Information
-
Patent Grant
-
6644032
-
Patent Number
6,644,032
-
Date Filed
Tuesday, October 22, 200222 years ago
-
Date Issued
Tuesday, November 11, 200321 years ago
-
Inventors
-
Original Assignees
-
Examiners
Agents
-
CPC
-
US Classifications
Field of Search
US
- 060 3937
- 060 752
- 060 805
-
International Classifications
-
Abstract
A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1 carried only to three decimal places wherein the coordinates are taken at a sweep angle θ wherein θ is an angle measured from said inlet end and X, Y, and Z are coordinates defining the panel assembly profile at each angle θ from the inlet end. An alternate embodiment is also disclosed defining an envelope for the uncoated internal profile of the panel assembly.
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to a transition duct for a gas turbine engine, specifically to a novel and improved profile for a transition duct that results in lower operating stresses and extended component life.
2. Description of Related Art
In a typical can annular gas turbine engine, a plurality of combustors are arranged in an annular array about the engine. The combustors receive pressurized air from the engine's compressor, adds fuel to create a fuel/air mixture, and combusts that mixture to produce hot gases. The hot gases exiting the combustors are utilized to turn a turbine, which is coupled to a shaft that drives a generator for generating electricity.
The hot gases are transferred from the combustor to the turbine by a transition duct. Due to the position of the combustors relative to the turbine inlet, the transition duct must change cross-sectional shape from a generally cylindrical shape at the combustor exit to a generally rectangular arc-like shape at the turbine inlet. In addition, the transition duct undergoes a change in radial position, since the combustors are typically mounted outboard of the turbine. Extreme care must be taken with respect to the design of these geometric transitions to avoid sharp geometric changes, otherwise regions of high stress and stress concentrations can occur. The combination of complex geometry changes as well as extreme mechanical and thermal loading seen by the transition duct create a harsh operating environment that can lead to premature deterioration, requiring repair and replacement of the transition ducts. To withstand the hot temperatures from the combustor gases, transition ducts are typically air-cooled. A variety of methods are available to provide cooling such as through internal channels, impingement cooling, or effusion cooling. Severe cracking has been known to occur in transition ducts having extremely sharp geometry changes and internal air-cooled channels.
The present invention seeks to overcome the shortfalls of the prior art by providing a transition duct having a geometric profile optimized to eliminate areas having high stress concentrations and high steady and vibratory stresses while still transferring the hot combustion gases from the combustor to the turbine inlet in an acceptable manner.
SUMMARY AND OBJECTS OF THE INVENTION
In accordance with the present invention, there is provided a novel and improved transition duct having an enhanced profile and other characteristics for improved performance and enhanced durability. To accomplish this, the internal flowpath geometry of the transition duct has been optimized to remove areas of sharp geometric change. The sharp geometric changes in combination with high thermal and mechanical loading, caused regions of high steady and vibratory stresses and local stress concentrations can lead to cracking and premature failure of the transition duct. The internal flowpath of the transition duct has been optimized to provide a more homogeneous temperature profile of the hot combustion gases to the turbine as well as to raise the natural frequency of the transition duct. Providing a more homogeneous temperature profile to the turbine inlet helps to minimize the distress to the first stage of the turbine.
A variety of cooling methods can be used in combination with the enhanced profile of the present invention transition duct. In the preferred embodiment, the cooling system continues to use air, but the air is directed through a plurality of effusion holes in the panel assembly of the transition duct. Effusion cooling provides more uniform cooling of the transition duct than the plurality of internal cooling channels used in the prior art and were a source of stress concentrations.
In the preferred embodiment of the present invention, there is provided a transition duct with a panel assembly having an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section with an uncoated internal profile substantially in accordance with the coordinate values θ, X, Y, and Z as set forth in Table 1. The origin of the coordinate system is positioned at the center of the panel assembly inlet end along a centerline axis. It will be appreciated that the coordinate values given are for manufacturing purposes, in a room temperature condition. Each set of coordinate values X, Y, and Z in Table 1 is standard Cartesian coordinates, and each set corresponds to a specific sweep angle θ, which together define a cross section of the panel assembly. Each cross section is joined smoothly with adjacent cross sections to define a panel assembly for the transition duct. It will also be appreciated that as the transition duct transfers hot combustion gases from a combustor to the turbine inlet, the transition duct heats up and therefore the coordinates provided in Table 1 do not necessarily correspond to the panel assembly position when in operation at an elevated temperature.
