Note: Descriptions are shown in the official language in which they were submitted.
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SEAL WITH COOLING FEATURE
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application claims priority to and the benefit of U.S.
Provisional
Patent Application Number 62/040,545, filed 22 August 2014 and to U.S. Utility
Patent Application Number 14/820,686, filed 07 August 2015, the disclosures of
which are expressly incorporated herein by reference.
FIELD OF THE DISCLOSURE
[0002] The present disclosure relates generally to seals, and more
specifically to seals for use in gas turbine engines.
BACKGROUND
[0003] Gas turbine engines are used to power aircraft, watercraft, power
generators, and the like. Gas turbine engines typically include a compressor,
a
combustor, and a turbine. The compressor compresses air drawn into the
engine and delivers high-pressure air to the combustor. In the combustor, fuel
is
mixed with the high-pressure air and is ignited. Products of the combustion
reaction in the combustor are directed into the turbine where work is
extracted to
drive the compressor and, sometimes, an output shaft. Left-over products of
the
combustion are exhausted out of the turbine and may provide thrust in some
applications.
[0004] Compressors and turbines typically include seals to control the flow
between fluid cavities formed in the engine. As an example, some turbines
include rotating wheel assemblies and static shrouds arranged around the
rotating wheel assemblies. Each static shroud may include a plurality of
segments arranged around an axis of the turbine to form a ring around the
rotating wheel assembly. Seals may be positioned between neighboring
segments to block fluid from moving radially through gaps formed between each
of the segments.
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SUMMARY
[0005] The present disclosure may comprise one or more of the following
features and combinations thereof.
[0006] A shroud ring for a use in a turbine of a gas turbine engine may
include a first shroud segment, a second shroud segment, and a strip seal. The
second shroud segment may be spaced apart circumferentially from the first
shroud segment to form a gap therebetween. The strip seal may be arranged to
extend across the gap and block a first flow of fluid through the gap and
direct a
second flow of fluid through the gap toward the second shroud segment.
[0007] In some embodiments, the strip seal may include a first strip
received in a first seal slot formed in the first shroud segment, a second
strip
received in a second seal slot formed in the second shroud segment, and a flow-
control band that extends between and interconnects the first and second
strips.
[0008] In some embodiments, the flow-control band may include a flow
blocker arranged to block the first flow of fluid through the gap and a flow
guide
arranged to direct the second flow of fluid through the gap and toward the
second
shroud segment.
[0009] In some embodiments, the flow guide may include a guide sheet
and a first cooling passage formed in the guide sheet. The first cooling
passage
may be arranged to extend through the guide sheet. The guide sheet may
include an outer surface, an inner surface radially spaced apart from the
outer
surface, and a passage sidewall extending between and interconnecting the
outer and inner surfaces to define the first cooling passage.
[0010] In some embodiments, the passage sidewall and the inner surface
may define an angle a therebetween and the angle a may be less than 90
degrees.
[0011] In some embodiments, the outer surface may be formed to include
an inlet aperture arranged to open into the first cooling passage. The inner
surface may be formed to include an outlet aperture arranged to open into the
first cooling passage. The inlet aperture may have a circular shape when
viewed
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from a position radially outward of the outer surface looking toward a central
axis
of the shroud ring.
[0012] In some embodiments, the strip seal may have a longitudinal axis
located about midway between the first and second strips. The inlet aperture
may include an inlet center point and the inlet center point may lie on the
longitudinal axis.
[0013] In some embodiments, the outlet aperture may have a circular
shape when viewed from a position radially inward of the inner surface looking
toward the central axis. The outlet aperture may include an outlet center
point
and the outlet center point is spaced apart from the longitudinal axis.
[0014] In some embodiments, the flow guide may include a guide sheet
and a first cooling passage formed in the guide sheet, the first cooling
passage is
arranged to extend through the guide sheet. The guide sheet may include a
forward sidewall and a rear sidewall spaced apart from the forward sidewall.
The
first shroud segment, the second shroud segment, the forward sidewall, and the
rear sidewall may cooperate to define the first cooling passage.
