[0001] The present invention relates generally to seals, and more particularly to a spline
seal for a turbine.
[0002] Turbines include gas and steam turbines. Gas turbines include, but are not limited
to, gas turbine power generation equipment and gas turbine aircraft engines.
[0003] A gas turbine has a gas path which typically includes, in serial-flow relationship,
an air intake (or inlet), a compressor, a combustor, a turbine, and a gas outlet (or
exhaust nozzle). Gas-path leakage occurs through gaps between gas turbine subassemblies
such as through gaps between the combustor and the turbine, and gas-path leakage occurs
through gaps between the components that make up a gas turbine subassembly, such as
through gaps between combustor casing segments. Such components and subassemblies
have surfaces of different shapes, suffer from assembly misalignment, and undergo
vibration. Hot-section components thermally experience hot gas flow and typically
undergo different thermal growths.
[0004] Gas leakage, either out of the gas path or into the gas path, from an area of higher
pressure to an area of lower pressure, is generally undesirable. For example, gas-path
leakage in the turbine or compressor area of a gas turbine, between the rotor of the
turbine or compressor and the circumferentially surrounding turbine or compressor
casing, will lower the efficiency of the gas turbine leading to increased fuel costs.
Additionally, gas-path leakage in the combustor area of a gas turbine will require
an increase in burn temperature to maintain power level, such increased burn temperature
leading to increased pollution, such as increased NOx and CO production.
[0005] Steam turbines (which can be considered a special type of gas turbine) include, but
are not limited to, steam turbine power generation equipment. A steam turbine includes
a steam inlet, a turbine, and a steam outlet, wherein steam is the gas which turns
the turbine rotor. The turbine of a steam turbine is similar to the turbine of a gas
turbine and suffers from steam-path leakage the way the turbine of a gas turbine suffers
from gas-path leakage.
[0006] Seals are used to minimize leakage of fluids. A known fluid-path leakage seal is
a cloth seal having a generally impervious and uniformly-thick shim assemblage and
a cloth assemblage generally surrounding the shim assemblage. Cloth seals may be used
in many applications including, but not limited to, seal assemblies for steam turbines
and gas turbines used for power generation and seal assemblies for gas turbines used
for aircraft and marine propulsion.
[0007] Commonly owned U.S. Patent Number 5,934,687 relates to a cloth seal that incorporates
a metal sheet having raised edges that are pushed against the associated turbine members
to provide improved sealing. However, no provision is made for facilitating the quick
assembly of the seal to the turbine members, and thus the metal sheet component design
limits functional, manufacturing, and assembly options.
[0008] Another fluid-path leakage seal for sealing the gap between two circumferentially-adjacent
(and non-rotating) transition pieces of a power-system gas turbine is disclosed in
commonly owned U.S. Patent Number 6,162,014. This seal is a manually-flexible metal
seal that has a uniform thickness in the general shape of an elongated rectangular
metal sheet, and has a fiber-fabric cloth layer wrapped around the metal sheet. One
elongated edge of the metal bar is engaged in a surface groove of one transition piece.
The other elongated edge of the metal bar is engaged in a matching and aligned surface
groove of the other transition piece. One end of the metal bar serves as a mounting
bracket, having a right-angle bend, which is used to secure the seal to a (non-rotating)
first-stage nozzle. The grooves of transition pieces are not perfectly machined, and
the grooves of transition pieces installed in power-system gas turbines are not perfectly
aligned. As a result, in spite of the flexibility of the metal seal an effective seal
may not be achieved between the transition pieces. In addition, the metal sheet component
design limits functional, manufacturing and assembly options.
[0009] What is needed is an leakage seal for a turbine that improves upon the seals of the
'687 and '014 seal configurations so as to be easy to assemble and install, and so
as to provide a more effective seal between components that are not perfectly aligned,
and that increases functional, manufacturing and assembly options.
