Transition duct for gas turbine engine

FIELD OF THE INVENTION

The present invention relates to a transition duct for a gas turbine engine and, more particularly, to a transition duct design having a longer structural life and an improved aero performance.

BACKGROUND OF THE INVENTION

Generally, combustion turbines have three main assemblies, including a compressor assembly, a combustor assembly, and a turbine assembly. In operation, the compressor assembly compresses ambient air. The compressed air is channeled into the combustor assembly where it is mixed with a fuel. The fuel and compressed air mixture is ignited creating a heated working gas. The heated working gas is typically at a temperature of between 2300 to 2900° F. (1200 to 1593° C.), and is expanded through the turbine assembly. The turbine assembly generally includes a rotating assembly comprising a centrally located rotating shaft and a plurality of rows of rotating blades attached thereto. A plurality of stationary vane assemblies, each including a plurality of stationary vanes, are connected to a casing of the turbine and are located interposed between the rows of rotating blades. The expansion of the working gas through the rows of rotating blades and stationary vanes or airfoils in the turbine assembly results in a transfer of energy from the working gas to the rotating assembly, causing rotation of the shaft.

The combustor assembly typically includes a plurality of combustors arranged in an annular array about the engine. The hot working gas from each combustor is transferred to the turbine by a respective transition duct. The outlet of the combustor is generally cylindrical, and the inlet to the turbine at the exit to each transition duct generally corresponds to an arcuate sector. Accordingly, the cross-sectional shape of the transition duct must change from a generally cylindrical shape at the combustor exit to a generally rectangular arc-like shape at the turbine inlet. In addition, since the combustors are typically mounted at a radial outward location relative to the turbine inlet, the transition ducts must define a gas path extending radially inwardly in the direction of the gas flow to the turbine.

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 duct. In particular, as higher firing temperatures are utilized, increased transition duct failures may occur due to low cycle fatigue (LCF) cracks that may be observed at an upper panel of the transition. Accordingly, extreme care must be taken with respect to the design of these geometric transitions to avoid sharp geometric changes that may create regions of high stress, i.e., stress concentration points.

SUMMARY OF THE INVENTION

The present invention provides a transition duct having a geometric profile that is preferably optimized to reduce high stress concentrations from LCF. The present transition duct also has an improved structural dynamic response that effectively increases the separation of the transition frequency response from the combustion resonant frequencies, while also maintaining a desired aero efficiency in transferring hot working gas from the combustor to the turbine inlet.

In accordance with one aspect of the invention, a transition duct is provided having an inlet opening and an outlet opening and a body portion extending between the inlet and outlet openings at respective inlet and outlet ends. The inlet opening defines a generally circular cross-section for the body portion and has a geometric center. The body portion has an internal profile substantially in accordance with coordinate values X, Y and Z at sections defined by a respective angle θ, as set forth in Table 1, where each of the X, Y and Z coordinates are taken at a sweep angle θ passing through the section origin and measured from a first plane defined by the inlet end and increasing toward a second plane defined by the outlet end. The first plane and the section planes intersect at an angle origin line about which the angle θ is measured. The X and Y coordinate values are determined relative to a section origin at a substantially central geometric location within each respective section. The Z coordinate values are measured along a Z-axis extending perpendicular to the first plane, and having an origin at the center of the generally circular inlet opening and increasing toward the outlet end.

In accordance with another aspect of the invention, a transition duct is provided having an inlet opening and an outlet opening and a body portion extending between the inlet and outlet openings at respective inlet and outlet ends. The inlet opening defines a generally circular cross-section for the body portion and has a geometric center. The body portion has an internal profile including first, second, third and fourth profile sections located approximately at angles θ of 1.0°, 10.0°, 21.0° and 30.0°, respectively, taken at a sweep angle θ passing through the section origin and measured from a first plane defined by the inlet end and increasing toward a second plane defined by the outlet end. The first plane and the section planes intersect at an angle origin line about which the angle θ is measured, where each section defines a Cartesian X Y coordinate origin with corresponding quadrants determined relative to the section origin at a substantially central geometric location within each respective section, wherein the first section comprises a generally circular cross-section; the second section comprises a first side extending from the third quadrant to the second quadrant, a second side extending from the fourth quadrant to the first quadrant, an outer side extending between the first and second quadrants and curved concave inwardly toward the coordinate origin, an inner side extending between the third and fourth quadrants and curved concave inwardly toward the coordinate origin, the first and second sides extending in diverging relation from the inner side toward the outer side; the third section comprises a first substantially linear side extending from the third quadrant to the second quadrant, a second substantially linear side extending from the fourth quadrant to the first quadrant, an outer side extending between the first and second quadrants and curved concave inwardly toward the coordinate origin, an inner side extending between the third and fourth quadrants and curved concave inwardly toward the coordinate origin, the first and second sides extending in diverging relation from the inner side toward the outer side; and the fourth section comprises a first substantially linear side extending from the third quadrant to the second quadrant, a second substantially linear side extending from the fourth quadrant to the first quadrant, an outer side extending between the first and second quadrants and curved concave inwardly toward the coordinate origin, an inner side extending between the third and fourth quadrants and curved concave outwardly away from the coordinate origin, the first and second sides extending in diverging relation from the inner side toward the outer side.