[0015] According to another aspect of the present disclosure, a strip seal
for use in a shroud ring of a turbine may comprise a first strip, a second
strip, and
a flow-control band. The second strip may be spaced apart from the first
strip.
The flow-control band may be arranged to extend between and interconnect the
first and second strips. The flow-control band may include a flow blocker
arranged to block a first flow of fluid through the strip seal and a flow
guide
arranged to allow a second flow of fluid to pass through the strip seal away
from
the first strip toward the second strip.
[0016] In some embodiments, the flow guide may include a guide sheet
and a first cooling passage formed in the guide sheet. The guide sheet may
include an outer surface and an inner surface spaced apart from the outer
surface. The outer surface may be formed to include an inlet aperture arranged
to open into the first cooling passage. The inner surface may be formed to
include an outlet aperture arranged to open into the first cooling passage.
The
inlet aperture may have a circular shape.
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[0017] In some embodiments, the strip seal may have a longitudinal axis
located about midway between the first and second strips. The inlet aperture
may include an inlet center point and the inlet center point may lie on the
longitudinal axis.
[0018] In some embodiments, the strip seal may have a longitudinal axis
located about midway between the first and second strips. The inlet aperture
may include an inlet center point and the inlet center point may be spaced
apart
from the longitudinal axis.
[0019] In some embodiments, the strip seal may have a longitudinal axis
located about midway between the first and second strips. The entire inlet
aperture may be spaced apart from the longitudinal axis.
[0020] In some embodiments, the outlet aperture may include an outlet
center point. The outlet center point may be spaced apart from the
longitudinal
axis.
[0021] In some embodiments, the outlet aperture may be spaced apart
axially from the inlet aperture relative to the longitudinal axis.
[0022] In some embodiments, the outlet aperture may include an outlet
center point. The outlet center point may be spaced apart from the
longitudinal
axis.
[0023] In some embodiments, the entire outlet aperture may be spaced
apart from the longitudinal axis.
[0024] In some embodiments, the flow guide may include a guide sheet
and a first cooling passage formed in the guide sheet. The guide sheet may
include an inlet aperture that opens into the cooling passage. The inlet
aperture
may be oval shaped.
[0025] In some embodiments, the flow guide may include a guide sheet
and a first cooling passage formed in the guide sheet. The guide sheet may
include an inlet aperture that opens into the cooling passage. The inlet
aperture
may be rectangle shaped.
[0026] In some embodiments, the second flow of fluid may include a first
portion of air and a second portion of air. The flow guide may include a guide
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sheet formed to include a first cooling passage and a second cooling passage.
The first cooling passage may be arranged to direct the first portion of air
through
the seal strip toward the second strip. The second cooling passage may be
spaced apart from the first cooling passage and arranged to direct the second
portion of air through the strip seal toward the first strip.
[0027] In some embodiments, the guide sheet may include an outer
surface formed to include a second inlet aperture that opens into the second
cooling passage and an inner surface formed to include a second outlet
aperture
that opens into the second cooling passage. The second inlet aperture may
have a circular shape.
[0028] In some embodiments, the strip seal may have a longitudinal axis
located about midway between the first and second strips. The outer surface
may be formed to further include a first inlet aperture that opens into the
first
cooling passage. The first inlet aperture may be spaced apart axially from the
second inlet aperture relative to the longitudinal axis.
[0029] In some embodiments, the strip seal may have a longitudinal axis
located about midway between the first and second strips. The outer surface
may be formed to further include a first inlet aperture that opens into the
first
cooling passage. The first inlet aperture may be spaced apart
circumferentially
from the second inlet aperture relative to the longitudinal axis.
[0030] According to another aspect of the present disclosure, a method of
making a strip seal may comprise the steps of providing a strip of material
including a first strip, a second strip, and a flow-control band extending
between
and interconnecting the first and second strips and forming a flow guide in
the
flow-control band. The flow guide may include a cooling passage. The cooling
passage may be arranged to extend through the strip seal to direct cooling air
away from the first strip and toward the second strip.