[0010] The gas-path leakage seal according to an embodiment of the invention is for generally
sealing a gas-path leakage-gap between spaced-apart first and second members of a
turbine.
[0011] In one aspect, the turbine seal of the present invention includes an elongated seal
member having a length and having opposing first and second ends bounding said length,
an elongated, imperforate, and flexible first portion, and a rigid second portion
lengthwise adjoining said first portion, wherein said first portion is lengthwise
disposed between said first end and said second portion, wherein said second portion
is lengthwise disposed between said first portion and said second end, wherein said
flexible first portion includes a shim-layer assemblage having opposing first and
second surfaces and having two longitudinally extending raised edge regions, wherein
each of said raised edge regions extends a generally identical distance above said
first surface and each of said raised edge regions extends generally said identical
distance below said second surface; and wherein said flexible first portion further
includes a cloth layer assemblage having a thickness generally equal to or slightly
greater than said identical distance and superimposed on said second surface between
said raised edge regions, and wherein said second portion defines a mounting bracket.
[0012] In an exemplary embodiment, the cloth layer assemblage and the shim-layer assemblage
are attached together by spot welds, and the raised edges have curved portions.
[0013] In another aspect of the invention, a turbine assembly is provided that includes
a) a first turbine member having a first surface groove; b) a second turbine member
proximate and spaced apart from said first turbine member so as to define a fluid-path
leakage gap therebetween, said second turbine member having a second surface groove
facing and generally aligned with said first surface groove; and c) a turbine seal
including an elongated turbine seal member having a length and having opposing first
and second ends bounding said length, an elongated, imperforate, and flexible first
portion, and a rigid second portion lengthwise adjoining said first portion, wherein
said first portion is lengthwise disposed between said first end and said second portion,
wherein said second portion is lengthwise disposed between said first portion and
said second end, wherein said flexible first portion includes a shim-layer assemblage
having opposing first and second surfaces and having two longitudinally extending
raised edge regions, wherein each of said raised edge regions extends a generally
identical distance above said first surface and each of said raised edge regions extends
generally said identical distance below said second surface; and wherein said flexible
first portion further includes a cloth layer assemblage having a thickness generally
equal to or slightly greater than said identical distance and superimposed on said
second surface between said raised edge regions, wherein said second portion defines
a mounting bracket, and wherein said turbine seal member is disposed in said gap with
said first edge engaged in said first surface groove and with said second edge engaged
in said second surface groove.
[0014] Advantageously, in one embodiment, the turbine seal is vibrationally excited within
a range of vibrational frequencies by motion of generally only the first and second
turbine members during operation of the turbine, and the turbine seal is devoid of
any resonant frequency within the range of vibrational frequencies.
[0015] In an exemplary application, the turbine assembly is a power-system gas turbine assembly,
the first and second turbine members are circumferentially-adjacent transition pieces,
and the mounting bracket is secured to a third turbine member comprising a first stage
nozzle.
[0016] Several benefits and advantages are derived from the invention. The manually-flexible
main body of the turbine seal member allows all transition-piece turbine spline seals
in a standard power-system gas turbine to be replaced in generally half a day instead
of the several days required for prior-art seals. Furthermore, manually flexible main
body, which may be a metal sheet, provides good sealing of gas flow as the raised
edges are pushed against the first and second turbine members by gas from the higher-pressure
side of the seal. The first cloth layer provides some sealing and good wear resistance.
The flexible metal sheet and the inherent flexibility of the cloth layer provides
good seal flexibility which means the seal is very compliant and can accommodate surfaces
of different shapes, assembly misalignment, vibration, and differential thermal growth.
The spot welds make it easier to assemble the seal, and the curved portions make it
easier to install the seal.
