EXHAUST FLOW MODIFIER, DUCT INTERSECTION INCORPORATING THE SAME, AND METHODS THEREFOR

Abstract

A duct intersection comprising a first duct portion and a second duct portion extending laterally from a side of the first duct portion. At least one flow modifier is mounted inside one of the first and second duct portions. The flow modifier is a contoured duct liner and/or the flow modifier includes at least one turning vane. The duct intersection may also include a transition portion extending between the first and second duct portions, wherein the transition portion has a length extending along a side of the first duct portion and a depth extending away from the side of the first duct portion, wherein the length is greater than a diameter of the second duct portion.

Claims

1-13. (canceled)

14-16. (canceled)

17. A method of improving gas flow in an exhaust system, the method comprising: determining a location having undesirable flow characteristics within a duct intersection having a first wall and a second wall angled relative to the first wall, the determined location being fluidically coupled to a duct having a selectively openable end portion; and providing a flow modifier in the duct intersection at the determined location, the flow modifier being anchored in a fixed position to a portion of the first wall and a portion of the second, such that fluid is inhibited from flowing between the flow modifier and both the portion of the first wall and the portion of the second wall, the flow modifier comprising a contoured duct liner including an outermost surface configured to modify the direction of gas flow at the determined location.

18. The method according to claim 17, wherein the location is determined with a computer aided design system.

19. The method according to claim 17, wherein the location is determined by measuring conditions at the duct intersection.

20. The method according to claim 19, wherein the conditions are selected from the group consisting of temperature, pressure, and velocity.

21-22. (canceled)

23. The method according to claim 17, wherein providing the flow modifier comprises gunning refractory material at the duct intersection at the determined location, wherein the refractory material comprises the flow modifier.

24-31. (canceled)

32. A method of improving gas flow in an exhaust system including at least one duct intersection, the method comprising: determining a location of a poor flow zone within the duct intersection including a first wall and a second wall intersecting with and angled relative to the first wall; and injecting a fluid at the determined location, thereby forming a flow modifier anchored in a fixed position to a portion of the first wall and a portion of the second wall, such that fluid is inhibited from flowing between the flow modifier and both the portion of the first wall and the portion of the second wall, wherein an outermost surface of the formed flow modifier is configured to modify the direction of fluid flow at the determined location.

33. The method of claim 32, wherein the flow modifier has a non-uniform thickness along a dimension of the flow modifier.

34. The method according to claim 32, wherein the location is determined with a computer aided design system.

35. The method according to claim 32, wherein the location is determined by measuring conditions at the duct intersection.

36. The method according to claim 35, wherein the conditions are selected from the group consisting of temperature, pressure, and velocity.

37. The method according to claim 32, wherein the flow modifier is a contoured duct liner.

38. The method according to claim 32, wherein providing the flow modifier comprises gunning refractory material at the duct intersection at the determined location, wherein the refractory material comprises the flow modifier.

39. The method according to claim 32, wherein the flow modifier comprises refractory material.

40. The method according to claim 32, wherein the outermost surface has a convex shape.

41. The method according to claim 32, wherein the determined location is fluidically coupled to a duct having a selectively openable end portion

42. The method of claim 17, wherein the flow modifier has a non-uniform thickness along a dimension of the contoured duct liner.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Non-limiting and non-exhaustive embodiments of the devices, systems, and methods, including the preferred embodiment, are described with reference to the following figures, wherein like reference numerals refer to like parts throughout the various view unless otherwise specified.

[0018] FIG. 1 is a schematic representation of a coke plant;

[0019] FIG. 2 is a schematic representation of a representative coke oven and associated exhaust system;

[0020] FIG. 3 is a side view in cross-section of an emergency stack and cross-over duct intersection indicating various flow anomalies near the intersection;

[0021] FIG. 4 is a side view in cross-section of a duct intersection according to an exemplary embodiment;

[0022] FIG. 5 is a perspective view of a fan manifold that extends between the duct fan and main stack of a coke plant;

[0023] FIG. 6 is a side view in cross-section of a traditional fan manifold indicating the velocity of gases traveling through the manifold and main stack;

[0024] FIG. 7 is a side view in cross-section of a modified fan manifold indicating the velocity of gases traveling through the manifold and main stack;