In an alternate preferred embodiment, there is provided a transition duct with a panel assembly having an inlet end of generally circular cross section and outlet end having a generally rectangular arc-like cross section with an uncoated internal profile within an envelope of +/−0.250 inches in a direction normal to any surface of the panel assembly substantially in accordance with the coordinate values θ, X, Y, and Z as set forth in Table 1. The origin of the Cartesian coordinate system is positioned at the center of the panel assembly inlet end along a centerline axis. A distance of +/−0.250 inches in a direction normal to any surface location along the panel assembly defines an envelope for this particular panel assembly and ensures that manufacturing tolerances are accommodated within the envelope of the panel assembly. As with the first preferred embodiment, it will be appreciated that the coordinate values given are for manufacturing purposes, in a room temperature condition. Each set of coordinate values X, Y, and Z in Table 1 is in standard Cartesian coordinates, and each set corresponds to a specific sweep angle θ, which defines a cross section of the panel assembly. Each cross section is joined smoothly with adjacent cross sections to define a panel assembly for the transition duct. It will also be appreciated that as the transition duct transfers hot combustion gases from a combustor to the turbine inlet, the transition duct heats up and therefore the Cartesian coordinates for a given θ value provided in Table 1 may not necessarily correspond to the panel assembly position when in operation at an elevated temperature.
It is an object of the present invention to provide a novel, optimized internal profile for a panel assembly of a gas turbine transition duct having improved robustness and extended life.
It is another object of the present invention to provide a novel and optimized internal profile for a panel assembly of a gas turbine transition duct having an envelope for the profile defining manufacturing tolerances.
In accordance with these and other objects, which will become apparent hereinafter, the instant invention will now be described with particular reference to the accompanying drawings.
BRIEF DESCRIPTION OF DRAWINGS
FIG. 1
is a perspective view of a transition duct of the prior art.
FIG. 2
is a cross section view of a transition duct of the prior art.
FIG. 3
is a perspective view of the preferred embodiment of the present invention.
FIG. 4
is a cross section view of the preferred embodiment of the present invention.
FIG. 5
is a cross section view of the preferred embodiment of the panel assembly of present invention.
FIGS. 6
a
,
6
b
,
6
c
, and
6
d
are section views taken through the panel assembly of the present invention at various sweep angles.
FIG. 7
is a perspective view showing each of the cross sections used to define the panel assembly of the present invention.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to
FIGS. 1 and 2
, a transition duct
10
of the prior art is shown. Transition duct
10
contains an inlet ring
11
, a panel assembly
12
, and an aft frame
13
. Inlet ring
11
is of generally circular cross section while aft frame
13
is of generally rectangular arc-like cross section where the generally rectangular arc-like shape is defined by a pair of concentric arcs of different diameters connected by a pair of radial lines. Transition duct
10
, which is used to transfer hot combustion gases from a combustor to a turbine, has geometric profile that must transition from a generally circular cross section to that of a generally arc-like cross section at the turbine inlet as well as changing radial positions. The geometric profile of transition duct
10
contains a sharp transition from circular to rectangular arc-like over a short axial and radial distance thereby resulting in high stress regions throughout the aft end of transition duct
10
.
The present invention is shown in
FIGS. 3-7
. Referring to
FIGS. 3 and 4
, transition duct
20
includes a panel assembly
23
having an inlet end
21
of generally circular cross section and an outlet end
22
having a generally rectangular arc-like cross section. Panel assembly
23
comprises an upper panel
24
and lower panel
25
joined together along a plurality of axial seams
26
by a means such as welding. Panel assembly
23
also contains a plurality of cooling holes
27
extending throughout upper panel
24
and lower panel
25
to provide cooling air to said panels. Transition duct
20
further includes an inlet ring
28
fixed to inlet end
21
and an aft frame
29
fixed to outlet end
22
. Panel assembly
23
of transition duct
20
is preferably manufactured from a high temperature nickel base alloy such as Haynes
230
.