In accordance with a further aspect of the invention, a transition duct is provided having an inlet opening and an outlet opening and a body portion extending between the inlet and outlet openings at respective inlet and outlet ends. The inlet opening defines a generally circular cross-section for the body portion and has a geometric center. The body portion has an internal profile including first, second, third and fourth profile sections substantially in accordance with coordinate values X, Y and Z located at angles θ of 1.0°, 10.0°, 21.0° and 30.0°, as set forth in Table 1, where each of the X, Y and Z coordinates are taken at a sweep angle θ passing through the section origin and measured from a first plane defined by the inlet end and increasing toward a second plane defined by the outlet end. The first plane and the section planes intersect at an angle origin line about which the angle θ is measured. The X and Y coordinate values are determined relative to a section origin at a substantially central geometric location within each respective section. The Z coordinate values are measured along a Z-axis extending perpendicular to the first plane, and having an origin at the center of the generally circular inlet opening and increasing toward the outlet end.

BRIEF DESCRIPTION OF THE DRAWINGS

While the specification concludes with claims particularly pointing out and distinctly claiming the present invention, it is believed that the present invention will be better understood from the following description in conjunction with the accompanying Drawing Figures, in which like reference numerals identify like elements, and wherein:

FIG. 1 is side elevation view of a portion of a gas turbine engine including a transition duct extending from a combustor to the entrance to a turbine section;

FIG. 2 is a cross-section view illustrating the coordinate system used to define the profile of the transition duct;

FIG. 3 is section view taken through the transition duct along section lines A-A in FIG. 2;

FIG. 4 is section view taken through the transition duct along section lines B-B in FIG. 2;

FIG. 5 is section view taken through the transition duct along section lines C-C in FIG. 2;

FIG. 6 is section view taken through the transition duct along section lines D-D in FIG. 2; and

FIG. 7 is a perspective view illustrating each of the section planes used to define the transition profile of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

Referring to FIG. 1, the present invention comprises a profile defining the interior surface of a transition duct 10. The transition duct 10 provides a conduit for conveying hot combustion gases from a combustor 12 for a gas turbine engine to the entrance 14 of a turbine assembly where the gases are directed toward a first row of vanes 16. An inlet ring 18 of generally circular cross-section may be provided at an inlet end 20 of the transition duct 10, supported by an inlet support 22. An outlet end 24 of the transition duct 10 may include an aft frame 26 having a generally rectangular arc-like shape. As is described further below, the transition duct 10 has a geometric profile that transitions from a generally circular cross-section, substantially corresponding to the shape of the outlet from the combustor 12, to a generally rectangular arc-like cross-section at the turbine entrance 14 (see also FIG. 7), while also defining a radially inwardly extending path for the gas flow.

The transition duct 10 may be formed by any known manufacturing process, and may comprise a body formed of an upper panel 28 and a lower panel 30 joined along longitudinally extending seams 32 (one illustrated) at longitudinal welds to form a panel assembly, as is known in the art. The upper and lower panels 28, 30 may also be provided with cooling holes in a manner known in the art. In addition, the upper and lower panels 28, 30 may be formed of a high temperature material such as a high temperature metal alloy including, without limitation, IN617 (Inconel 617) or H230 (Haynes 230). It should be noted that the transition duct 10 is not limited to any particular construction, and the invention encompasses any transition duct 10 that utilizes the profile described further below.