[0025] FIG. 8 is a side view in cross-section of a turning vane assembly according to an exemplary embodiment;

[0026] FIG. 9 is a perspective view of the turning vane assembly shown in FIG. 8;

[0027] FIG. 10 is a side view in cross-section of a fan manifold according to an exemplary embodiment indicating the velocity of gases traveling through the manifold and main stack;

[0028] FIG. 11A is a front view schematic representation of a duct intersection according to an exemplary embodiment;

[0029] FIG. 11B is a side view schematic representation of the duct intersection shown in FIG. 11A;

[0030] FIG. 12A is a front view schematic representation of a duct intersection according to an exemplary embodiment;

[0031] FIG. 12B is a side view schematic representation of the duct intersection shown in FIG. 12A;

[0032] FIG. 13 is a side view of a duct intersection according to another exemplary embodiment;

[0033] FIG. 14 is a schematic representation of a fluid injection system for use at a duct intersection;

[0034] FIG. 15A is a perspective view of an intermediate HRSG tie in with transition pieces at the tie-in joints;

[0035] FIG. 15B is a side view of an intermediate HRSG tie in with transition pieces at the tie-in joints;

[0036] FIG. 15C is a perspective view of an intermediate HRSG tie in with transition pieces at the tie-in joints; and

[0037] FIG. 15D is a top view of an intermediate HRSG tie in with transition pieces at the tie-in joints.

DETAILED DESCRIPTION

[0038] Provided herein is a contoured duct liner, a duct intersection, and methods of improving gas flow in an exhaust system. The described embodiments may be implemented as original designs or as retrofits to existing facilities. The disclosed designs have been found to improve flow, thermal conditions, and structural integrity at intersections or tie-ins in a coke oven or similar system. By optimizing the external and/or internal shape of intersections, the mixing can be improved, areas of relatively undesirable conditions can be minimized, and pressure drop losses at the intersection can be minimized. Reducing pressure losses at the intersections can help lower draft set point(s), which can lead to improved operation as well as potentially lower cost designs and maintenance. Furthermore, it can be advantageous to minimize the draft set point of the overall system to minimize infiltration of any unwanted outside air into the system.

[0039] Specific details of several embodiments of the technology are described below with reference to FIGS. 1-14. Other details describing well-known structures and systems often associated with coke making and/or duct design have not been set forth in the following disclosure to avoid unnecessarily obscuring the description of the various embodiments of the technology. Many of the details, dimensions, angles, and other features shown in the figures are merely illustrative of particular embodiments of the technology. Accordingly, other embodiments can have other details, dimensions, angles, and features without departing from the spirit or scope of the present technology. A person of ordinary skill in the art, therefore, will accordingly understand that the technology may have other embodiments with additional elements, or the technology may have other embodiments without several of the features shown and described below with reference to FIGS. 1-14.

[0040] FIG. 1 illustrates a representative coke plant 5 where coal 1 is fed into a battery of coke ovens 10 where the coal is heated to form coke. Exhaust gases (i.e. flue gases) from the coke ovens are collected in a common tunnel 12 which intersects emergency stack 14. Cross-over duct 16 is also connected to common tunnel 12 via the emergency stack 14. Hot flue gases flow through the cross-over duct 16 into a co-generation plant 18 which includes a heat recovery steam generator (HRSG) 20 which in turn feeds steam turbine 22. The flue gases continue on to a sulfur treatment facility 24 and finally the treated exhaust gases are expelled through main stack 28 via duct fans 26, which provide negative pressure on the entire system in addition to the draft created by gases rising through the main stack 28.

[0041] With further reference to FIG. 2, it can be appreciated that coke ovens 10 are connected to the common tunnel 12 via uptakes 15. Common tunnel 12 extends horizontally along the top of the coke ovens 10. An emergency stack 14 extends vertically from common tunnel 12 as shown. Cross-over duct 16 intersects emergency stack 14 at a duct intersection 30. In normal operation, the emergency stack 14 is closed whereby exhaust gases travel through the cross-over duct 16 to the co-generation plant 18 (see FIG. 1). In the event of a problem with the co-generation plant 18, or other downstream equipment, the emergency stack 14 may be opened to allow exhaust gases to exit the system directly. While the figures show the common tunnel 12 and cross-over duct 16 intersecting the emergency stack 14 at different elevations, the common tunnel 12 and cross-over duct 16 may intersect the emergency stack 14 at the same elevation. Furthermore, the technology disclosed herein may be applied to the intersections whether they are at the same elevation or different elevations.