Panel assembly
23
, formed from upper panel
24
and lower panel
25
, has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1, carried only to three decimal places. Although the preferred unit of measure for the values given in Table 1 is inches, those skilled in the art will appreciate that the values of Table 1 for X, Y, and Z can be scaled up or down depending on the diameter of the particular combustion liner with which the present invention is to be used. This uncoated internal profile provides an optimized transition from a generally circular inlet end to a generally rectangular arc-like outlet end over the allowable axial and radial distance for a gas turbine engine, such that high steady stresses and stress concentrations in transition duct
20
are minimized. For the purpose of describing the present invention, the coordinate values X, Y, and Z of Table 1 are taken at various sweep angles θ wherein θ is an angle measured from inlet end
21
and increases to its maximum value at outlet end
22
. Sweep angle θ originates at the intersection line
90
of two planes, a first plane
100
that is defined by inlet end
21
of panel assembly
23
and a second plane
102
that is defined by outlet end
22
of panel assembly
23
, as shown in
FIGS. 4 and 5
. The origin
92
of the Cartesian coordinate system, from which data in Table 1 is generated, is positioned at center of inlet end
21
of transition duct
20
along an axis A—A that runs through the center of inlet end
21
, and is perpendicular to plane
100
, at inlet end
21
. The Cartesian coordinate system is oriented such that X and Y extend radially out from origin
92
, or center point of inlet end
21
, and Z extends axially along axis A—A towards outlet end
22
, as shown in FIG.
5
. Coordinate values X, Y, and Z are listed in Table 1 for each sweep angle θ, measured in one degree increments, necessary to define the optimized internal profile of panel assembly
23
. The data compiled in Table 1 is computer generated and though it represents the nominal uncoated internal profile, the data will vary depending on manufacturing tolerances. Therefore, it will be appreciated that a gas turbine component of this size having a panel assembly
23
fabricated primarily from formed and welded sheet metal can be expected to have manufacturing tolerances of at least +/−0.062 inches.
For the data listed in Table 1 a plurality of wireframe sections can be created when applying a best-fit curve to the section data for each sweep angle θ. For example,
FIGS. 6
a
-
6
d
show wireframe cross sections taken at various sweep angles from inlet end
21
to outlet end
22
of panel assembly
23
as well as the Cartesian coordinates (each shown as an “x” in
FIGS. 6
a
-
6
d
) used to define each section taken. In
FIGS. 6
a
-
6
d
, for clarity, the wireframe sections are shown progressively stacked to show the change from the previous section(s). In each of
FIGS. 6
a
-
6
d
, the relevant section is the one with multiple “x” markings; the other sections shown are merely for reference purposes. At inlet end
21
, a section is taken corresponding to θ=0.0 degrees and is shown in section view in
FIG. 6
a
, while
FIG. 6
b
shows a section taken where the sweep angle θ=10.0 degrees. In
FIG. 6
c
, where a section is taken with θ=20.0 degrees, panel assembly
23
is shown transitioning from a generally circular cross section to a rectangular arc-like shape. A final section demonstrating this transition is shown in
FIG. 6
d
and taken at θ=31.0 degrees, at the outlet end
22
of panel assembly
23
. It can be seen in
FIGS. 6
a
-
6
d
how the section geometry of panel assembly
23
transitions from a generally circular cross section to a generally rectangular arc-like cross section.
FIG. 7
shows, in perspective view, each wireframe section formed at each respective sweep angle θ, that when compiled, define the internal flowpath of panel assembly
23
of transition duct
20
.