[0017] The invention will now be described in greater detail, by way of example, with reference
to the drawings, in which:-
FIGURE 1 is a perspective view of a first embodiment of the turbine seal of the present
invention;
FIGURE 2 is a top plan view of a seal strip embodying the invention;
FIGURE 3 is a cross-sectional view taken along line 3-3 of FIGURE 2;
FIGURE 4 is a fragmentary view of the seal assembly of FIGURE 1 illustrating an exemplary
welding pattern;
FIGURE 5 is a top plan view of the seal assembly of FIGURE 1;
FIGURE 6 is a side elevational view of the assembly of FIGURE 5;
FIGURE 7 is a view of a section of a turbine including a seal assembly embodying the
invention; and
FIGURE 8 is a cross-sectional view taken along line 8-8 of FIGURE 7 showing the edges
of the seal assembly engaged in the surface groove of first and second turbine members
in an embodiment of the invention.
[0018] Referring now to the drawings, wherein like numerals represent like elements throughout,
FIGURE 1 shows a first embodiment of the turbine seal of the present invention. The
turbine seal is defined by an elongated turbine seal member 10 that has having a length
and first and second ends 12 and 14.
[0019] The turbine seal member includes an elongated, imperforate first portion 16 and also
includes a second portion 18 lengthwise adjoining the first portion. In an exemplary
embodiment, the first portion 16 defines the main body of the seal member and is manually-flexible.
The second portion 18 defines a mounting bracket of the seal member and is manually-rigid.
By "manually-flexible" it is meant that the first portion 16 can be flexed by hand
by an adult person of average strength. By "manually-rigid" it is meant that the second
portion 18 cannot be flexed by hand by an adult person of average strength. The first
portion is lengthwise disposed between the first end and the second portion, the second
portion is lengthwise disposed between the first portion and the second end.
[0020] In a first embodiment, as seen in FIGURE 3, 5 and 6, the first portion 16 is comprised
of an imperforate shim-layer assemblage 20 that has a first thickness and the second
portion 18 is defined from a bent strip or plate 22 that has a second thickness. In
an exemplary embodiment, the second thickness is on the order of at least about five
times greater than the first thickness.
[0021] The shim-layer assemblage comprises at least one shim layer or plate of uniform thickness,
and may comprise at least two superimposed, generally identical shim layers or plates.
In this exemplary embodiment, the assemblage has no more than four layers. Each shim
layer is impervious to gas and comprises a metal, ceramic, and/or polymer sheet. The
choice of materials for the shim and the choice of the thickness for a shim layer
are made by the artisan to meet the sealing, flexibility, and resilience requirements
of a particular seal application. Usually, the shim-layer has a thickness of generally
between about five and twenty thousandths of an inch, for example, about ten thousandths
of an inch where two shim layers are provided. In one embodiment, each shim layer
comprises a high-temperature, cobalt-based super-alloy, such as HS-188. It is noted
that the shim layers can comprise different materials and/or have different thicknesses
depending on the particular seal application.
[0022] In the illustrated embodiment, the first portion of the seal member is comprised
of two superimposed and identical shim layers 24, 124, formed from metal. To integrate
the assembly, the first end 12 of the seal member is edge-welded. Further, to facilitate
placement of the seal member, the first end 12 is chamfered as shown at 26.
[0023] Thus, a flexible and generally imperforate shim-layer assemblage 20 is provided having
opposing first and second surfaces, defined in the illustrated embodiment by the top
surface 28 of shim plate 24 and the bottom surface 30 of shim plate 124, respectively.
The shim-layer assemblage further includes to raised edges 32, 132. In the illustrated
embodiment, one raised edge 32 is formed entirely from one of the edges of one metal
shim sheet 24, and the other raised edge 132 is formed entirely from one of the edges
of another metal shim sheet 124. Each of the raised edges extends a generally identical
distance above the first surface 28, and each of the raised edges extends generally
that same identical distance below the second surface 30. It is noted that the directions
"above" and "below" are relative directions applying to the seal as viewed in FIGURES
1 and 3. In the illustrated embodiment, the raised edges 32, 132 are generally mirror
images of each other.