[0042] FIG. 3 illustrates various flow anomalies present in traditional duct intersections, such as duct intersection 30. Flow anomaly 32 is a point of localized combustion that is due to poor flow/distribution. An additional area of poor flow/mixing distribution 36 is located in the emergency stack 14 across from the cross-over duct 16. A poor flow zone 34 (e.g. dead, stagnant, recirculation, separation, etc.) is located in cross-over duct 16. These poor flow zone areas contain separated flows which can dissipate useful flow energy. These potential poor flow spaces can also contain unwanted, unsteady vortical flow, sometimes enhanced by buoyancy or chemical reactions, which can contribute to unwanted, poor acoustics, forced harmonics, potential flow instabilities, and incorrect instrument readings. Incorrect instrument readings may occur if measurements are made in a poor flow zone that has conditions not representative of flow in the duct. Because of the nature of the poor flow zones, these areas can also cause particle drop out and promote particle accumulation.

[0043] FIG. 4 illustrates an improved duct intersection 130 according to an exemplary embodiment. Duct intersection 130 includes a first duct portion in the form of emergency stack 114 and a second duct portion in the form of cross-over duct 116 that extends laterally from a side of the emergency stack 114. In this embodiment, duct intersection 130 includes a plurality of flow modifiers (40, 42, 44) to improve exhaust flow. For example, flow modifier 40 is in the form of a contoured duct liner that is positioned at the intersection 130 of emergency stack 114 and cross-over duct 116. Flow modifier 40 occupies the area where traditional designs have poor flow and mixing such as flow anomaly 32 in FIG. 3. Flow modifier 42 is disposed in cross-over duct 116 to occupy the poor flow zone 34 shown in FIG. 3. Flow modifier 44 is disposed in the emergency stack 114 opposite the cross-over duct 116 and, in this case, occupies the poor mixing distribution region 36 shown in FIG. 3. With the addition of flow modifiers 40, 42, and 44 the flow F within intersection 130 is improved (see FIG. 4).

[0044] The duct liners reshape the internal contours of the duct, inherently changing the nature and direction of the flow path among other effects. The duct liners can be used to smooth or improve flow entrance or provide better transition from one path to another especially when there are limitations to do so with the duct shape. The contoured duct liners can be used to alleviate wall shear stress/erosion stemming from high velocities and particle accumulation from settling and/or particle impaction, which could result in slow or poor flow zones. The contoured duct liners also provide better duct transitions, or paths, for better flow transition and movement, mitigation of stress and thermal concentrations, and mitigation of flow separation, etc.

[0045] With continued reference to FIG. 4 it can be appreciated that, in this embodiment, the contoured duct liners 40, 42, and 44 are each comprised of a first contoured wall mated to an inside surface of the duct intersection and a second contoured wall mated to the first contoured wall. For example, contoured duct liner 40 includes a first contoured wall 50 which is mated to the inside surface 17 of emergency stack 114 and inside surface 19 of cross-over duct 116. Duct liner 40 also includes a second contoured wall 52 that is mated to the first contoured wall 50. In this case, the second contoured wall 52 is convex and extends into the flow F of the flue gases traveling through the duct intersection 130. Contoured duct liner 42 includes a first contoured wall 54 which is mated to an inside surface 19 of the cross-over duct 116. A second contoured wall 56 is mated to the first contoured wall 54 and is also convex. Similarly, contoured duct liner 44 includes a first contoured wall 58 mated to inside surface 17 of the emergency stack 114 and includes a second contoured wall 60 mated to the first contoured wall 58.