[0031] These and other features of the present disclosure will become
more apparent from the following description of the illustrative embodiments.
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BRIEF DESCRIPTION OF THE DRAWINGS
[0032] Fig. 1 is a cutaway view of a gas turbine engine including a turbine
for extracting work from hot high-pressure products to power a fan assembly
and
a compressor included in the engine and showing that the turbine includes a
plurality of rotating wheel assemblies and a plurality of static shroud rings
arranged around the rotating wheel assemblies to insulate the outer band from
the hot high-pressure products and to provide a desired dimensional tolerance
between the rotating wheel assembly and the shroud ring;
[0033] Fig. 2 is a cutaway view of a portion of the turbine included in the
gas turbine engine of Fig. 1 showing that the portion of the turbine includes
an
outer band, one of the rotating wheel assemblies, and one of the associated
static shroud rings positioned radially between the outer band and the
rotating
wheel assembly and further showing that the shroud ring includes a plurality
of
shroud segments arranged around a central axis of the engine and a plurality
of
strip seals positioned in a gap between each neighboring pair of shroud
segments as suggested in Fig. 3;
[0034] Fig. 3 is a sectional view taken along line 3-3 of Fig. 2 showing a
first shroud segment, a second shroud segment, and the strip seal located
between the first and second shroud segments and suggesting that the strip
seal
includes a flow guide configured to direct cooling air through the strip seal
toward
an inner surface of the second shroud segment to cool the inner surface and
minimize oxidation of the second shroud segment as hot high-pressure products
move past the inner surface of the shroud ring;
[0035] Fig. 4 is an exploded perspective view of the portion of the shroud
ring of Fig. 3 showing that the shroud ring includes the first shroud segment,
the
second shroud segment, and the strip seal arranged to lie in corresponding
slots
formed in the first and second shroud segments;
[0036] Fig. 5 is a side elevation view of the turbine of Fig. 1 showing
that
the turbine includes the outer band, the shroud ring, and the rotating wheel
assembly and that the turbine assembly further includes a static vane assembly
spaced apart axially forward from the rotating wheel assembly;
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[0037] Fig. 6 is a cutaway view of the shroud ring similar to Fig. 3
showing
that the strip seal extends between the first and second shroud segments to
close the gap therebetween and the flow guide included in the strip seal
includes
a plurality of cooling passages to direct cooling air through the strip seal
toward
the second shroud segment;
[0038] Fig. 7 is a top plan view of the strip seal of Fig. 6 showing that
the
strip seal includes a flow blocker arranged to block a first flow of fluid
through the
gap and a flow guide arranged to allow a second flow of fluid through the gap
and to direct the second flow toward the second shroud segment;
[0039] Fig. 8 is a top plan view of another the strip seal in accordance
with
the present disclosure showing that the strip seal includes a flow blocker
arranged to block a first flow of fluid through the gap and a flow guide
arranged to
allow a second flow of fluid through the gap and direct the second flow toward
the first and second shroud segments;
[0040] Fig. 9 is a perspective view of another strip seal in accordance
with
the present disclosure showing that the strip seal includes a flow blocker and
a
flow guide formed to include two circular cooling passages and two oval shaped
cooling passages;
[0041] Fig. 10 is a perspective view of another strip seal in accordance
with the present disclosure showing that the strip seal includes a first body
and a
second body spaced apart from the first body to form the flow guide
therebetween; and
[0042] Fig. 11 is a perspective view of another strip seal in accordance
with the present disclosure showing that the strip seal includes a flow
blocker and
a flow guide and the flow guide is formed to include a rectangular shaped
cooling
passage.
DETAILED DESCRIPTION OF THE DRAWINGS
[0043] For the purposes of promoting an understanding of the principles of
the disclosure, reference will now be made to a number of illustrative
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embodiments illustrated in the drawings and specific language will be used to
describe the same.
