Transition duct for gas turbine engine

Abstract

The transition duct (300) includes a liner tube (302) defining an inlet opening (318) and an outlet opening (316), and an outlet frame (304) connected to the liner tube and disposed about a perimeter of the outlet opening. The outlet frame defines an inner peripheral edge (418) surrounding the outlet opening and includes a first side panel (306), a second side panel (308), an outer diameter panel (310) disposed between the first side panel and the second side panel, and an inner diameter panel (312) disposed between the first side panel and the second side panel. An intermediate projection (420), a left projection (428) disposed on a left side of the intermediate projection, and a right projection (430) disposed on a right side of the intermediate projection extend from the inner diameter panel toward the outer diameter panel.

Description

Background Art

[0001] A gas turbine engine generally includes a compressor section, a turbine section, and a combustion section disposed between the compressor section and the turbine section. The compressor section includes multiple stages of rotating compressor blades and fixed compressor vanes. The combustion section generally includes multiple combustion chambers. The turbine section includes multiple stages of rotating turbine blades and fixed turbine vanes. The combustion chamber generates hot exhaust gas and directs the hot exhaust gas to the turbine section. The hot exhaust gas may be sucked into the gap between the combustion chamber and the turbine inlet. Summary of the invention

[0002] In one aspect, a transition duct includes a liner defining an inlet opening and an outlet opening, and an outlet frame connected to the liner and disposed around a periphery of the outlet opening. The outlet frame includes a first side panel, a second side panel, an outer diameter panel disposed between the first side panel and the second side panel, an inner diameter panel disposed between the first side panel and the second side panel, and a middle protrusion extending from the inner diameter panel toward the outer diameter panel.

[0003] In one aspect, the transition duct includes: a liner defining an inlet opening and an outlet opening; an outlet frame connected to the liner, the outlet frame defining an inner peripheral edge surrounding the outlet opening; a middle protrusion extending from the inner peripheral edge into the outlet opening; a left side protrusion disposed on the left side of the middle protrusion and extending from the inner peripheral edge into the outlet opening; and a right side protrusion disposed on the right side of the middle protrusion and extending from the inner peripheral edge into the outlet opening. BRIEF DESCRIPTION OF THE DRAWINGS

[0004] To easily identify the discussion of any particular element or act, the most significant digit(s) in a reference number refers to the figure number in which the element is first introduced.

[0005] Figure 1 is a longitudinal cross-sectional view of a gas turbine engine taken along a plane containing the longitudinal axis or central axis.

[0006] Figure 2 yes Figure 1 A longitudinal cross-sectional view of a combustion section of a gas turbine engine.

[0007] Figure 3 yes Figure 2 A perspective view of the transition duct is shown in FIG.

[0008] Figure 4 yes Figure 3 A portion of a perspective view of a transition duct is shown in FIG. 1 , which better illustrates the outlet frame.

[0009] Figure 5 yes Figure 3A portion of a perspective view of a transition duct is shown in , which better illustrates the protrusion. DETAILED DESCRIPTION

[0010] Before describing in detail any embodiment of the present invention, it should be understood that the present invention is not limited in its application to the details of the structure and arrangement of the components set forth in this description or shown in the following drawings. The present invention can have other embodiments and can be practiced or performed in various ways. In addition, it should be understood that the words and terms used herein are for descriptive purposes and should not be regarded as limiting.

[0011] Various techniques for systems and methods will now be described with reference to the accompanying drawings, wherein similar reference numerals represent similar elements throughout. The drawings discussed below in this patent document and the various embodiments for describing the principles of the present disclosure are intended to be illustrative only and should not be construed in any way to limit the scope of the present disclosure. It will be appreciated by those skilled in the art that the principles of the present disclosure may be implemented with any suitably arranged device. It should be understood that the functions described as being performed by certain system elements may be performed by multiple elements. Similarly, for example, an element may be configured to perform the functions described as being performed by multiple elements. Many innovative teachings of the present application will be described with reference to exemplary non-limiting embodiments.