An additional feature of transition duct
20
is a protective two-layer coating applied along the internal profile of panel assembly
23
to protect transition duct
20
from deterioration associated with prolonged exposure to elevated temperatures. The two-layer air plasma sprayed coating preferably comprises a MCrAlY bond coating applied directly to panel assembly
23
and a Yttra Stabilized Zirconia top coating applied over the bond coating, the combined coating having a thickness of at least 0.019 inches. The two-layer coating is preferably applied once panel assembly
23
has been formed and welded in accordance with the profile as defined in Table 1.
In an alternate embodiment of the present invention there is provided a transition duct identical to that of the preferred embodiment except for the uncoated internal profile of panel assembly
23
is within an envelope of +/−0.250 inches in a direction normal to any surface of the panel assembly substantially in accordance with the Cartesian coordinate values X, Y, and Z as set forth in Table 1. A distance of +/−0.250 inches in a direction normal to any surface of the panel assembly thereby defines a profile envelope for this specific transition duct panel assembly. This envelope ensures that all reasonable manufacturing tolerances are accommodated within the profile.
The X, Y, Z Cartesian coordinate data and corresponding sweep angles θ are summarized in the following Table 1.
TABLE 1
|
|
Theta (deg.)
X
Y
Z
|
|
|
0.0
0.000
6.880
0.000
|
0.0
0.839
6.829
0.000
|
0.0
1.666
6.675
0.000
|
0.0
2.468
6.422
0.000
|
0.0
3.234
6.073
0.000
|
0.0
3.950
5.633
0.000
|
0.0
4.952
4.776
0.000
|
0.0
5.772
3.745
0.000
|
0.0
6.380
2.575
0.000
|
0.0
6.754
1.312
0.000
|
0.0
6.880
0.000
0.000
|
0.0
6.859
−0.537
0.000
|
0.0
6.796
−1.071
0.000
|
0.0
6.692
−1.598
0.000
|
0.0
6.547
−2.116
0.000
|
0.0
6.361
−2.620
0.000
|
0.0
5.800
−3.700
0.000
|
0.0
5.058
−4.664
0.000
|
0.0
4.157
−5.482
0.000
|
0.0
3.127
−6.129
0.000
|
0.0
1.998
−6.583
0.000
|
0.0
1.607
−6.690
0.000
|
0.0
1.210
−6.773
0.000
|
0.0
0.809
−6.832
0.000
|
0.0
0.405
−6.868
0.000
|
0.0
0.000
−6.880
0.000
|
0.0
−0.405
−6.868
0.000
|
0.0
−0.809
−6.832
0.000
|
0.0
−1.210
−6.773
0.000
|
0.0
−1.607
−6.690
0.000
|
0.0
−1.998
−6.583
0.000
|
0.0
−3.127
−6.129
0.000
|
0.0
4.157
−5.482
0.000
|
0.0
−5.058
−4.664
0.000
|
0.0
−5.800
−3.700
0.000
|
0.0
−6.361
−2.620
0.000
|
0.0
−6.547
−2.116
0.000
|
0.0
−6.692
−1.598
0.000
|
0.0
−6.796
−1.071
0.000
|
0.0
−6.859
−0.537
0.000
|
0.0
−6.880
0.000
0.000
|
0.0
−6.754
1.312
0.000
|
0.0
−6.380
2.575
0.000
|
0.0