[0044] A strip seal 14 for use in a gas turbine engine 100 is arranged to
control a flow of fluid between cavities formed in the engine 100 as suggested
in
Fig. 1. The illustrative gas turbine engine 100 includes an engine core 120
and a
fan assembly 130 mounted illustratively to the engine core 120 to be driven by
the engine core 120. The engine core 120 includes at least two cavities and a
plurality of strip seals 14 arranged to control the flow of fluid moving
between the
two cavities. In the illustrative embodiment, the strip seals 14 are included
in a
shroud ring 10 arranged around rotating wheel assemblies 134. In other
embodiments, the strip seals 14 are included in other components of the engine
100. As an example, the strip seals 14 may be included in static vanes of a
high-
pressure turbine included in the engine core 120.
[0045] The engine core 120 includes a compressor 122, a combustor 124,
and a turbine 126 arranged along a central axis 20 of the engine 100. The
compressor 122 is configured to compress and deliver air to the combustor 124.
The combustor 124 is configured to mix fuel with the compressed air received
from the compressor 122 and to ignite the fuel. The hot high-pressure products
of the combustion reaction in the combustor 124 are directed into the turbine
126
where the turbine 126 extracts work to drive the compressor 122 and the fan
assembly 130.
[0046] The turbine 126 includes an outer band 132, a plurality of rotating
wheel assemblies 134 arranged along the central axis 20, and a plurality of
associated shroud rings 10 arranged around the rotating wheel assemblies 134
as shown in Figs. 1 and 2. The outer band 132 and the shroud rings 10 extend
around the central axis 20 of the engine 100 to define a case 136. The
rotating
wheel assemblies 134 are arranged to rotate as a result of the hot high-
pressure
products passing through the turbine 126. The rotating wheel assemblies 134
rotate within the case 136 to power the fan assembly 130 and the compressor
122.
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[0047] Each shroud ring 10 includes a plurality of shroud segments 12 and
a plurality of strip seals 14 as shown in Figs. 3 and 4. The shroud segments
12
extend around the central axis 20 circumferentially to insulate the outer band
132
from the hot high-pressure products and to provide a desired dimensional
tolerance between the blades of the rotating wheel assembly 134 and the outer
band 132 as shown in Fig. 2. The strip seals 14 are positioned between
neighboring shroud segments 12 to block a first flow of fluid from moving
radially
through gaps 18 formed between each of the shroud segments 12 and to direct a
second flow of fluid through the gaps 18 as shown in Fig. 3.
[0048] Illustratively, the shroud segments 12 extend around the central
axis 20 to form a full ring as shown in Fig. 2. Each shroud segment 12 is
spaced
apart from the adjacent shroud segment 12 to form the gap 18 therebetween as
shown in Fig. 3. Each strip seal 14 is received in a neighboring pair of
shroud
segments 12 to block the first flow of fluid from passing through the gap 18
formed between the pair of shroud segments 12 and to allow the second flow of
fluid to pass through the gap 18.
[0049] In the illustrative embodiment, the strip seal 14 extends between a
first shroud segment 12A and a second shroud segment 12B that is spaced apart
from the first shroud segment 12A as shown in Fig. 3. A source of cooling air
22
provides the first and second flows of fluid into the gap 18. The strip seal
14
blocks the first flow of fluid from passing through the strip seal 14. The
strip seal
14 allows the second flow of fluid to pass through the strip seal 14 and
directs the
second flow of fluid toward the second shroud segment 12B.
[0050] The first ring segment 12A is spaced apart radially from the central
axis 20 to form a portion of the shroud ring 10 as shown in Figs. 2-4. The
first
ring segment 12A includes an inner sidewall 26A, an outer sidewall 28A, a body
30A that extends between the inner and outer sidewalls 26A, 28A, and a first
seal slot 32A as shown in Fig. 4.
[0051] The inner sidewall 26A is spaced apart circumferentially from the
second ring segment 12B to form the gap 18 therebetween as shown in Figs. 3
and 4. The outer sidewall 28A is spaced apart circumferentially from another
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shroud segment 12 (not shown). The body 30A provides a desired dimensional
tolerance between the blades of the rotating wheel assembly 134 and the outer
band 132 as suggested in Fig. 5. The body 30A insulates the outer band 132
from the hot high-pressure products being passed through the turbine 126. The
first seal slot 32A opens into the inner sidewall 26A and extends into the
body
30A circumferentially as shown in Fig. 4.