[0012] In addition, it should be understood that, unless explicitly limited in some examples, the words or phrases used in this article should be interpreted broadly. For example, the terms "include", "have" and "include" and their derivatives mean to include but not limit. Unless the context clearly indicates otherwise, the singular forms "one", "a kind of" and "the" are also intended to include plural forms. In addition, the term "and / or" used in this article refers to and covers any combination and all possible combinations of one or more of the associated listed items in the associated listed items. Unless the context clearly indicates otherwise, the term "or" is inclusive, meaning and / or. The phrases "associated with..." and "associated with this" and their derivatives can mean including, included in, interconnected with, including, included in, connected to or connected with, connected to or connected with, able to communicate with, cooperate with, interlaced, juxtaposed, close to, combined with or combined with, have, have the characteristics of, etc. Furthermore, although multiple embodiments or configurations may be described herein, any features, methods, steps, components, etc. described with respect to one embodiment may also be applicable to other embodiments without specific statement to the contrary.

[0013] In addition, although the terms "first", "second", "third" etc. can be used herein to refer to various elements, information, functions or actions, these elements, information, functions or actions should not be limited by these terms. On the contrary, these digital adjectives are used to distinguish different elements, information, functions or actions from each other. For example, without departing from the scope of the present disclosure, the first element, the first information, the first function or the first action can be referred to as the second element, the second information, the second function or the second action, and similarly, the second element, the second information, the second function or the second action can be referred to as the first element, the first information, the first function or the first action.

[0014] Furthermore, in this specification, the term "axial" or "axially" refers to a direction along the longitudinal axis of the gas turbine engine. The term "radial" or "radially" refers to a direction perpendicular to the longitudinal axis of the gas turbine engine. The term "downstream" or "rearward" refers to a direction along the flow direction. The term "upstream" or "ahead" refers to a direction opposite to the flow direction.

[0015] Additionally, unless the context clearly indicates otherwise, the term "adjacent to..." may mean: one element is fairly close to another element but not in contact with the other element, or the element is in contact with another part. Furthermore, unless otherwise clearly indicated, the phrase "based on" is intended to mean "based at least in part on." The term "about" or "approximately" or similar terms are intended to encompass variations in the value of the dimension within normal industrial manufacturing tolerances. If no industry standard is available, a twenty percent variation will fall within the meaning of these terms unless otherwise indicated.

[0016] Figure 1 An example of a gas turbine engine 100 is illustrated, which includes a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a central axis 108. The compressor section 102 includes a plurality of compressor stages 110, wherein each compressor stage 110 includes a set of fixed vanes 112 or adjustable guide vanes and a set of rotating blades 114. The rotor 116 supports the rotating blades 114 to rotate about the central axis 108 during operation. In some configurations, a single integral rotor 116 extends the length of the gas turbine engine 100 and is supported for rotation by bearings at either end. In other configurations, the rotor 116 is assembled from several separate spools attached to each other, or may include multiple disk segments attached via one bolt or multiple bolts.

[0017] The compressor section 102 is in fluid communication with the inlet section 118 to allow the gas turbine engine 100 to draw atmospheric air into the compressor section 102. During operation of the gas turbine engine 100, the compressor section 102 draws in atmospheric air and compresses the air for delivery to the combustion section 104. The illustrated compressor section 102 is an example of one compressor section 102, wherein other arrangements and designs are possible.

[0018] In the illustrated configuration, the combustion section 104 includes a plurality of individual combustion chambers 120, each of which operates to mix a flow of fuel with compressed air from the compressor section 102 and combust the air-fuel mixture to produce a flow of high temperature, high pressure combustion gases or exhaust gases 122. Of course, many other arrangements of the combustion section 104 are possible.