[0046] The first contoured walls of the contoured duct liners may be attached to the inside surfaces 17 and 19 by welding, fasteners, or the like. Similarly, the second contoured walls may be attached to their respective first contoured walls by appropriate fasteners or by welding. As one of ordinary skill in the art will recognize, the contoured duct liners may be comprised of various materials which are suitable for corrosive, high heat applications. For example, first contoured walls 50, 54, and 58 may be comprised of steel or other suitable material. The second contoured walls 52, 56, and 60 may comprise a refractory material such as ceramic that is capable of resisting the heat associated with the flue gases and local combustion. The selection of materials can be dependent on the thermal, flow, and chemical properties of the flue gases. Because the flue gases can be of varied temperatures, velocities, chemical composition, in which all can depend on many factors such as the time in the coking cycle, flow control settings, ambient conditions, at the locations in the coking oven system, etc., the material selection can vary as well. The internal lining layers for the hot duct tie-ins could have more significant refractory layers than for cold ducts. Selection of appropriate materials may take into account min/max temperatures, thermal cycling, chemical reactions, flow erosion, acoustics, harmonics, resonance, condensation of corrosive chemicals, and accumulation of particles, for example.

[0047] In an embodiment, the flow modifiers may comprise a multilayer lining that is built up with a relatively inexpensive material and covered with a skin. In yet another embodiment, refractory or similar material can be shaped via gunning (i.e. spraying). Better control of shaping via gunning may be accomplished by gunning in small increments or layers. In addition, a template or mold may be used to aid the shaping via gunning. A template, mold, or advanced cutting techniques may be used to shape the refractory (e.g. even in the absence of gunning for the main shape of an internal insert) for insertion into the duct and then attached via gunning to the inner lining of the duct. In yet another embodiment, the flow modifier may be integrally formed along the duct. In other words, the duct wall may be formed or “dented” to provide a convex surface along the interior surface of the duct. As used herein, the term convex does not require a continuous smooth surface, although a smooth surface may be desirable. For example, the flow modifiers may be in the form of a multi-faceted protrusion extending into the flow path. Such a protrusion may be comprised of multiple discontinuous panels and/or surfaces. Furthermore, the flow modifiers are not limited to convex surfaces. The contours of the flow modifiers may have other complex surfaces that may be determined by CFD analysis and testing, and can be determined by design considerations such as cost, space, operating conditions, etc.

[0048] FIG. 5 illustrates a traditional fan manifold 70 that extends between the duct fans 26 and main stack 28 (see FIG. 1). Fan manifold 70 comprises a plurality of branches 72, 74, and 76 which all intersect into plenum 80. As shown in the figure, branches 74 and 76 include flow diverters 78 while plenum 80 includes flow straightener 79. With reference to FIG. 6, which indicates velocity magnitude in the fan manifold 70, traditional fan manifold designs result in a high velocity flow 82 which can damage the duct as a result of high shear stress. In contrast, FIG. 7 illustrates a fan plenum 180 intersection which includes a turning vane assembly 90. In this case, the magnitude of the velocity flowing next to the surface of main stack 128 is much lower than in the conventional duct configuration shown in FIG. 6. The higher flow velocity 184 is displaced inward away from the inside wall of the main stack 128, thereby reducing shear stress on the wall and helping to prevent erosion and corrosion of the stack. Turning vanes inside the duct help direct the flow path for a more efficient process. Turning vanes can be used to better mix flow, better directing of flow, and mitigation of total pressure losses, for example.

[0049] With reference to FIGS. 8 and 9, the turning vane assembly 90 includes an inner vane 92 and an outer vane 94. In this embodiment, both the inner and outer vanes are disposed in the main stack 128. FIG. 8 provides exemplary dimensions by which a turning vane assembly could be constructed. However, these dimensions are exemplary and other dimensions and angles may be used. As perhaps best shown in FIG. 9 the inner vane 92 includes a leading portion 902 that connects to an angled portion 904, which, in turn, connects to trailing portion 906. As shown in the figure, the angled portion 904 tapers from a 100 inch width to an 80 inch width. Similarly, the trailing portion 906 tapers from an 80 inch width to a 50 inch width. Here again, the dimensions are only representative and may vary. In this embodiment, the angled portion 904 is angled at approximately 45 degrees; however, other angles may be used depending on the particular application. Outer vane 94 includes a leading portion 908 connected to an angled portion 910 which in turn is connected to a trailing portion 912. Outer turning vane 94 also includes side walls 914 and 916 as shown. Side walls 914 and 916 are canted inward towards the angled and trailing portions 910 and 912 at an angle A. In this embodiment angle A is approximately 10 degrees. Turning vane assembly 90 may be mounted or assembled into the main stack 128 with suitable fasteners or may be welded in place, for example.

