Transition duct with enhanced profile optimization

Information

  • Patent Grant
  • 6644032
  • Patent Number
    6,644,032
  • Date Filed
    Tuesday, October 22, 2002
    22 years ago
  • Date Issued
    Tuesday, November 11, 2003
    21 years ago
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




2.904







3.0




−5.233




−3.340




2.859







3.0




−5.728




−2.384




2.809







3.0




−5.898




−1.929




2.785







3.0




−6.033




−1.462




2.760







3.0




−6.131




−0.986




2.735







3.0




−6.213




−0.019




2.685







3.0




−6.115




1.164




2.623







3.0




−5.792




2.307




2.563







3.0




−5.258




3.367




2.507







3.0




−4.529




4.304




2.458







3.0




−3.631




5.082




2.417







3.0




−2.971




5.487




2.396







3.0




−2.269




5.811




2.379







3.0




−1.532




6.051




2.367







3.0




−0.773




6.198




2.359







4.0




0.000




6.166




3.150







4.0




0.767




6.116




3.153







4.0




1.521




5.968




3.163







4.0




2.251




5.730




3.180







4.0




2.949




5.408




3.203







4.0




3.604




5.008




3.230







4.0




4.491




4.243




3.284







4.0




5.210




3.318




3.349







4.0




5.738




2.273




3.422







4.0




6.057




1.146




3.501







4.0




6.156




−0.020




3.582







4.0




6.134




−0.503




3.616







4.0




6.077




−0.984




3.649







4.0




5.981




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28.684







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27.0




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27.0




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27.0




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27.542







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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0.309




25.934







27.0




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27.0




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0.785




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27.0




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1.046




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27.0




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1.237




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1.355




25.401







28.0




0.000




1.496




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1.294




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26.448







28.0




2.585




1.375




26.496







28.0




3.869




1.227




28.575







28.0




5.142




1.021




26.684







28.0




6.400




0.749




26.829







28.0




6.682




0.641




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28.0




6.925




0.475




26.974







28.0




7.114




0.261




27.088







28.0




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0.010




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28.0




7.263




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28.0




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28.0




6.997




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28.0




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28.0




6.644




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28.0




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28.0




6.317




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28.0




6.145




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29.548







28.0




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28.0




5.683




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29.665







28.0




5.423




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29.686







28.0




4.338




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29.690







28.0




3.254




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29.686







28.0




2.169




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29.684







28.0




1.085




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29.684







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0.000




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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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27.365







28.0




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0.010




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28.0




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27.088







28.0




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0.475




26.974







28.0




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26.886







28.0




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26.829







28.0




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1.021




26.684







28.0




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1.227




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28.0




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1.375




26.496







28.0




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1.466




26.448







29.0




0.000




1.726




27.427







29.0




1.323




1.702




27.441







29.0




2.643




1.629




27.481







29.0




3.959




1.509




27.547







29.0




5.268




1.342




27.640







29.0




6.566




1.122




27.762







29.0




6.823




1.036




27.810







29.0




7.043




0.891




27.890







29.0




7.208




0.698




27.998







29.0




7.301




0.471




28.123







29.0




7.311




0.230




28.256







29.0




7.161




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28.687







29.0




6.993




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29.117







29.0




6.817




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29.0




6.633




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29.0




6.434




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30.400







29.0




6.337




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30.511







29.0




6.178




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30.604







29.0




5.973




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30.672







29.0




5.738




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29.0




5.490




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29.0




4.394




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30.690







29.0




3.296




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29.0




2.198




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30.639







29.0




1.099




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29.0




0.000




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29.0




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30.629







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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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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29.117







29.0




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28.687







29.0




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0.230




28.256







29.0




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0.471




28.123







29.0




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0.698




27.998







29.0




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0.891




27.890







29.0




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1.036




27.810







29.0




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1.122




27.762







29.0




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1.342




27.640







29.0




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1.509




27.547







29.0




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1.629




27.481







29.0




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1.702




27.441







30.0




0.000




2.073




28.367







30.0




1.342




2.052




28.379







30.0




2.683




1.990




28.415







30.0




4.020




1.887




28.474







30.0




5.352




1.743




28.558







30.0




6.678




1.557




28.665







30.0




6.918




1.484




28.707







30.0




7.121




1.352




28.784







30.0




7.268




1.172




28.887







30.0




7.343




0.962




29.009







30.0




7.339




0.741




29.136







30.0




7.165




−0.050




29.593







30.0




6.986




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30.0




6.804




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30.0




6.621




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30.961







30.0




6.433




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30.0




6.347




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30.0




6.199




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31.623







30.0




6.001




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31.691







30.0




5.772




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30.0




5.532




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30.0




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30.0




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31.607







30.0




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30.0




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30.0




0.000




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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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31.730







30.0




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30.0




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30.0




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30.0




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31.416







30.0




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30.0




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30.0




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30.0




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0.741




29.136







30.0




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29.009







30.0




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1.172




28.887







30.0




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1.352




28.784







30.0




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1.484




28.707







30.0




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1.557




28.665







30.0




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1.743




28.558







30.0




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1.887




28.474







30.0




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1.990




28.415







30.0




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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




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31.434







31.0




6.615




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31.909







31.0




6.431




−2.690




32.384







31.0




6.350




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32.499







31.0




6.205




−3.042




32.596







31.0




6.010




−3.157




32.665







31.0




5.783




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32.701







31.0




5.546




−3.215




32.700







31.0




4.444




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32.616







31.0




3.337




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32.550







31.0




2.227




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32.503







31.0




1.114




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32.475







31.0




0.000




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31.0




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32.475







31.0




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32.503







31.0




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32.550







31.0




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32.616







31.0




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32.700







31.0




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31.0




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31.0




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32.499







31.0




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32.384







31.0




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31.909







31.0




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31.0




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30.959







31.0




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30.484







31.0




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1.263




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31.0




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1.474




29.882







31.0




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1.677




29.760







31.0




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1.851




29.656







31.0




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1.979




29.579







31.0




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2.047




29.538







31.0




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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