[0019] The turbine section 106 includes a plurality of turbine stages 124, wherein each turbine stage 124 includes a number of stationary turbine blades 126 and a number of rotating turbine blades 128. The turbine stage 124 is arranged to receive exhaust gas 122 from the combustion section 104 at a turbine inlet 130 and expand the gas to convert heat and pressure energy into rotational or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For a gas turbine engine 100 used for power generation or as a prime mover, the turbine section 106 is also connected to a generator, pump, or other device to be driven. As with the compressor section 102, other designs and arrangements of the turbine section 106 are possible.

[0020] An exhaust portion 132 is positioned downstream of the turbine section 106 and is arranged to receive a flow of expanded exhaust gas 122 from the final turbine stage 124 in the turbine section 106. The exhaust portion 132 is arranged to effectively direct the exhaust gas 122 away from the turbine section 106 to ensure efficient operation of the turbine section 106. Many variations and design differences are possible in the exhaust portion 132. Therefore, the illustrated exhaust portion 132 is merely one example of those variations.

[0021] The control system 134 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and control various operations of the gas turbine engine 100. In a preferred configuration, the control system 134 is typically microprocessor-based and includes memory devices and data storage devices for collecting, analyzing, and storing data. In addition, the control system 134 provides output data to various devices including monitors, printers, indicators, etc. that allow a user to interact with the control system 134 to provide input or adjustments. In the example of a power generation system, a user can input a power output set point, and the control system 134 can adjust various control inputs to achieve the power output in an efficient manner.

[0022] The control system 134 can control various operating parameters, including but not limited to variable inlet guide vane position, fuel flow rate and pressure, engine speed, valve position, generator load, and generator excitation. Of course, other applications may have fewer or more controllable devices. The control system 134 also monitors various parameters to ensure that the gas turbine engine 100 is operating properly. Some of the parameters monitored may include inlet air temperature, compressor outlet temperature and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, etc. Many of these measurements are displayed to the user and recorded for later review if needed.

[0023] Figure 2 The diagram shows the Figure 1 A longitudinal cross-sectional view of a combustion section 200 used in a gas turbine engine 100 of FIG. The combustion section 200 may replace Figure 1 The combustion section 104 is provided.

[0024] The combustion section 200 includes a casing 204 and a plurality of combustion chambers 202 enclosed by the casing 204. The plurality of combustion chambers 202 are circumferentially arranged around the central axis 108 of the gas turbine engine 100 and are spaced apart from each other to define a can-type combustion chamber, wherein other arrangements are possible. The plurality of combustion chambers 202 are enclosed by the casing 204. A compressor outlet diffuser 206 is connected to the outlet of the compressor section 102 for providing compressed air 208 to the combustion chambers 202.

[0025] Each combustor 202 of the illustrated configuration includes a head end section 210 connected to a transition duct 300. The head end section 210 includes a premixer fuel injector 212, which includes a premixer fuel supply pipe 214 and a pilot burner 216. The premixer fuel supply pipe 214 injects fuel into the combustor 202. The fuel is mixed with the compressed air 208 and ignited by the pilot burner 216 to produce exhaust gas 218. Other arrangements of the combustor 202 are possible.

[0026] The transition duct 300 defines an interior 220 through which the exhaust gas 218 passes. The transition duct 300 is adjacent to the turbine inlet 130. The exhaust gas 218 exits the transition duct 300 and enters the turbine section 106 through the turbine inlet 130. There is a gap 222 between the transition duct 300 and the turbine inlet 130. A portion of the exhaust gas 218 may be drawn into the gap 222. Purge air may be used to reduce the amount of exhaust gas 218 drawn into the gap 222. The purge air includes compressed air 208.

[0027] Figure 3A perspective view of a transition duct 300 is illustrated. The transition duct 300 includes a liner 302 surrounding the interior 220. The liner 302 defines an inlet opening 318 and an outlet opening 316. The transition duct 300 has an outlet frame 304 connected to the liner 302 and disposed around the perimeter of the outlet opening 316.