[0024] As will be understood from the discussion above, in a first exemplary embodiment,
the shim-layer assemblage is an elongated metal strip assemblage having a centerline
running midway between the raised edges and having a cross section (shown in FIGURE
3) generally perpendicular to the centerline. Here, each of the raised edges has a
first portion 34, 134 disposed at the previously-defined generally identical distance
above the first surface 28 of the metal sheet assemblage, each of the raised edges
has a second portion 36, 136 disposed at the previously-defined generally identical
distance below the second surface 30. In the previously-defined cross section the
first portion has a curved shape. Also, in the previously-defined cross-section the
raised edges each terminate proximate the second portion 36, 136. Furthermore, each
of the raised edges has a connecting portion 38, 138 joining together the first and
second portions. The connecting portions 38, 138 have a curved shape, more specifically
a generally bowed shape, pointing away from each other as illustrated in FIGURE 3.
Such curved bowed shape facilitates seal installation in many seal applications, as
described in greater detail below. In an exemplary mode of making the seal, each sheet
metal member is stamped or rolled to form the curved raised edges. It is noted that
seal can be made by pressing seal between two pressing plates (not shown).
[0025] The seal member further includes a cloth layer assemblage 40. In the illustrated
embodiment, the cloth layer assemblage 40 has a thickness generally the same as or
slightly greater than (e.g. by the thickness of one of the metal sheets or shims comprising
the shim-layer assemblage) the previously defined identical distance (i.e., the identical
distance the first and second raised edges extend above the first surface). The cloth
layer assemblage 40 is superimposed on the second surface between the raised edges.
The cloth layer assemblage comprises at least one cloth layer, only one of which is
shown in FIGURE 3. Each cloth layer comprises metal, ceramic, and/or polymer fibers
that have been woven, knitted, or pressed into a layer of fabric. The choice of layer
construction (i.e., woven, knitted, or pressed), the choice of materials for the cloth,
and the choice of the thickness for a layer are made by the artisan to meet the wear
resistance, flexibility, and sealing requirements of a particular seal application.
It is noted that such multiple cloth layers can comprise different materials, different
layer construction (i.e., woven, knitted, or pressed) and/or have different thicknesses
depending on the particular seal application. In this exemplary embodiment, the cloth
layer assemblage has no more than two cloth layers. In one embodiment, each cloth
layer is a woven cloth layer comprising L605 or Haynes-25. An exemplary cloth layer
is a twilled metal cloth layer. By "twilled" is meant a cloth having a twill weave
(such as a twill weave which floats weft threads over two warp threads and which staggers
these floats regularly). In an exemplary construction, the cloth layer has 30 warp
wires per inch and 250 weft wires per inch with each warp and weft wire having a thickness
of 7-10 mils and with the cloth layer having an overall thickness of about 0.052 inch.
An exemplary cloth-layer assemblage is a Dutch Twill weave cloth assemblage comprising
a high-temperature, cobalt-based super-alloy, such as L-605. It is noted that a Dutch
Twill weave will allow a small controlled leakage which provides cooling, as can be
appreciated by the artisan.
[0026] In an exemplary embodiment, the cloth layer assemblage 40 is superimposed on generally
the entire second surface 30. In the illustrated construction, the cloth layer assemblage
40 and the metal shim-layer assemblage 20 are attached together by a plurality of
spot welds 42 (as shown in FIGURE 4). In another exemplary construction, seam welds
(not shown) are used in place of spot welds.
[0027] Thus, the first portion 16 of the turbine seal member is defined by its corresponding
sections of the shim-layer and cloth-layer assemblages. The second portion 18 of the
turbine seal member 10 includes a base portion 44 lengthwise overlapping the corresponding
section of the cloth-layer assemblage 40 of the first portion and attached (such as
by spot welding 46) to the corresponding sections of the cloth-layer and shim-layer
assemblages. The second portion 18 of the turbine seal member 10, which may be made
of stainless steel, includes a generally right-angle bend 48 to define mounting bracket
22 having a support portion 50 adjoining the base portion 44.
