts. An infinite number of
possible configurations are possible, of which the ones shown in
FIGS. 6, 7, and 12 are shown as examples.
[0039] FIGS. 4 and 5 show an alternate embodiment seal assembly 100
of the present invention. FIG. 4 shows the movable stator in a
first non-sealing position and FIG. 5 shows the movable stator in a
second, sealing position. The seal 100 includes flexure members 150
located at opposite ends of an elongate fastener 107. The flexure
members are separated by spacer 155 that is slidably located on the
fastener 107. In this alternate configuration, flexure members 150
are positioned in a parallel orientation and are held apart by a
spacer 155. Spacer 155 is a useful but not required device between
the two flexure members 150.
[0040] The flexure members 150 always act to open the seal (moving
the movable stator member 110 to the position shown in FIG. 4). Air
pressures during engine operation overcome the spring forces of the
flexure members 150 to move the moveable stator member 110 to the
closed position (FIG. 5).
[0041] As shown in FIGS. 4 and 5, two flexible members 151 are
coupled between ends 150 and 152 as described in conjunction with
the description of seal assembly 100. Both members 151 extend when
the movable stator is displaced in direction 200 to a sealing
position. Additionally, seal 132 is in sealing contact with surface
90 of fixed stator base 102.
[0042] During operation, cooling air and/or fluids flow through gas
turbine engine 10. When engine 10 is in operation, high pressure
air flows toward the aft engine end 29. 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. The pressures acting on the
moveable stator member 110 are such that the pressure forces
overcome the spring force of the flexure member 151, and the
moveable stator member 110 will translate from the first position
(shown in FIGS. 2 and 4) to the second, sealing position (FIGS. 3
and 5).
[0043] Additionally, during operation, a portion of the high
pressure air flows through openings 135. In the exemplary
embodiment, opening 135 is a plurality of feed openings. Openings
135 form a high pressure film or air bearing between surfaces 124
and rotating member surface 125. The air bearing prevents moveable
stator member 110 from contacting rotating member 104.
[0044] After air flows through opening 135, the air exits to the
region of lower pressure 140. Also, a portion of air may leak past
seal teeth 126, 127, 128. Air that leaks past seal teeth 126, 127,
128 and that portion of the air that has exited opening 135 and
flows radially outward, flows through radial openings 134 to the
region of lower pressure 140.
[0045] 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.
* * * * *