[0028] The outlet frame 304 includes a first side panel 306, a second side panel 308, an outer diameter panel 310 disposed between the first side panel 306 and the second side panel 308, and an inner diameter panel 312 disposed between the first side panel 306 and the second side panel 308. A frame head 314 is disposed above and extends from the outer diameter panel 310. The first side panel 306, the second side panel 308, the outer diameter panel 310, and the inner diameter panel 312 surround an outlet opening 316. The exhaust gas 218 exits the transition duct 300 through the outlet opening 316 and enters the turbine section 106.

[0029] The outer diameter panel 310, the inner diameter panel 312, the first side panel 306 and the second side panel 308 are formed as a single piece. In other configurations, the inner diameter panel 312, the first side panel 306 and the second side panel 308 may be formed as separate pieces and connected to each other, such as by welding.

[0030] Figure 4 Pictured Figure 3 4. A portion of a perspective view of transition duct 300 is shown in FIG. 3, which better illustrates outlet frame 304. First side panel 306 defines first side edge 402. Second side panel 308 defines second side edge 404. Outer diameter panel 310 defines outer edge 406. Inner diameter panel 312 defines inner edge 408.

[0031] The outer edge 406 is connected to the first side edge 402 by a first outer edge fillet 410 and to the second side edge 404 by a second outer edge fillet 412. The inner edge 408 is connected to the first side edge 402 by a first inner edge fillet 416 and to the second side edge 404 by a second inner edge fillet 414. The first side edge 402, the first outer edge fillet 410, the outer edge 406, the second outer edge fillet 412, the second side edge 404, the second inner edge fillet 414, the inner edge 408 and the first inner edge fillet 416 cooperate to define an inner peripheral edge 418. The inner peripheral edge 418 surrounds the outlet opening 316. The first outer edge fillet 410 and the second outer edge fillet 412 are defined by a non-circular elliptical curve. The first inner edge fillet 416 and the second inner edge fillet 414 are defined by a circular elliptical curve. In other configurations, the first outer edge fillet 410 , the second outer edge fillet 412 , the first inner edge fillet 416 , and the second inner edge fillet 414 may be defined by curves of any shape to meet the requirements of the gas turbine engine 100 .

[0032] The inner edge 408 includes a middle protrusion 420, a left protrusion 428 disposed on the left side of the middle protrusion 420, a right protrusion 430 disposed on the right side of the middle protrusion 420, and a non-protrusion portion 424. The middle protrusion 420 extends outward from the inner diameter panel 312 to a radial peak 422 toward the outer diameter panel 310. The non-protrusion portion 424 extends outward from the inner diameter panel 312 and extends between the first side panel 306 and the second side panel 308 along a curve. The curve follows a second-order polynomial. The height of the middle protrusion 420 is measured from the radial peak 422 of the middle protrusion 420 to the inner edge projection 426 located below the middle protrusion 420. The radial peak 422 is in the same plane as the inner diameter panel 312. The height of the middle protrusion 420 is between 3 mm and 30 mm. The height of the left protrusion 428 is measured in the same manner as the middle protrusion 420. The height of the right protrusion 430 is measured in the same manner as the middle protrusion 420. The middle protrusion 420, the left protrusion 428, and the right protrusion 430 have the same height. In other configurations, the inner edge 408 may include less than three protrusions or more than three protrusions and / or protrusion heights of other sizes to meet the requirements of the gas turbine engine 100.

[0033] Figure 5 Pictured Figure 3 4, which better illustrates the middle protrusion 420, the left protrusion 428, and the right protrusion 430. The middle protrusion 420 extends outward from the inner diameter panel 312 to the head end section 210 ( Figure 2). The depth of the middle protrusion 420 is measured perpendicular to the inner diameter face plate 312 from the transverse peak 502 of the middle protrusion 420. The transverse peak 502 is disposed on the liner 302. The depth of the left protrusion 428 is measured in the same manner as the middle protrusion 420. The depth of the right protrusion 430 is measured in the same manner as the middle protrusion 420.