The interior surface of the body formed by the panels 28, 30 may preferably be provided with a coating to protect the interior of the transition duct 10 from deterioration, such as may be caused by prolonged exposure to the hot combustion gases traveling from the combustor 12. The coating may comprise a known coating material, such as is described in U.S. Pat. No. 6,644,032, incorporated herein by reference, or any other coating having similar protective properties. In addition, the coating is preferably a thin coating layer that will not substantially affect the beneficial profile characteristics provided by the present invention.

The profile of the transition duct 10 is described herein with reference to the uncoated surface profile of the interior surface of the body defined by the upper and lower panels 28, 30. Referring to FIG. 2, the profile of the transition duct 10 is described with reference to an angle θ to identify a location of a discrete section 34 (FIG. 7), i.e., a transverse cross-section, of the transition duct 10. In particular, each section 34 defines an origin located substantially at a geometric center of the section 34, as is illustrated for example by section origins O′, O_A, O_B, O_Cand O_Din FIGS. 2-6. The angle θ identifying a particular discrete section 34 is a sweep angle measured between a first plane 36 defined by a section 34 at the inlet end 20 and a plane passing through the origin of the particular discrete section 34. The first plane 36 and the planes defined by the sections 34 intersect at an angle origin line 38 about which the angle θ is measured, where the line 38 is a distance D approximately 1223 mm from the section origin O′ at the inlet end 20. The value of the sweep angle θ increases from the first plane 36 toward a second plane 40 defined by the outlet end 24, where the total sweep angle of the illustrated transition duct 10 is approximately 31.07°.

Coordinate values X, Y and Z are provided to identify points on the transition duct 10 for each discrete section 34 at specified angles θ substantially in accordance with the X, Y and Z coordinate values as set forth in Table 1 below. The values given in Table 1 are in millimeters. However, it should be understood that the present invention is not limited to particular dimensions, in that the X, Y and Z values given in Table 1 could be scaled up or down, i.e., may represent unitless scaled values, depending on the diameter of the particular combustion liner with which the transition duct 10 of the present invention is intended to be used.

Further, it should be noted that the coordinate values given in Table 1 correspond to coordinates on the transition duct 10 when at room temperature, and that the given coordinate values will not necessarily correspond to the location of particular points on the transition duct 10 when the transition duct 10 is at an elevated temperature during transfer of hot combustion gases.

The X and Y coordinate values are determined with reference to respective X and Y axes having a zero point or origin of a Cartesian coordinate system at the origin of the particular section 34 located substantially at the geometric center within each respective section 34 (see FIGS. 3-6). The Z coordinate values are measured along a Z-axis extending perpendicular to the first plane 36, and having an origin at the center of the section 34 defined at the generally circular inlet opening of the inlet end 20, and the Z values increase in the direction extending toward the outlet end 40. The data in Table 1 corresponds to 1 degree increments of the angle θ, provided to define an optimized internal profile for the transition duct 10,

It should be apparent that although the X, Y and Z coordinate values given in Table 1 provide discrete sections 34 comprising wireframe sections for defining the transition profile, the entire profile is defined by a best-fit curve to the given sections to define a smoothly continuous internal flow path formed by the interior surface of the transition duct 10. Further it may be noted that the data provided in Table 1 is computer generated and that limited deviations from this data may occur, within manufacturing tolerances, during production of the transition duct 10.

Referring to FIGS. 3-6 first, second, third and fourth sections 34_A, 34_B, 34_Cand 34_Ddepict the transition of the internal profile from the generally circular first cross-section 34_Aof FIG. 3, taken at θ=1°, to the generally rectangular arc-like fourth cross-section 34_Dof FIG. 6, taken at θ=30°. Each section may define a Cartesian X Y coordinate origin, as depicted by the section origins O_A, O_B, O_Cand O_D, with corresponding quadrants I, II, III and IV determined relative each respective section origin. The quadrants are numbered sequentially in accordance with a conventional Cartesian coordinate system, starting in the upper right-hand quadrant and proceeding counterclockwise.

The second section 34_Bof FIG. 4 is taken at θ=10° and comprises a first side 42_Bextending from the third quadrant to the second quadrant, and a second side 44_Bextending from the fourth quadrant to the first quadrant. An outer side 46_Bextends between the first and second quadrants and curves concave inwardly toward the coordinate origin O_B, and an inner side 48_Bextends between the third and fourth quadrants and curves concave inwardly toward the coordinate origin O_B. The first and second sides 42_B, 44_Bextend in diverging relation from the inner side 48_Btoward the outer side 46_B.