[0028] FIGURES 7 and 8 schematically show a first embodiment of the gas-path leakage seal
of the present invention. Although the invention is described in terms of a gas turbine,
it is understood to be equally applicable to a steam turbine, which can be considered
a special type of gas turbine. The gas-path leakage seal is for generally sealing
a gas-path leakage-gap between spaced-apart first and second members of a gas turbine
(only a small portion of which is shown in FIGURE 7). The turbine assembly includes
a first turbine member 52, a second turbine member 54 which is proximate and circumferentially
spaced apart from the first turbine member so as to define a fluid-path leakage gap
56 therebetween, and a turbine seal 10 embodying the invention. The first turbine
member 52 has a first surface groove or slot 58, and the second turbine member has
a second surface groove or slot 60 facing and generally aligned with the first surface
groove 58. A fluid-path leakage gap as used herein includes, without limitation, a
steam-path leakage gap of a turbine of a steam turbine, a compressed-air leakage gap
of a compressor of a gas turbine, and a combustion-gas leakage gap in or downstream
of a combustor of a gas turbine. In a power-system gas turbine, downstream of the
combustor includes the transition pieces, first-stage nozzle and turbine sections.
[0029] The turbine seal 10 is identical to the previously-described turbine seal shown in
FIGURES 1-6. The gas-path leakage seal member is disposed in the gap to extend partially
in the first groove and partially in the second groove with one of the raised edges
disposed entirely within the first groove and the other of the raised edges disposed
entirely within the second groove. The gas-path leakage-gap has a higher-pressure
end and a lower-pressure end. This pressure differential seats the seal such that
the raised edges can resiliently and unattachedly contact the first and second members
respectively along the lower pressure side of the respective first and second slots
and such that the second cloth layer assemblage can also unattachedly contact the
first and second members and along the lower pressure side of the first and second
slots. The resilient contact of the metal sheet assemblage maintains sealing in the
"plane" of the seal while allowing for different surface shapes, assembly misalignment,
vibration, and/or thermally-induced relative movement between the first and second
members. In an embodiment of the invention, the way in which the seal assembly is
inserted with respect to the turbine members is controlled so that the cloth layer
40 may only be provided on one side of the seal strip, as illustrated. Specifically,
the cloth is provided on the downstream, pressure side of the junction. Thus, the
cloth layer assemblage is pushed by the differential pressure into contact with the
first and second members (as shown in FIGURE 8). The cloth layer assemblage protects
the metal sheet assemblage 20 against wear. The installed seal is not welded or otherwise
attached to the first and/or second members allowing for ease of installation.
[0030] During operation of the turbine, the turbine spline seal is vibrationally excited
within a range of vibrational frequencies by motion of generally only the first and
second turbine members 52, 54. The turbine spline seal is devoid of any resonant frequency
within the range of vibrational frequencies, as is within the skill of the artisan
to design by choosing, for example, an appropriate thickness and length of the mounting
bracket 22.
[0031] The turbine assembly also includes a third turbine member 62, and the mounting bracket
22 is secured to the third turbine member 62. In one application of the present invention,
the turbine assembly is a power-system gas turbine assembly, the first and second
turbine members 52, 54 are circumferentially-adjacent transition pieces of the gas
turbine assembly, and the third turbine member 62 is a first stage nozzle of the gas
turbine assembly. Here, the installed turbine seal member 10 is radially aligned,
with the mounting bracket 22 located at its radially-outer end, and a mounting block
64 is used to secure the mounting bracket 35 to the third turbine member 62. The mounting
block has a bolt hole 66 and the third turbine member has a threaded bolt hole (not
shown). A bolt 68 passes through the bolt hole in the mounting block and threadably-engages
the threaded bolt hole of the third turbine member.