[0052] The first seal slot 32A receives a portion of the strip seal 14 as
shown in Figs. 3 and 4. In the illustrative embodiment, the first seal slot
32A
includes a radial outer surface 34A, a radial inner surface 36A spaced apart
radially from the radial outer surface 34A, and an intermediate surface 38A
that
extends between and interconnects the radial outer and radial inner surfaces
34A, 36A.
[0053] The second ring segment 12B is substantially similar to the first
ring
segment 12A. As such, the second ring segment 12B is not discussed in detail.
[0054] The strip seal 14 has a longitudinal axis 40, a forward end 42, and
a rearward end 44 spaced apart axially from the forward end 42 along the
longitudinal axis 40 as shown in Fig. 7. In some embodiments, the strip seal
14
is curved or includes a curved portion. In the illustrative embodiment, a
first
portion of the strip seal 14 extends axially relative to the central axis 20
and a
second portion of the strip seal 14 extends axially and radially relative to
the
central axis 20 as shown in Fig. 4. In other embodiments, the strip seal 14 is
about flat.
[0055] The strip seal 14 includes a first strip 46, a second strip 48, and
a
flow-control band 50 that extends between the first and second strips 46, 48
as
shown in Fig. 7. The first strip 46 is received in the first seal slot 32A to
couple
the strip seal 14 to the first ring segment 12A. The second strip 48 is
received in
the second seal slot 32B to couple the strip seal 14 to the second ring
segment
12B. The flow-control band 50 controls the flow of fluid provided into the gap
18
by the cooling source.
[0056] The first strip 46 is received in the first seal slot 32A formed in
the
first ring segment 12A as shown in Fig. 7. The first strip 46 is coupled to
the first
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ring segment 12A and the flow-control band 50 to locate the flow-control band
50
in the gap 18 as shown in Fig. 6.
[0057] The first strip 46 extends along the longitudinal axis 40 between
the
forward end 42 and the rearward end 44 of the strip seal 14 as shown in Fig.
7.
In the illustrative embodiment, the first strip 46 is continuous. The first
strip46
illustratively engages the radial outer and inner surfaces 34A, 36A of the
first seal
slot 32A as suggested in Fig. 6. In some embodiments, the first strip 46 may
engage only one of the radial outer and inner surfaces 34A, 36A of the first
seal
slot 32A and/or may intermittently engage with one or more of the radial outer
and inner surfaces 34A, 36A of the first seal slot 32A along the length of the
first
strip 46. As a result, the circumferential movement of the first strip 46 into
the
first seal slot 32A is limited. The intermediate surface 38A is arranged to
engage
the first strip 46 to block circumferential movement of the strip seal 14.
[0058] The second strip 48 is received in the second seal slot 32B formed
in the second ring segment 12B as shown in Fig. 6. The second strip 48 is
coupled to the second ring segment 12B and the flow-control band 50 to locate
the flow-control band 50 in the gap 18 as shown in Fig. 6.
[0059] The second strip 48 extends along the longitudinal axis 40 between
the forward end 42 and the rearward end 44 of the strip seal 14 as shown in
Fig.
7. In the illustrative embodiment, the second strip 48 is continuous. The
second
strip 48 illustratively engages the radial outer and inner surfaces 34B, 36B
of the
second seal slot 32B as suggested in Fig. 6. In some embodiments, the second
strip 48 may engage only one of the radial outer and inner surfaces 34B, 36B
of
the second seal slot 32B and/or may intermittently engage with one or more of
the radial outer and inner surfaces 34B, 36B of the second seal slot 32B along
the length of the second strip 48. As a result, the circumferential movement
of
the second strip 48 into the second seal slot 32B is limited. The intermediate
surface 38B is arranged to engage the second strip 48 to block circumferential
movement of the strip seal 14.