−5.772
3.745
0.000
|
0.0
−4.952
4.776
0.000
|
0.0
−3.234
6.073
0.000
|
0.0
−2.468
6.422
0.000
|
0.0
−1.666
6.675
0.000
|
0.0
−0.839
6.829
0.000
|
1.0
0.000
6.607
0.778
|
1.0
0.808
6.557
0.779
|
1.0
1.604
6.407
0.782
|
1.0
2.376
6.161
0.786
|
1.0
3.112
5.823
0.792
|
1.0
3.801
5.398
0.800
|
1.0
4.760
4.571
0.814
|
1.0
5.541
3.576
0.831
|
1.0
6.116
2.448
0.851
|
1.0
6.465
1.231
0.872
|
1.0
6.573
−0.030
0.894
|
1.0
6.548
−0.537
0.903
|
1.0
6.485
−1.042
0.912
|
1.0
6.383
−1.540
0.921
|
1.0
6.242
−2.028
0.929
|
1.0
6.064
−2.504
0.938
|
1.0
5.530
−3.526
0.955
|
1.0
4.824
−4.439
0.971
|
1.0
3.970
−5.214
0.985
|
1.0
2.993
−5.827
0.996
|
1.0
1.923
−6.258
1.003
|
1.0
1.546
−6.359
1.005
|
1.0
1.165
−6.439
1.006
|
1.0
0.779
−6.497
1.007
|
1.0
0.390
−6.532
1.008
|
1.0
0.000
−6.543
1.008
|
1.0
−0.390
−6.532
1.008
|
1.0
−0.779
−6.497
1.007
|
1.0
−1.165
−6.439
1.006
|
1.0
−1.546
−6.359
1.005
|
1.0
−1.923
−6.258
1.003
|
1.0
−2.993
−5.827
0.996
|
1.0
−3.970
−5.214
0.985
|
1.0
−4.824
−4.439
0.971
|
1.0
−5.530
−3.526
0.955
|
1.0
−6.064
−2.504
0.938
|
1.0
−6.242
−2.028
0.929
|
1.0
−6.383
−1.540
0.921
|
1.0
−6.485
−1.042
0.912
|
1.0
−6.548
−0.537
0.903
|
1.0
−6.573
−0.030
0.894
|
1.0
−6.465
1.231
0.872
|
1.0
−6.116
2.448
0.851
|
1.0
−4.760
4.571
0.814
|
1.0
−3.801
5.398
0.800
|
1.0
−3.112
5.823
0.792
|
1.0
−2.376
6.161
0.786
|
1.0
−1.604
6.407
0.782
|
1.0
−0.808
6.557
0.779
|
2.0
0.000
6.394
1.565
|
2.0
0.786
6.344
1.567
|
2.0
1.560
6.196
1.572
|
2.0
2.310
5.955
1.580
|
2.0
3.026
5.624
1.592
|
2.0
3.696
5.211
1.606
|
2.0
4.618
4.413
1.634
|
2.0
5.367
3.452
1.668
|
2.0
5.918
2.364
1.706
|
2.0
6.249
1.191
1.747
|
2.0
6.351
−0.024
1.789
|
2.0
6.326
−0.517
1.806
|
2.0
6.264
−1.007
1.823
|
2.0
6.164
−1.490
1.840
|
2.0
6.027
−1.964
1.857
|
2.0
5.854
−2.427
1.873
|
2.0
5.341
−3.407
1.907
|
2.0
4.666
−4.284
1.938
|
2.0
3.849
−5.030
1.964
|
2.0
2.913
−5.621
1.984
|
2.0
1.887
−6.036
1.999
|
2.0
1.517
−6.135
2.002
|
2.0
1.143
−6.214
2.005
|
2.0
0.764
−6.272
2.007
|
2.0
0.383
−6.306
2.008
|
2.0
0.000
−6.317
2.009
|
2.0
−0.383
−6.306
2.008
|
2.0
−0.764
−6.272
2.007
|
2.0
−1.143
−6.214
2.005
|
2.0
−1.517
−6.135
2.002
|
2.0
−1.887
−6.036
1.999
|
2.0
−2.913
−5.621
1.984
|
2.0
−3.849
−5.030
1.964
|
2.0
−4.666
−4.284
1.938
|
2.0
−5.341
−3.407
1.907
|
2.0
−5.854
−2.427
1.873
|
2.0
−6.027
−1.964
1.857
|
2.0
−6.164
−1.490
1.840
|
2.0
−6.264
−1.007
1.823
|
2.0
−6.326
−0.517
1.806
|
2.0
−6.351
−0.024
1.789
|
2.0
−5.918
2.364
1.706
|
2.0
−5.367
3.452
1.668
|
2.0
−4.618
4.413
1.634
|
2.0
−3.696
5.211
1.606
|
2.0
−3.026
5.625
1.592
|
2.0
−2.310
5.955
1.580
|
2.0