The third section 34_Cof FIG. 5 is taken at θ=21′ and defines a generally expanded rectangular cross-section comprising a first substantially linear side 42_Cextending from the third quadrant to the second quadrant, and a second substantially linear side 44_Cextending from the fourth quadrant to the first quadrant. An outer side 46_Cextends between the first and second quadrants and curves concave inwardly toward the coordinate origin O_C, and an inner side 48_Cextends between the third and fourth quadrants and curves concave inwardly toward the coordinate origin O_C, where the outer and inner sides 46_C, 48_Chave substantially less curvature than the outer and inner sides 46_B, 48_Bof the second section 34_B. The first and second sides 42_C, 44_Cextend in diverging relation from the inner side 48_Ctoward the outer side 46_C.

The fourth section 34_Dof FIG. 6 comprises a first substantially linear side 42_Dextending from the third quadrant to the second quadrant, and a second substantially linear side 44_Dextending from the fourth quadrant to the first quadrant. An outer side 46_Dextends between the first and second quadrants and curves concave inwardly toward the coordinate origin O_D, and an inner side 48_Dextends between the third and fourth quadrants and curves concave outwardly away from the coordinate origin O_D, where the outer and inner sides 46_D, 48_Dhave substantially less curvature than the outer and inner sides 46_D, 48_Dof the third section 34_C. The first and second sides 42_D, 44_Dextend in diverging relation from the inner side 48_Dtoward the outer side 46_D.

As an alternative embodiment to the invention the internal profile may be provided within an envelope of the profile given by the coordinate values of Table 1. By way of example and without limitation, the internal profile described herein may be provided within an envelope of ±6.350 mm normal to any surface with the X, Y and Z coordinate values and the angles θ noted in Table 1.

The transition duct 10 described herein provides a preferred transition duct internal profile for transitioning from a generally circular inlet to a generally rectangular arc-like outlet while minimizing stress concentrations and providing frequency separation between the natural frequency of the transition duct 10 and the combustion resonant frequencies, resulting in a reduced likelihood of low cycle fatigue cracks.

The X, Y and Z coordinate values, determined by the above-described Cartesian coordinated system, identified at corresponding sweep angles θ are summarized in the following Table 1.