[0060] The flow-control band 50 extends between the first and second
strips 46, 48 to close the gap 18 as shown in Fig. 6. The flow-control band 50
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includes a flow blocker 52 and a flow guide 54 as shown in Fig. 7. The flow
blocker 52 blocks the first flow of fluid through the gap 18. The flow guide
54
allows the second flow of fluid through the gap 18 and directs the second flow
of
fluid in a desired direction. In the illustrative embodiment, the flow guide
54
directs the second flow of fluid away from the first shroud segment 12A toward
the second shroud segment 12B. However, it is within the scope of the present
disclosure for the flow guide to direct the second flow of fluid away from the
second shroud segment toward the first shroud segment.
[0061] The flow blocker 52 extends along the longitudinal axis 40 as
shown in Fig. 7. The flow blocker 52 is continuous to block the first flow of
fluid
from passing through the strip seal 14. In the illustrative embodiment the
flow
blocker 52 includes a first leg 56 and a second leg 58 spaced apart from the
first
leg 56 to locate the flow guide 54 therebetween. The first leg 56 extends
between and interconnects the first and second strips 46, 48 adjacent the
forward end 42 of the strip seal 14. The second leg 58 extends between and
interconnects the first and second strips 46, 48 adjacent the rearward end 44
of
the strip seal 14.
[0062] The flow guide 54 extends between and interconnects the first and
second legs of the flow blocker 52 as shown in Fig. 7. The flow guide 54 is
arranged to allow the second flow of fluid to pass through the gap 18.
Illustratively, the flow guide 54 is formed to include a guide sheet 60 and a
plurality of cooling passages 62 that extend through the guide sheet 60. In
other
embodiments, the flow guide 54 includes a single cooling passage 62 as shown
in Fig. 10 for example.
[0063] The guide sheet 60 includes an outer surface 64, an inner surface
66, and a plurality of passage sidewalls 68 as shown in Figs. 6 and 7. The
inner
surface 66 is spaced apart radially from the outer surface 64 relative to the
central axis 20. Each of the plurality of passage sidewalls 68 extend between
and interconnect the outer and inner surfaces 64, 66 to define the cooling
passages 62. In the illustrative embodiment, each passage sidewall 68 is
continuous.
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[0064] In the illustrative embodiment, the passage sidewall 68 and the
inner surface 66 define an angle a therebetween. In some embodiments, the
angle a is less than 90 degrees. In the illustrative embodiment, the angle a
is
about 50 degrees. In other embodiments, the angle a is between about 0
degrees and about 90 degrees. In some embodiments, the angle a is between
about 30 degrees and about 70 degrees.
[0065] The outer surface 64 is formed to include a plurality of inlet
apertures 72. Each inlet aperture 72 opens into a cooling passage 62. In the
illustrative embodiment, the inlet aperture 72 has a circular cross section
when
viewed from a position radially outward of the outer surface 64 looking toward
the
central axis 20 as shown in Fig. 7. The circular inlet aperture 72 has an
inlet
center point 78 as shown in Fig. 7. In the illustrative embodiment, the inlet
center
point 78 lies on the longitudinal axis 40.
[0066] In other embodiments, the inlet center point is spaced apart from
the longitudinal axis. For example, another embodiment of a strip seal 214
including an inlet aperture having an inlet center point spaced apart from the
longitudinal axis 240 is shown in Fig. 8. The inlet center points may be
spaced
apart from the longitudinal axis 240 circumferentially, axially, or both
circumferentially and axially. As shown in Fig. 8, in some embodiments, the
entire inlet aperture is spaced apart from the longitudinal axis 240.
[0067] In other embodiments, the inlet aperture may have a plurality of
shapes. For example, another embodiment of a strip seal 314 is shown in Fig.
9.
The inlet aperture of the strip seal 314 has an oval cross section when viewed
from a position radially outward from the outer surface relative to the
central axis
as shown in Fig. 9. In other embodiments, such as, for example, strip seals
414,
514 shown in Figs. 10 and 11, the inlet aperture has a rectangle cross section
when viewed from a position radially outward from the outer surface looking
toward the central axis.