−1.560
6.196
1.572
|
2.0
−0.786
6.344
1.567
|
3.0
0.000
6.248
2.356
|
3.0
0.773
6.198
2.359
|
3.0
1.532
6.051
2.367
|
3.0
2.269
5.811
2.379
|
3.0
2.971
5.487
2.396
|
3.0
3.631
5.082
2.417
|
3.0
4.529
4.304
2.458
|
3.0
5.258
3.367
2.507
|
3.0
5.792
2.307
2.563
|
3.0
6.115
1.164
2.623
|
3.0
6.213
−0.019
2.685
|
3.0
6.190
−0.504
2.710
|
3.0
6.131
−0.986
2.735
|
3.0
6.033
−1.462
2.760
|
3.0
5.898
−1.929
2.785
|
3.0
5.728
−2.384
2.809
|
3.0
5.233
−3.340
2.859
|
3.0
4.580
−4.197
2.904
|
3.0
3.787
−4.927
2.942
|
3.0
2.878
−5.507
2.972
|
3.0
1.880
−5.914
2.994
|
3.0
1.512
−6.012
2.999
|
3.0
1.138
−6.092
3.003
|
3.0
0.761
−6.150
3.006
|
3.0
0.381
−6.185
3.008
|
3.0
0.000
−6.196
3.008
|
3.0
−0.381
−6.185
3.008
|
3.0
−0.761
−6.150
3.006
|
3.0
−1.138
−6.092
3.003
|
3.0
−1.512
−6.012
2.999
|
3.0
−1.880
−5.914
2.994
|
3.0
−2.878
−5.507
2.972
|
3.0
−3.787
−4.927
2.942
|
3.0
−4.580
−4.197
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30.0
−2.683
1.990
28.415
|
30.0
−1.342
2.052
28.379
|
31.0
0.000
2.530
29.248
|
31.0
1.350
2.511
29.259
|
31.0
2.698
2.453
29.294
|
31.0
4.043
2.356
29.352
|
31.0
5.384
2.220
29.434
|
31.0
6.719
2.047
29.538
|
31.0
6.952
1.979
29.579
|
31.0
7.149
1.851
29.656
|
31.0
7.289
1.677
29.760
|
31.0
7.358
1.474
29.882
|
31.0
7.349
1.263
30.009
|
31.0
7.165
0.473
30.484
|
31.0
6.982
−0.318
30.959
|
31.0
6.798
−1.109
31.434
|
31.0
6.615
−1.899
31.909
|
31.0
6.431
−2.690
32.384
|
31.0
6.350
−2.881
32.499
|
31.0
6.205
−3.042
32.596
|
31.0
6.010
−3.157
32.665
|
31.0
5.783
−3.217
32.701
|
31.0
5.546
−3.215
32.700
|
31.0
4.444
−3.075
32.616
|
31.0
3.337
−2.966
32.550
|
31.0
2.227
−2.888
32.503
|
31.0
1.114
−2.841
32.475
|
31.0
0.000
−2.825
32.466
|
31.0
−1.114
−2.841
32.475
|
31.0
−2.227
−2.888
32.503
|
31.0
−3.337
−2.966
32.550
|
31.0
−4.444
−3.075
32.616
|
31.0
−5.546
−3.215
32.700
|
31.0
−6.010
−3.157
32.665
|
31.0
−6.205
−3.042
32.596
|
31.0
−6.350
−2.881
32.499
|
31.0
−6.431
−2.690
32.384
|
31.0
−6.615
−1.899
31.909
|
31.0
−6.798
−1.109
31.434
|
31.0
−6.982
−0.318
30.959
|
31.0
−7.165
0.473
30.484
|
31.0
−7.349
1.263
30.009
|
31.0
−7.358
1.474
29.882
|
31.0
−7.289
1.677
29.760
|
31.0
−7.149
1.851
29.656
|
31.0
−6.952
1.979
29.579
|
31.0
−6.719
2.047
29.538
|
31.0
−5.384
2.220
29.434
|
31.0
−4.043
2.356
29.352
|
31.0
−2.698
2.453
29.294
|
31.0
−1.350
2.511
29.259
|
|
While the invention has been described in the preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment but, on the contrary, is intended to cover various modifications and equivalent arrangements within the scope of the following claims.