TABLE 1

θ
X
Y
Z

1.0
0.000
174.094
18.310

1.0
27.361
171.930
18.348

1.0
54.047
165.510
18.460

1.0
79.411
155.021
18.643

1.0
102.856
140.749
18.892

1.0
123.849
123.068
19.200

1.0
141.929
102.418
19.561

1.0
156.693
79.282
19.965

1.0
167.221
53.951
20.407

1.0
172.981
27.122
20.875

1.0
174.705
−0.271
21.353

1.0
172.481
−27.629
21.831

1.0
166.351
−54.383
22.298

1.0
156.392
−79.957
22.744

1.0
142.206
−103.440
23.154

1.0
124.128
−124.084
23.515

1.0
103.029
−141.638
23.821

1.0
79.494
−155.761
24.067

1.0
54.074
−166.115
24.248

1.0
27.365
−172.441
24.359

1.0
0.000
−174.571
24.396

1.0
−27.365
−172.441
24.359

1.0
−54.074
−166.115
24.248

1.0
−79.494
−155.761
24.067

1.0
−103.029
−141.638
23.821

1.0
−124.128
−124.084
23.515

1.0
−142.206
−103.440
23.154

1.0
−156.392
−79.957
22.744

1.0
−166.351
−54.383
22.298

1.0
−172.481
−27.629
21.831

1.0
−174.705
−0.271
21.353

1.0
−172.981
27.122
20.875

1.0
−167.221
53.951
20.407

1.0
−156.693
79.282
19.965

1.0
−141.929
102.418
19.561

1.0
−123.849
123.068
19.200

1.0
−102.856
140.749
18.892

1.0
−79.411
155.021
18.643

1.0
−54.047
165.510
18.460

1.0
−27.361
171.930
18.348

2.0
0.000
172.882
36.673

2.0
27.425
170.707
36.749

2.0
54.172
164.267
36.974

2.0
79.605
153.780
37.340

2.0
103.155
139.561
37.837

2.0
124.329
122.002
38.450

2.0
142.717
101.544
39.164

2.0
157.939
78.639
39.964

2.0
168.504
53.281
40.850

2.0
173.677
26.280
41.793

2.0
175.011
−1.190
42.752

2.0
172.708
−28.597
43.709

2.0
166.805
−55.460
44.647

2.0
157.321
−81.274
45.548

2.0
143.277
−104.895
46.373

2.0
124.908
−125.350
47.088

2.0
103.514
−142.641
47.691

2.0
79.778
−156.547
48.177

2.0
54.227
−166.748
48.533

2.0
27.432
−172.989
48.751

2.0
0.000
−175.094
48.825

2.0
−27.433
−172.989
48.751

2.0
−54.228
−166.748
48.533

2.0
−79.779
−156.547
48.177

2.0
−103.515
−142.640
47.691

2.0
−124.908
−125.349
47.088

2.0
−143.278
−104.894
46.373

2.0
−157.321
−81.274
45.548

2.0
−166.805
−55.459
44.647

2.0
−172.708
−28.597
43.709

2.0
−175.011
−1.190
42.752

2.0
−173.677
26.281
41.793

2.0
−168.504
53.281
40.850

2.0
−157.939
78.639
39.964

2.0
−142.717
101.545
39.164

2.0
−124.329
122.002
38.450

2.0
−103.154
139.561
37.837

2.0
−79.605
153.780
37.340

2.0
−54.172
164.267
36.974

2.0
−27.425
170.707
36.749

3.0
0.000
170.905
55.141

3.0
27.478
168.722
55.256

3.0
54.277
162.274
55.594

3.0
79.774
151.808
56.142

3.0
103.427
137.665
56.883

3.0
124.785
120.255
57.796

3.0
143.484
100.021
58.856

3.0
159.159
77.375
60.043

3.0
169.755
52.007
61.372

3.0
174.377
24.875
62.794

3.0
175.350
−2.646
64.237

3.0
172.969
−30.082
65.675

3.0
167.263
−57.025
67.087

3.0
158.221
−83.037
68.450

3.0
144.337
−106.783
69.694

3.0
125.685
−127.030
70.755

3.0
103.987
−144.013
71.645

3.0
80.044
−157.662
72.361

3.0
54.364
−167.676
72.886

3.0
27.488
−173.809
73.207

3.0
−0.001
−175.880
73.315

3.0
−27.491
−173.809
73.207

3.0
−54.366
−167.676
72.885

3.0
−80.046
−157.661
72.361

3.0
−103.988
−144.012
71.645

3.0
−125.687
−127.029
70.755

3.0
−144.338
−106.782
69.694

3.0
−158.222
−83.036
68.450

3.0
−167.263
−57.024
67.086

3.0
−172.969
−30.081
65.674

3.0
−175.350
−2.645
64.237

3.0
−174.377
24.876
62.794

3.0
−169.755
52.008
61.372

3.0
−159.158
77.376
60.043

3.0
−143.484
100.022
58.856

3.0
−124.785
120.255
57.796

3.0
−103.427
137.665
56.883

3.0
−79.774
151.808
56.142

3.0
−54.277
162.275
55.594

3.0
−27.478
168.722
55.256

4.0
0.000
168.192
73.764

4.0
27.518
166.005
73.917

4.0
54.359
159.563
74.367

4.0
79.914
149.138
75.096

4.0
103.668
135.097
76.078

4.0
125.210
117.866
77.283

4.0
144.222
97.888
78.680

4.0
160.345
75.533
80.243

4.0
170.973
50.178
82.016

4.0
175.077
22.952
83.920

4.0
175.712
−4.593
85.846

4.0
173.252
−32.037
87.765

4.0
167.719
−59.031
89.653

4.0
159.088
−85.199
91.483

4.0
145.377
−109.054
93.151

4.0
126.454
−129.070
94.550

4.0
104.440
−145.696
95.713

4.0
80.288
−159.044
96.646

4.0
54.480
−168.836
97.331

4.0
27.533
−174.836
97.751

4.0
−0.001
−176.864
97.892

4.0
−27.536
−174.836
97.751

4.0
−54.483
−168.835
97.331

4.0
−80.290
−159.043
96.646

4.0
−104.442
−145.695
95.713

4.0
−126.455
−129.068
94.550

4.0
−145.378
−109.052
93.150

4.0
−159.088
−85.198
91.482

4.0
−167.720
−59.029
89.653

4.0
−173.252
−32.035
87.765

4.0
−175.712
−4.592
85.846

4.0
−175.077
22.953
83.920

4.0
−170.972
50.179
82.016

4.0
−160.345
75.534
80.243

4.0
−144.222
97.888
78.680

4.0
−125.209
117.866
77.283

4.0
−103.667
135.098
76.078

4.0
−79.913
149.138
75.096

4.0
−54.359
159.563
74.367

4.0
−27.518
166.005
73.917

5.0
0.000
164.766
92.589

5.0
27.545
162.582
92.780

5.0
54.416
156.161
93.342

5.0
80.020
145.800
94.248

5.0
103.871
131.890
95.465

5.0
125.598
114.869
96.954

5.0
144.925
95.182
98.677

5.0
161.493
73.152
100.604

5.0
172.156
47.836
102.819

5.0
175.772
20.554
105.206

5.0
176.088
−6.987
107.615

5.0
173.547
−34.413
110.015

5.0
168.167
−61.430
112.378

5.0
159.916
−87.715
114.678

5.0
146.389
−111.656
116.773

5.0
127.203
−131.416
118.501

5.0
104.866
−147.631
119.920

5.0
80.503
−160.632
121.058

5.0