[0068] In particular, the strip seal 414 includes a flow guide 454 as
shown
in Fig. 10. The flow guide 454 includes a guide sheet 460 and a cooling
passage
462 formed in the guide sheet 460. The cooling passage 462 is arranged to
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extend through the guide sheet 460. The guide sheet 460 includes a forward
sidewall 468F and a rear sidewall 468R spaced apart from the forward sidewall
468F. The first shroud segment 12A, the second shroud segment 12B, the
forward sidewall 468F, and the rear sidewall 468R cooperate to define the
cooling passage 462. As such, the inlet aperture has a rectangular cross
section
when viewed from a position radially outward from the outer surface looking
toward the central axis.
[0069] The inner surface 66 is formed to include a plurality of outlet
apertures 74 as shown in Fig. 6. Each outlet aperture 74 opens into a cooling
passage 62. In the illustrative embodiment, the outlet aperture 74 has a
circular
cross section when viewed from a position radially inward of the inner surface
66
looking toward the central axis. The circular outlet aperture 74 has an outlet
center point. In the illustrative embodiment, the outlet center point is
spaced
apart from the longitudinal axis 40. The outlet center point may be spaced
apart
from the longitudinal axis 40 circumferentially, axially, or both
circumferentially
and axially.
[0070] As shown in Fig. 8, the center points may be spaced apart from the
longitudinal axis 240 circumferentially, axially, or both circumferentially
and
axially. In some embodiments, the entire outlet aperture is spaced apart from
the
longitudinal axis 240 as shown in Fig. 8.
[0071] In other embodiments, the outlet aperture may have a plurality of
shapes. For example, the outlet aperture of the strip seal 314 has an oval
cross
section when viewed from a position radially inward of the inner surface
looking
toward the central axis as shown in Fig. 9. In other embodiments, such as
strip
seals 414, 514, the outlet aperture has a rectangle cross section when viewed
from a position radially inward of the inner surface looking toward the
central axis
as shown in Figs. 10 and 11.
[0072] A method of making a strip seal 14 comprises a first step and a
second step. In the first step, a strip of material including the first strip
46, the
second strip 48, and a flow-control band 50 extending between and
interconnecting the first and second strips 46, 48 is provided. In the second
step,
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the flow guide 54 is formed in the flow-control band 50. The flow guide
includes
a cooling passage 62. The cooling passage 62 is arranged to extend through the
strip seal 14 to direct cooling air away from the first strip 46 and toward
the
second strip 48.
[0073] A method of cooling an inner surface of a shroud ring 10 comprises
a plurality of steps. In a first step, cooling air is provided into the gap
18. The
cooling air includes the first flow of fluid and the second flow of fluid. In
a second
step, the first flow of fluid is blocked from passing through the strip seal
14. In a
third step, the second flow of fluid is directed through the strip seal 14
toward the
second shroud segment 12B.
[0074] Another illustrative strip seal 214 for use in the engine system 100
is shown in Fig. 8. The strip seal 214 is substantially similar to the strip
seal 14
shown in Figs. 1-7 and described herein. Accordingly, similar reference
numbers
in the 200 series indicate features that are common between the strip seal 14
and the strip seal 214. The description of the strip seal 14 is hereby
incorporated
by reference to apply to the strip seal 214, except in instances when it
conflicts
with the specific description and drawings of the strip seal 214.
[0075] The strip seal 214 includes a plurality of cooling passages 262 as
shown in Fig. 8. The cooling passages 262 include circular shaped inlet
apertures 272 and outlet apertures 274.
[0076] The center point of the inlet aperture 272 of the first cooling
passage 262A lies on the longitudinal axis 240. The center point of the outlet
aperture 274 of the first cooling passage 262A is spaced apart from the
longitudinal axis 240 to direct the cooling air toward the second shroud
segment
12B.
[0077] The center point of the inlet aperture 272 of the second cooling
passage 2628 lies on the longitudinal axis 240. The center point of the outlet
aperture 274 of the second cooling passage 262B is spaced apart
circumferentially from the longitudinal axis 240 to direct the cooling air
toward the
first shroud segment 12A.