[0034] exist Figure 5 In the configuration shown in FIG. 4 , the depth of the middle protrusion 420 is greater than the depth of the left protrusion 428 and the depth of the right protrusion 430. The depth of the left protrusion 428 is equal to the depth of the right protrusion 430. In other configurations, the protrusions may have different depths, for example, the depth of the middle protrusion 420 may be equal to or less than the depth of the left protrusion 428 and / or the depth of the right protrusion 430, or the depth of the left protrusion 428 may be different from the depth of the right protrusion 430.

[0035] Each of the middle protrusion 420, the left protrusion 428, and the right protrusion 430 has a tapered surface that tapers from the inner diameter face plate 312 to the transverse peak 502, and tapers from the radial peak 422 to the transverse peak 502, thereby forming a wedge shape. The middle protrusion 420, the left protrusion 428, and the right protrusion 430 are solid. In other configurations, the middle protrusion 420, the left protrusion 428, and the right protrusion 430 may be hollow, or may be formed from sheet material and welded to the inner diameter face plate 312 and the liner 302 as desired.

[0036] In operation, refer to Figures 1 to 5 The middle protrusion 420, the left protrusion 428, and the right protrusion 430 of the inner diameter panel 312 define the following profile: the profile reduces the amount of exhaust gas 218 sucked into the gap 222 between the transition duct 300 and the turbine inlet 130. Therefore, the amount of purge air used to purge the exhaust gas 218 out of the gap 222 is reduced. The purge air includes compressed air 208. Therefore, the performance of the combustion chamber 120 is improved and the emissions of the combustion chamber 120 are reduced. The first outer edge fillet 410 connecting the outer diameter panel 310 with the first side panel 306 and the second outer edge fillet 412 connecting the outer diameter panel 310 with the second side panel 308 have a non-circular elliptical shape, which reduces the deformation of the gap between the outer diameter panel 310 and the fixed turbine blades 126 at the turbine inlet 130, so that a uniform circumferential radial gap is maintained.

[0037] Although the exemplary embodiments of the present disclosure have been described in detail, those skilled in the art will understand that various changes, substitutions, variations, and improvements may be made to what is disclosed herein without departing from the spirit and scope of the disclosure in its broadest form.

[0038] Nothing in this application should be construed as implying that any particular element, step, act, or function is essential to be included in the claims: the scope of patented subject matter is limited only by the allowed claims. Furthermore, unless the exact phrase "means for..." is followed by a participle, none of the claims are intended to invoke a means-plus-function claim construction.