Claims
- 1. A transition duct having an inlet ring, an aft frame, and a panel assembly connecting said inlet ring to said aft frame, said panel assembly having an inlet end of generally circular cross section having a center and being connected to said inlet ring and having an outlet end of generally rectangular arc-like cross section connected to said aft frame, said panel assembly having an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z at an angle θ, as set forth in Table 1, said X, Y, and Z values carried only to three decimal places wherein said coordinates are relative to an origin at the center of said inlet end and taken at a sweep angle θ that is measured from a first plane defined by said inlet end and increases toward a second plane defined by said outlet end, said planes intersecting at a line about which the angle θ is measured, and X, Y, and Z are coordinates defining the panel assembly profile at each angle θ from said inlet end, X, Y, and Z have an origin at the center of said inlet end, and the z-axis is perpendicular to said first plane.
- 2. A transition duct according to claim 1 wherein said panel assembly comprises an upper panel and lower panel, said upper panel and lower panel joined together along a plurality of axial seams by welding.
- 3. A transition duct according to claim 1 wherein manufacturing tolerances for said panel assembly internal profile are at least 0.062 inches.
- 4. A transition duct according to claim 1 wherein said transition duct panel assembly has a two-layer air plasma sprayed coating comprising a bond coating applied along said internal profile of said panel assembly and a top coating applied over said bond coating.
- 5. A transition duct according to claim 4 wherein said two layer coating applied along said internal profile is at least 0.019 inches thick.
- 6. A transition duct according to claim 1 wherein said transition duct contains a plurality of cooling holes in said panel assembly.
- 7. A transition duct according to claim 1 wherein said panel assembly is fabricated from a high temperature nickel base alloy.
- 8. A transition duct having an inlet ring, an aft frame, and a panel assembly connecting said inlet ring to said aft frame, said panel assembly having an inlet end of generally circular cross section having a center and being connected to said inlet ring and having an outlet end of generally rectangular arc-like cross section connected to said aft frame, said panel assembly having an uncoated internal profile within an envelope of +/−0.250 inches in a direction normal to any surface with coordinate values X, Y, and Z at an angle θ, as set forth in Table 1, said X, Y, and Z values carried only to three decimal places wherein said coordinates are relative to an origin at the center of said inlet end and taken at a sweep angle θ that is measured from a first plane defined by said inlet end and increases toward a second plane defined by said outlet end, said planes intersecting at a line about which the angle θ is measured, and X, Y, and Z are coordinates defining the panel assembly profile at each angle θ from said inlet end, X, Y, and Z have an origin at the center of said inlet end, and the z-axis is perpendicular to said first plane.
- 9. A transition duct according to claim 8 wherein said panel assembly comprises an upper panel and lower panel, said upper panel and lower panel joined together along a plurality of axial seams by welding.
- 10. A transition duct according to claim 8 wherein said transition duct panel assembly has a two-layer air plasma sprayed coating comprising a bond coating applied along said internal profile of said panel assembly and a top coating applied over said bond coating.
- 11. A transition duct according to claim 10 wherein said two-layer coating applied along said internal profile is at least 0.019 inches thick.
- 12. A transition duct according to claim 8 wherein said transition duct contains a plurality of cooling holes in said panel assembly.
- 13. A transition duct according to claim 8 wherein said panel assembly is fabricated from a high temperature nickel base alloy.
US Referenced Citations (3)
Number |
Name |
Date |
Kind |
3657882 |
Hugoson |
Apr 1972 |
A |
5761898 |
Barnes et al. |
Jun 1998 |
A |
5983641 |
Mandai et al. |
Nov 1999 |
A |