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[0078] The entire inlet aperture 272 of the third cooling passage 2620 is
spaced apart from the longitudinal axis 240. The entire outlet aperture 274 of
the
third cooling passage 262C is spaced apart circumferentially from the
longitudinal
axis 240. The outlet aperture 274 is spaced apart axially from the inlet
aperture
272 relative to the longitudinal axis 240.
[0079] The center point of the inlet aperture 272 of the fourth cooling
passage 262D is spaced apart from the longitudinal axis 240. The center point
of
the outlet aperture 274 of the fourth cooling passage 262D is spaced apart
circumferentially and axially from the longitudinal axis 240.
[0080] Another illustrative strip seal 314 for use in the engine system
100
is shown in Fig. 9. The strip seal 314 is substantially similar to the strip
seal 14
shown in Figs. 1-7 and described herein. Accordingly, similar reference
numbers
in the 300 series indicate features that are common between the strip seal 14
and the strip seal 314. The description of the strip seal 14 is hereby
incorporated
by reference to apply to the strip seal 314, except in instances when it
conflicts
with the specific description and drawings of the strip seal 314.
[0081] The guide sheet 360 includes an outer surface 364 and an inner
surface 366 as shown in Fig. 9. The outer surface 364 is formed to include an
inlet aperture that opens into a cooling passage 362. The inlet aperture is
oval
shaped when viewed from a position radially outward from the outer surface 264
looking toward the central axis 20. The inner surface 366 is formed to include
an
outlet aperture and the outlet aperture is oval shaped when viewed from a
position radially inward of inner surface 366 looking toward the central axis
20.
[0082] Another illustrative strip seal 414 for use in the engine system
100
is shown in Fig. 10. The strip seal 414 is substantially similar to the strip
seal 14
shown in Figs. 1-7 and described herein. Accordingly, similar reference
numbers
in the 400 series indicate features that are common between the strip seal 14
and the strip seal 414. The description of the strip seal 14 is hereby
incorporated
by reference to apply to the strip seal 414, except in instances when it
conflicts
with the specific description and drawings of the strip seal 414.
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[0083] The flow guide 454 includes the guide sheet 460 and a cooling
passage 462 formed in the guide sheet 460 as shown in Fig. 10. The cooling
passage 462 is arranged to extend through the guide sheet 460. The guide
sheet 460 includes a forward sidewall 468F and a rear sidewall 468R spaced
apart from the forward sidewall 468F. The first shroud segment 12A, the second
shroud segment 12B, the forward sidewall 468F, and the rear sidewall 468R
cooperate to define the cooling passage 462.
[0084] Another illustrative strip seal 514 for use in the engine system 100
is shown in Fig. 11. The strip seal 514 is substantially similar to the strip
seal 14
shown in Figs. 1-7 and described herein. Accordingly, similar reference
numbers
in the 500 series indicate features that are common between the strip seal 14
and the strip seal 514. The description of the strip seal 14 is hereby
incorporated
by reference to apply to the strip seal 514, except in instances when it
conflicts
with the specific description and drawings of the strip seal 514.
[0085] The flow guide 554 includes the guide sheet 560 and a cooling
passage 562 formed in the guide sheet 560 as shown in Fig. 11. The cooling
passage 562 is arranged to extend through the guide sheet 560. The guide
sheet 560 includes an outer surface 564, an inner surface 566, and a passage
sidewall 568. The outer surface 564 is formed to include the inlet aperture
572
that opens into the cooling passage 562. The inlet aperture 572 is rectangular
shaped when viewed from a position radially outward from the outer surface 564
looking toward the central axis 20. The inner surface 566 is formed to include
the outlet aperture 574 that opens into the cooling passage 562. The outlet
aperture 574 is rectangular shaped when viewed from a position radially inward
of the inner surface 566 looking toward the central axis 20.
[0086] While the disclosure has been illustrated and described in detail in
the foregoing drawings and description, the same is to be considered as
exemplary and not restrictive in character, it being understood that only
illustrative embodiments thereof have been shown and described and that all
changes and modifications that come within the spirit of the disclosure are
desired to be protected.