[0050] In an exemplary embodiment shown in FIG. 10, a fan manifold plenum 280 intersects main stack 228 with a ramped transition. In this case, it can be appreciated that the fan manifold plenum 280 has an upper wall 281 which transitions into the main stack 228 at an angle. As shown by the velocity magnitude 282, this results in a lower flow velocity magnitude than with traditional fan manifold designs shown in FIGS. 5 and 6. It has been found that improving the intersection/transition from the duct fan to the main stack can reduce wear and erosion as well as ash buildup in the main stack. In addition to the ramped transition, contoured duct liners and/or turning vanes may be used together in combination. For example, contoured duct liners may be located in the slower velocity regions 202, 204, and 206 as shown in FIG. 10.

[0051] FIGS. 11A and 11B illustrate a duct intersection 230 according to another exemplary embodiment. In this embodiment, the duct intersection 230 includes an emergency stack 214 and a cross-over duct 216 with a transition portion 240 extending therebetween. Changing the size of the duct cross sectional areas near or at intersections can help improve flow performance. In general, increasing the size of the flow cross sectional area as in transition portion 240 can help reduce flow losses. The transition portion can help better transition flow from a duct to a joining duct at tie-ins or intersections. The transitions can be flared, swaged, swept, or the like to provide the desired flow behavior at the intersections. In addition, the transitions may converge or diverge with respect to the direction of flow. Converging and diverging portions may be used in combination, e.g. the duct may first converge and then diverge or vice versa. Furthermore, it should be understood that the embodiments may be implemented in various combinations. For example, a turning vane assembly, such as described above with respect to FIGS. 7-9, may be used in conjunction with the duct liners, whether fabricated or gunned in place, as well as transition portions.

[0052] The transition portion 240 has a length L extending along a side of the exhaust duct and a depth D extending away from the side of the exhaust duct. In this embodiment, the length is greater than a diameter d of the cross-over duct 216. The length L may be a function of the duct diameter d or the depth D. For example, the length L may be twice the depth D. FIGS. 12A and 12B illustrate a duct intersection 330 including a transition portion 340 that is similar to that shown in FIGS. 11A and 11B, except in this case the exhaust stack 314 includes an enlarged annular region 315 that is adjacent to the intersection 330. FIG. 13 illustrates yet another embodiment of a duct intersection 430 with an asymmetric transition portion 440. Depending on the desired design performance, external fins could be added to help enhance heat transfer with the surrounding ambient air. For example, external fins from the surfaces could be used to help cool localized hot spots.

[0053] Duct intersections can be designed, retrofitted, or modified to introduce fluids such as oxidizers (for better combustion or to remove PIC's, products of incomplete combustion), liquids such as water, fuels, inert gases, etc. to help better distribute combustion and mitigate hot spots or allow cooling of the hot stream. For example, fluid could be introduced to provide a boundary layer of cold inert fluid to mitigate hot spots at affected wall surfaces. The fluids, which could include liquids such as water, inert or other gases, could be used for cooling or mitigating certain chemical reactions. The ducts can be modified to accommodate ports or additional pathways for introducing fluids. Fluid introduction, if introduced from a pressurized source, could also create entrainment, thereby improving mixing or flow energy.

[0054] FIG. 14 illustrates a duct intersection 530 including a fluid injection system 540. Fluid injection system 540 is operative to inject fluid at particular regions in the intersection 530 to energize or direct flow, as well as insulate the surface of the ducts from exhaust gases. Fluid injection system 540 includes a controller 542 which is connected to a plurality of valves, or fluid injectors 544, via wiring 548. Each injector 544 is connected by tubing 546 to a fluid reservoir 550. It should be understood that the term fluid encompasses liquids as well as gases. Thus, the injection system 540 may inject liquids or gases into the exhaust flow. The injectors may be spaced optimally depending on design conditions. The injectors can inject fluid transversely into the duct, as shown in FIG. 14. Alternatively, the injectors could inject external fluid axially or along the exhaust flow direction at various locations. The injectors could also inject fluid at different injection angles. The direction and method of injection depends on the conditions that exist at the tie-ins and intersections. The injected fluid may come from an external pressurized source. In another embodiment, the fluid may be entrained through a port or valve by the draft of the exhaust flow.