[0032] Mounting block 64 also has a first slot 70 and a second slot 72. In the illustrated
embodiment, the right-angle bend 48 of the second portion 18 engages the lower of
the two slots. It is pointed out that the first slot 70 is the lower slot in FIGURE
7. It is noted that the mounting block 64 may be rotated one half turn about bolt
66. As rotated, the second slot 72 will become the lower slot for engagement with
the right-angle bend 48 of the second portion 18 of the turbine seal member 10.
[0033] As previously mentioned, the manually-flexible first portion 16 of the turbine seal
member 10 allows all transition-piece turbine spline seals in a standard power-system
gas turbine to be replaced in generally half a day instead of the several days required
for prior-art seals. It has been found that some prior-art seals had a dominant resonant
frequency which was excited by the vibration (including twisting) motion of the transition
pieces leading to early seal failure. The manually-rigid second portion 18 of the
turbine seal member of the turbine seal 10 has its length and thickness chosen, as
can be appreciated by those skilled in the art, to avoid the installed turbine seal
from having any resonant frequencies which can be excited by the vibrational motion
(typically between 80 and 200 Hertz) of the transition pieces during operation of
the turbine.
[0034] For the sake of good order, various aspects of the invention are set out in the following
clauses:-
1. A turbine seal comprising an elongated seal member (10) having a length and having
opposing first and second ends (12, 14) bounding said length, an elongated, imperforate,
and flexible first portion (16), and a rigid second portion (18) lengthwise adjoining
said first portion, wherein said first portion (16) is lengthwise disposed between
said first end (12) and said second portion (18), wherein said second portion (18)
is lengthwise disposed between said first portion (16) and said second end (14),
wherein said flexible first portion (16) includes a shim-layer assemblage (20)
having opposing first and second surfaces (28, 30) and having two longitudinally extending
raised edge regions (32, 132), wherein each of said raised edge regions extends a
generally identical distance above said first surface (28) and each of said raised
edge regions extends generally said identical distance below said second surface (30);
and wherein said flexible first portion (16) further includes a cloth layer assemblage
(40) having a thickness generally equal to or slightly greater than said identical
distance and superimposed on said second surface (30) between said raised edge regions,
and
wherein said second portion (18) defines a mounting bracket (22).
2. The turbine seal of clause 1, wherein said shim-layer assemblage has a first thickness
and includes at least first and second metal strips (24, 124), wherein said second
portion has a second thickness and comprises a metal plate, and wherein said second
thickness is at least five times greater than said first thickness.
3. The turbine seal of clause 1, wherein said second portion includes a generally
right-angle bend (48), and wherein said mounting bracket is an angled mounting bracket
(22).
4. The turbine seal of clause 1, wherein said cloth layer assemblage (40) is mechanically
secured to said shim-layer assemblage (20).
5. The turbine seal of clause 4, wherein said cloth layer assemblage (40) is spot
welded (42) to said shim-layer assemblage (20).
6. The turbine seal of clause 4, wherein said second portion (18) is mechanically
secured to corresponding sections of said shim-layer and cloth layer assemblages (20,
40) of said first portion.
7. The turbine seal of clause 1, wherein said raised edge regions (32, 132) are generally
mirror images of each other.
8. The turbine seal of clause 1, wherein each of said raised edge regions has a first
portion (34, 134) disposed at said identical distance above said first surface, wherein
each of said raised edge regions has a second portion (36, 136) disposed at said identical
distance below said second surface, and wherein each of said raised edge regions has
a connecting portion (38, 138) joining together said first and second portions, and
wherein in said cross section said connecting portion has a curved shape.