54.573
−170.163
121.891

5.0
27.564
−176.005
122.402

5.0
−0.001
−177.981
122.575

5.0
−27.567
−176.004
122.402

5.0
−54.575
−170.162
121.891

5.0
−80.505
−160.631
121.057

5.0
−104.868
−147.630
119.920

5.0
−127.205
−131.414
118.501

5.0
−146.390
−111.654
116.773

5.0
−159.917
−87.713
114.678

5.0
−168.168
−61.428
112.378

5.0
−173.547
−34.412
110.015

5.0
−176.088
−6.986
107.615

5.0
−175.772
20.556
105.206

5.0
−172.156
47.837
102.819

5.0
−161.492
73.152
100.604

5.0
−144.925
95.183
98.677

5.0
−125.598
114.869
96.954

5.0
−103.871
131.890
95.465

5.0
−80.019
145.800
94.248

5.0
−54.416
156.161
93.342

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555.692

25.0
49.401
29.927
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25.0
73.992
27.561
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25.0
98.463
24.330
558.978

25.0
122.788
20.289
560.862

25.0
146.945
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563.098

25.0
170.717
9.463
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25.0
185.258
−7.751
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25.0
182.974
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584.273

25.0
178.609
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25.0
174.081
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25.0
169.370
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25.0
164.015
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25.0
147.790
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25.0
123.618
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25.0
98.904
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25.0
74.182
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25.0
49.455
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25.0
24.725
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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25.0
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27.561
557.471

25.0
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29.927
556.368

25.0
−24.723
31.378
555.692

26.0
0.000
30.974
581.420

26.0
24.601
30.561
581.621

26.0
49.169
29.340
582.217

26.0
73.674
27.339
583.193

26.0
98.088
24.590
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26.0
122.391
21.128
586.223

26.0
146.562
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26.0
170.428
11.744
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26.0
185.392
−4.833
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26.0
183.102
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26.0
178.611
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26.0
174.006
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26.0
169.273
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26.0
163.837
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26.0
147.117
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26.0
122.932
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26.0
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26.0
73.797
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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26.0
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29.340
582.217

26.0
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30.561
581.621

27.0
0.000
32.123
606.814

27.0
24.511
31.774
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27.0
48.997
30.737
607.520

27.0
73.436
29.028
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27.0
97.807
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27.0
122.090
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27.0
146.267
20.066
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27.0
170.199
15.459
615.304

27.0
185.508
−0.566
623.470

27.0
183.223
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634.454

27.0
178.628
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27.0
173.960
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27.0
169.208
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27.0
163.697
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27.0
146.563
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27.0
122.391
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27.0
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27.0
73.506
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27.0
49.017
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27.0
24.512
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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27.0
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30.737
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27.0
−24.511
31.774
606.992

28.0
0.000
35.676
631.344

28.0
24.452
35.375
631.505

28.0
48.886
34.474
631.983

28.0
73.282
32.984
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28.0
97.624
30.913
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28.0
121.895
28.270
635.282

28.0
146.080
25.067
636.985

28.0
170.056
20.942
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28.0
185.611
5.354
647.467