[0055] The fluid injection system 540 may also include various sensors, such as temperature sensor 552 connected to controller 542 via cable 554. Various sensors, such as sensor 552, may provide feedback to controller 542 such that fluid may be injected at appropriate times. While the embodiment is illustrated as having a single temperature sensor, other additional sensors of different types of sensors may be employed in providing control feedback to controller 542. For example, other sensor may include pressure, velocity, and emissions sensors, such as an oxygen sensor.

[0056] The fluid injection system 540 may be used in conjunction with the contoured duct liners, turning vanes, and transition portions disclosed above. The contoured duct liners in conjunction with the fluid injection system may extend the use of the duct intersection as a true mixing zone and potentially a combustion chamber. Air and other additives (e.g. oxygen) may be injected into the intersection to allow better combustion and use of the tunnels as extended combustion zones. Also, a well-mixed duct intersection may be configured to act as a second combustion chamber. The addition of extra air into the duct intersection mixing zone can burn any excess flue gas and even cool off the intersection with excess air or other gases, such as nitrogen. For example, if the common tunnel is too hot and fully combusted, air may be injected to cool the process. In contrast, if the flue gas is not completely combusted before entering the heat recovery steam generator (HRSG), it could reduce the HRSG tubes, which are typically made of metal, leading to accelerated corrosion and failure. In this case, an oxidizer is added, such as air, to burn all the combustibles before entering the HRSG.

[0057] Although the embodiments have been described with respect to a duct intersection between an emergency stack and cross-over duct, the disclosed technology may be applicable to hot duct tie-ins, cold duct tie-ins, stack junctions, and HRSGs. For example, as shown in FIGS. 15A-15D, an intermediate HRSG tie in may include transition pieces (632, 634, 652) at the tie-in joints. Transitions 632 and 634 connect duct 622 to duct 630. Duct 630 connects to a rectangular tube 650 via transition piece 652.

[0058] Also contemplated herein are methods of improving gas flow in an exhaust system that includes at least one duct intersection. The methods may include any procedural step inherent in the structures described herein. In an embodiment, the method comprises determining a location of a low or poor flow zone, an area of poor combustion, or an area of poor mixing (i.e. areas of relatively undesirable conditions) within the duct intersection and providing a flow modifier at the determined location. Providing a flow modifier may include, for example and without limitation, mounting a duct liner within the duct, gunning a refractory material to the inside of the duct, mounting turning vanes within the duct, forming a convex surface along the duct, and combinations of the above. The location may be determined with a computer aided design system, such as a CFD system. The location may also be determined by measuring conditions at the duct intersection, such as temperature, pressure, and velocity. In another embodiment the method comprises determining a location of a poor flow zone within the duct intersection and injecting a fluid into the duct intersection at the determined location.

[0059] From the foregoing it will be appreciated that, although specific embodiments of the technology have been described herein for purposes of illustration, various modifications may be made without deviating from the spirit and scope of the technology. Further, certain aspects of the new technology described in the context of particular embodiments may be combined or eliminated in other embodiments. Moreover, while advantages associated with certain embodiments of the technology have been described in the context of those embodiments, other embodiments may also exhibit such advantages, and not all embodiments need necessarily exhibit such advantages to fall within the scope of the technology. Accordingly, the disclosure and associated technology can encompass other embodiments not expressly shown or described herein. Thus, the disclosure is not limited except as by the appended claims.

EXAMPLES

[0060] 1. A duct intersection, comprising: [0061] a first duct portion; [0062] a second duct portion extending laterally from a side of the first duct portion; and [0063] at least one flow modifier disposed inside one of the first and second duct portions.

[0064] 2. The duct intersection according to claim 1, wherein the flow modifier is a contoured duct liner.

[0065] 3. The duct intersection according to claim 2, wherein the contoured duct liner comprises a first contoured wall mated to an inside surface of the duct and a second contoured wall mated to the first contoured wall.