9. A turbine assembly comprising:
a) a first turbine member (52) having a first surface groove (58);
b) a second turbine member (54) proximate and spaced apart from said first turbine
member so as to define a fluid-path leakage gap (56) therebetween, said second turbine
member having a second surface groove (60) facing and generally aligned with said
first surface groove (58); and
c) a turbine seal including an elongated turbine seal member (10) having a length
and having opposing first and second ends (12, 14) bounding said length, an elongated,
imperforate, and flexible first portion (16), and a rigid second portion (18) lengthwise
adjoining said first portion, wherein said first portion (16) is lengthwise disposed
between said first end (12) and said second portion (18), wherein said second portion
(18) is lengthwise disposed between said first portion (16) and said second end (14),
wherein said flexible first portion includes a shim-layer assemblage (20) having
opposing first and second surfaces (28, 30) and having two longitudinally extending
raised edge regions (32, 132), wherein each of said raised edge regions extends a
generally identical distance above said first surface (28) and each of said raised
edge regions extends generally said identical distance below said second surface (30);
and wherein said flexible first portion (16) further includes a cloth layer assemblage
(40) having a thickness generally equal to or slightly greater than said identical
distance and superimposed on said second surface (30) between said raised edge regions,
wherein said second portion (18) defines a mounting bracket (22), and
wherein said turbine seal member is disposed in said gap (56) with said first edge
(32) engaged in said first surface groove (58) and with said second edge (132) engaged
in said second surface groove (60).
10. The turbine assembly of clause 9, wherein said shim-layer assemblage (20) has
a first thickness and includes at least first and second metal strips, wherein said
second portion (18) has a second thickness and comprises a metal plate, and wherein
said second thickness is at least five times greater than said first thickness.
11. The turbine assembly of clause 9, wherein said second portion (18) includes a
generally right-angle bend, and wherein said mounting bracket is an angled mounting
bracket (22).
12. The turbine assembly of clause 9, wherein said cloth layer assemblage (40) is
mechanically secured to said shim-layer assemblage (20).
13. The turbine assembly of clause 12, wherein said cloth layer assemblage (40) is
spot welded (42) to said shim-layer assemblage (20).
14. The turbine assembly of clause 12, wherein said second portion (18) is mechanically
secured (46) to corresponding sections of said shim-layer and cloth layer assemblages
(20, 40) of said first portion (16).
15. The turbine assembly of clause 9, also including a third turbine member (62),
and wherein said mounting bracket (22) defined by said second portion is secured to
said third turbine member.
16. The turbine assembly of clause 15, wherein said second portion includes a generally
right-angle bend (48), and wherein said mounting bracket is an angled mounting bracket.
17. The turbine assembly of clause 16, wherein said turbine assembly is a power-system
gas turbine assembly, wherein said first and second turbine members (52, 54) are circumferentially-adjacent
transition pieces of said gas turbine assembly, and wherein said third turbine member
(62) is a first stage nozzle of said gas turbine assembly.
18. The turbine assembly of clause 16, further comprising a mounting block (64) for
securing the mounting bracket (22) to the third turbine member (62),'the mounting
block having a bolt hole (66) and the third turbine member having a threaded bolt
hole for receiving a common bolt (68) to secure the mounting block to the third turbine
member.
19. The turbine assembly of clause 18, wherein the mounting block (64) includes first
and second slots (70, 72), the right-angle bend of the second portion engaging one
of said slots to secure the seal member (10) to the third turbine member (62).
20. The turbine assembly of clause 9, wherein each of said raised edge regions (32,
132) has a first portion (34, 134) disposed at said identical distance above said
first surface, wherein each of said raised edge regions has a second portion (36,
136) disposed at said identical distance below said second surface, and wherein each
of said raised edge regions has a connecting portion (38, 138) joining together said
first and second portions, and wherein in said cross section said connecting portion
has a curved shape.