28.0
183.327
−15.943
658.791

28.0
178.652
−37.138
670.060

28.0
173.935
−58.325
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28.0
169.171
−79.505
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28.0
163.597
−100.486
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28.0
146.142
−114.796
711.352

28.0
121.990
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28.0
97.668
−112.919
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28.0
73.293
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28.0
48.878
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28.0
24.437
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28.0
−0.016
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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28.0
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30.913
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28.0
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28.0
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631.983

28.0
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631.505

29.0
0.000
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654.704

29.0
24.421
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654.854

29.0
48.827
40.866
655.302

29.0
73.202
39.521
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29.0
97.531
37.644
657.088

29.0
121.799
35.239
658.421

29.0
145.991
32.309
660.045

29.0
169.999
28.508
662.152

29.0
185.699
13.242
670.614

29.0
183.407
−7.818
682.288

29.0
178.678
−28.776
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29.0
173.930
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29.0
169.160
−70.680
717.133

29.0
163.554
−91.425
728.632

29.0
145.896
−105.340
736.345

29.0
121.762
−105.295
736.320

29.0
97.509
−102.781
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29.0
73.187
−100.831
733.846

29.0
48.816
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733.075

29.0
24.411
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732.614

29.0
−0.010
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732.460

29.0
−24.430
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732.614

29.0
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733.076

29.0
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29.0
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29.0
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29.0
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29.0
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29.0
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717.127

29.0
−173.932
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705.515

29.0
−178.680
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29.0
−183.408
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29.0
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13.249
670.610

29.0
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29.0
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29.0
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29.0
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37.645
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29.0
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39.522
656.047

29.0
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40.866
655.302

29.0
−24.420
41.675
654.854

30.0
0.000
51.170
676.592

30.0
24.441
50.916
676.739

30.0
48.868
50.153
677.179

30.0
73.267
48.882
677.913

30.0
97.623
47.105
678.939

30.0
121.923
44.821
680.258

30.0
146.153
42.034
681.867

30.0
170.198
38.368
683.983

30.0
185.821
23.186
692.749

30.0
183.411
2.319
704.797

30.0
178.648
−18.444
716.784

30.0
173.880
−39.206
728.771

30.0
169.107
−59.967
740.757

30.0
163.421
−80.501
752.612

30.0
145.485
−94.016
760.415

30.0
121.318
−93.624
760.189

30.0
97.066
−90.982
758.664

30.0
72.739
−88.929
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30.0
48.355
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756.634

30.0
23.933
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756.129

30.0
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755.966

30.0
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756.143

30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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30.0
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48.892
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30.0
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50.157
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30.0
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50.917
676.738

31.0
0.000
63.034
697.015

31.0
24.425
62.785
697.165

31.0
48.837
62.037
697.614

31.0
73.220
60.790
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31.0
97.563
59.046
699.411

31.0
121.849
56.806
700.757

31.0
146.067
54.071
702.401

31.0
170.107
50.489
704.553

31.0
185.821
35.549
713.530

31.0
183.473
14.911
725.930

31.0
178.704
−5.624
738.269

31.0
173.938
−26.160
750.609

31.0
169.175
−46.697
762.948

31.0
163.588
−67.034
775.168

31.0
145.851
−80.583
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31.0
121.716
−80.306
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31.0
97.488
−77.647
781.545

31.0
73.181
−75.576
780.300

31.0
48.815
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779.411

31.0
24.410
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778.877

31.0
−0.014
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778.699

31.0
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778.877

31.0
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31.0
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31.0
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31.0
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31.0
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31.0
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31.0
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31.0
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31.0
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31.0
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31.0
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31.0
−170.098
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31.0
−146.059
54.072
702.400

31.0
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56.807
700.757

31.0
−97.557
59.047
699.411

31.0
−73.216
60.790
698.363

31.0
−48.834
62.037
697.614

31.0
−24.424
62.785
697.165

While particular embodiments of the present invention have been illustrated and described, it would be obvious to those skilled in the art that various other changes and modifications can be made without departing from the spirit and scope of the invention. It is therefore intended to cover in the appended claims all such changes and modifications that are within the scope of this invention.

Transition duct for gas turbine engine

Information

Patent Number

Date Filed

Date Issued

Inventors

Original Assignees

Examiners

CPC

US Classifications

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US

International Classifications

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Abstract

Description

Claims

US Referenced Citations (1)

Related Publications (1)