[0066] 4. The duct intersection according to claim 3, wherein the second contoured wall comprises a refractory material.

[0067] 5. The duct intersection according to claim 2, wherein the second duct portion tees into the first duct portion.

[0068] 6. The duct intersection according to claim 5, wherein the contoured duct liner is mounted inside the first duct portion.

[0069] 7. The duct intersection according to claim 5, wherein the contoured duct liner is mounted inside the second duct portion.

[0070] 8. The duct intersection according to claim 1, wherein the flow modifier includes at least one turning vane.

[0071] 9. The duct intersection according to claim 1, wherein the flow modifier comprises molded refractory material.

[0072] 10. The duct intersection according to claim 1, wherein the second duct portion extends laterally from the side of the first duct portion at an angle of less than 90 degrees.

[0073] 11. A contoured duct liner for use in a duct intersection, comprising: [0074] a first wall contoured to mate with an inside surface of a duct intersection; and [0075] a second wall attached to the first wall, wherein the second wall is contoured to modify the direction of gas flow within the duct intersection.

[0076] 12. The contoured duct liner according to claim 11, wherein the second wall includes at least one convex surface.

[0077] 13. The contoured duct liner according to claim 11, wherein the second wall comprises a refractory material.

[0078] 14. A coking facility exhaust system, comprising: [0079] an emergency stack; [0080] a crossover duct extending laterally from a side of the emergency stack; and [0081] a contoured duct liner, including a convex surface operative to modify the direction of gas flow proximate an intersection of the emergency stack and crossover duct.

[0082] 15. The coking facility exhaust system according to claim 14, further comprising a second contoured duct liner disposed on an inside surface of the crossover duct.

[0083] 16. An improved coking facility exhaust system including an emergency stack and a crossover duct extending laterally from a side of the emergency stack, the improvement comprising: [0084] a contoured duct liner, including a convex surface operative to modify the direction of gas flow proximate an intersection of the emergency stack and crossover duct.

[0085] 17. A method of improving gas flow in an exhaust system including at least one duct intersection, the method comprising: [0086] determining a location having undesirable flow characteristics within the duct intersection; and [0087] providing a flow modifier in the duct intersection at the determined location.

[0088] 18. The method according to claim 17, wherein the location is determined with a computer aided design system.

[0089] 19. The method according to claim 17, wherein the location is determined by measuring conditions at the duct intersection.

[0090] 20. The method according to claim 19, wherein the conditions are selected from the group consisting of temperature, pressure, and velocity.

[0091] 21. The method according to claim 17, wherein the flow modifier is a contoured duct liner.

[0092] 22. The method according to claim 17, wherein the flow modifier is at least one turning vane.

[0093] 23. The method according to claim 17, further comprising gunning refractory material on an inside surface of the duct intersection at the determined location, thereby providing the convex surface.

[0094] 24. A duct intersection, comprising: [0095] a first duct portion; [0096] a second duct portion extending laterally from a side of the first duct portion; and [0097] a transition portion extending between the first and second duct portions, wherein the transition portion has a length extending along a side of the first duct portion and a depth extending away from the side of the first duct portion, wherein the length is greater than a diameter of the second duct portion.

[0098] 25. The duct intersection according to claim 24, wherein the length is twice the depth.

[0099] 26. The duct intersection according to claim 24, wherein the transition portion is flared.

[0100] 27. The duct intersection according to claim 24, wherein the first duct portion includes an enlarged annular region and the transition portion extends between the enlarged annular region and the second duct portion.

[0101] 28. The duct intersection according to claim 24, wherein the second duct portion extends laterally from the side of the first duct portion at an angle of less than 90 degrees.

[0102] 29. The duct intersection according to claim 24, wherein the second duct portion tees into the first duct portion.

[0103] 30. The duct intersection according to claim 24, further comprising at least one flow modifier having a convex surface disposed inside one of the first and second duct portions.

[0104] 31. The duct intersection according to claim 30, further comprising at least one turning vane.

[0105] 32. A method of improving gas flow in an exhaust system including at least one duct intersection, the method comprising: [0106] determining a location of a poor flow zone within the duct intersection; and [0107] injecting a fluid into the duct intersection at the determined location.