1. turbine seal comprising an elongated seal member (10) having a length and having opposing
first and second ends (12, 14) bounding said length, an elongated, imperforate, and
flexible first portion (16), and a rigid second portion (18) lengthwise adjoining
said first portion, wherein said first portion (16) is lengthwise disposed between
said first end (12) and said second portion (18), wherein said second portion (18)
is lengthwise disposed between said first portion (16) and said second end (14),
wherein said flexible first portion (16) includes a shim-layer assemblage (20)
having opposing first and second surfaces (28, 30) and having two longitudinally extending
raised edge regions (32, 132), wherein each of said raised edge regions extends a
generally identical distance above said first surface (28) and each of said raised
edge regions extends generally said identical distance below said second surface (30);
and wherein said flexible first portion (16) further includes a cloth layer assemblage
(40) having a thickness generally equal to or slightly greater than said identical
distance and superimposed on said second surface (30) between said raised edge regions,
and
wherein said second portion (18) defines a mounting bracket (22).
2. The turbine seal of claim 1, wherein said shim-layer assemblage has a first thickness
and includes at least first and second metal strips (24, 124), wherein said second
portion has a second thickness and comprises a metal plate, and wherein said second
thickness is at least five times greater than said first thickness.
3. The turbine seal of claim 1, wherein said second portion includes a generally right-angle
bend (48), and wherein said mounting bracket is an angled mounting bracket (22).
4. The turbine seal of claim 1, wherein said cloth layer assemblage (40) is mechanically
secured to said shim-layer assemblage (20).
5. The turbine seal of claim 1, wherein each of said raised edge regions has a first
portion (34, 134) disposed at said identical distance above said first surface, wherein
each of said raised edge regions has a second portion (36, 136) disposed at said identical
distance below said second surface, and wherein each of said raised edge regions has
a connecting portion (38, 138) joining together said first and second portions, and
wherein in said cross section said connecting portion has a curved shape.
6. A turbine assembly comprising:
a) a first turbine member (52) having a first surface groove (58);
b) a second turbine member (54) proximate and spaced apart from said first turbine
member so as to define a fluid-path leakage gap (56) therebetween, said second turbine
member having a second surface groove (60) facing and generally aligned with said
first surface groove (58); and
c) a turbine seal including an elongated turbine seal member (10) having a length
and having opposing first and second ends (12, 14) bounding said length, an elongated,
imperforate, and flexible first portion (16), and a rigid second portion (18) lengthwise
adjoining said first portion, wherein said first portion (16) is lengthwise disposed
between said first end (12) and said second portion (18), wherein said second portion
(18) is lengthwise disposed between said first portion (16) and said second end (14),
wherein said flexible first portion includes a shim-layer assemblage (20) having
opposing first and second surfaces (28, 30) and having two longitudinally extending
raised edge regions (32, 132), wherein each of said raised edge regions extends a
generally identical distance above said first surface (28) and each of said raised
edge regions extends generally said identical distance below said second surface (30);
and wherein said flexible first portion (16) further includes a cloth layer assemblage
(40) having a thickness generally equal to or slightly greater than said identical
distance and superimposed on said second surface (30) between said raised edge regions,
wherein said second portion (18) defines a mounting bracket (22), and
wherein said turbine seal member is disposed in said gap (56) with said first edge
(32) engaged in said first surface groove (58) and with said second edge (132) engaged
in said second surface groove (60).
7. The turbine assembly of claim 6, wherein said shim-layer assemblage (20) has a first
thickness and includes at least first and second metal strips, wherein said second
portion (18) has a second thickness and comprises a metal plate, and wherein said
second thickness is at least five times greater than said first thickness.
8. The turbine assembly of claim 6, wherein said cloth layer assemblage (40) is mechanically
secured to said shim-layer assemblage (20).
9. The turbine assembly of claim 6, also including a third turbine member (62), and wherein
said mounting bracket (22) defined by said second portion is secured to said third
turbine member.
10. The turbine assembly of claim 6, wherein each of said raised edge regions (32, 132)
has a first portion (34, 134) disposed at said identical distance above said first
surface, wherein each of said raised edge regions has a second portion (36, 136) disposed
at said identical distance below said second surface, and wherein each of said raised
edge regions has a connecting portion (38, 138) joining together said first and second
portions, and wherein in said cross section said connecting portion has a curved shape.