[0039] Reference numerals

[0040] 100 Gas turbine engines

[0041] 102 Compressor Section

[0042] 104 Combustion Section

[0043] 106 Turbine section

[0044] 108 Central Axis

[0045] 110 compressor stages

[0046] 112 Fixed blades

[0047] 114 Rotating Blades

[0048] 116 Rotor

[0049] 118 Entrance section

[0050] 120 Combustion Chamber

[0051] 122 Exhaust

[0052] 124 turbine stages

[0053] 126 Fixed turbine blades

[0054] 128 Rotating turbine blades

[0055] 130 Turbine inlet

[0056] 132 Exhaust section

[0057] 134 Control System

[0058] 200 Combustion Section

[0059] 202 Combustion Chamber

[0060] 204 Shell

[0061] 206 Compressor outlet diffuser

[0062] 208 Compressed air

[0063] 210 Head end section

[0064] 212 Premixer fuel injector

[0065] 214 Premixer fuel supply pipe

[0066] 216 Pilot Burner

[0067] 218 Exhaust

[0068] 220 Interior

[0069] 222 Gap

[0070] 300 Transition Pipe

[0071] 302 Liner

[0072] 304 Exit Framework

[0073] 306 First side panel

[0074] 308 Second side panel

[0075] 310 OD Panel

[0076] 312 ID Panel

[0077] 314 frame header

[0078] 316 Exit opening

[0079] 318 Entrance Opening

[0080] 402 First side edge

[0081] 404 Second side edge

[0082] 406 Outer Edge

[0083] 408 Inner Edge

[0084] 410 First outer edge fillet

[0085] 412 Second outer edge fillet

[0086] 414 Second inner edge fillet

[0087] 416 First inner edge fillet

[0088] 418 Inner edge

[0089] 420 middle bulge

[0090] 422 Radial Peak

[0091] 424 Non-raised part

[0092] 426 Inner Edge Projection

[0093] 428 Left side raised

[0094] 430 right side raised

[0095] 502 Horizontal Peak

Claims

1. A transition pipeline, comprising: a liner defining an inlet opening and an outlet opening; as well as An outlet frame connected to the liner and disposed around a periphery of the outlet opening, the outlet frame comprising: first side panel; second side panel; an outer diameter panel, the outer diameter panel being disposed between the first side panel and the second side panel; an inner diameter panel disposed between the first side panel and the second side panel; and A middle protrusion extends from the inner diameter panel toward the outer diameter panel.

2. The transition duct according to claim 1, wherein: The inner diameter panel defines an inner edge including a non-raised portion and the intermediate projection.

3. The transition duct according to claim 2, wherein: The non-raised portion extends between the first side panel and the second side panel along a curve defined by a second-order polynomial.

4. The transition duct according to claim 2, wherein: The height of the intermediate protrusion is measured from a projection of a radial peak of the intermediate protrusion to the inner edge below the radial peak, wherein the radial peak is in the same plane as the inner diameter panel, and wherein the height is between 3 mm and 30 mm. 5 . The transition duct according to claim 4 , further comprising a left side boss positioned to the left of the middle boss and a right side boss positioned to the right of the middle boss.

6. The transition duct according to claim 5, wherein: The height of the left protrusion and the height of the right protrusion are equal to the height of the middle protrusion.

7. The transition duct according to claim 5, wherein: The depth of the middle projection is measured from a lateral peak of the middle projection to the inner diameter face plate, wherein the lateral peak is disposed on the liner, and wherein the depth of the middle projection is greater than a depth of the left projection.

8. The transition duct according to claim 7, wherein: The depth of the left protrusion is equal to the depth of the right protrusion.

9. The transition duct according to claim 7, wherein: The intermediate projection has a tapered surface that tapers from the radial peak to the lateral peak.

10. The transition duct according to claim 1, wherein: The outer diameter panel defines an outer edge, and the first side panel defines a first side edge, wherein the outer edge and the first side edge are joined by a first outer edge fillet, and wherein the first outer edge fillet is defined by a non-circular elliptical curve.

11. A transition pipe comprising: a liner defining an inlet opening and an outlet opening; an outlet frame connected to the liner, the outlet frame defining an inner peripheral edge surrounding the outlet opening; a central protrusion extending from the inner peripheral edge into the outlet opening; a left protrusion, the left protrusion being disposed on the left side of the middle protrusion and extending from the inner peripheral edge into the outlet opening; as well as A right protrusion is disposed on the right side of the middle protrusion and extends from the inner peripheral edge into the outlet opening.

12. The transition duct according to claim 11, wherein: The inner peripheral edge includes an inner edge, and wherein the middle protrusion, the left protrusion, and the right protrusion extend from the inner edge.

13. The transition duct according to claim 12, wherein: The inner edge, the middle protrusion, the left protrusion, and the right protrusion cooperate to define a continuous curve.

14. The transition duct according to claim 12, wherein: The inner edge extends from one side to the other side and includes a non-raised portion, the middle raise, the left raise, and the right raise.

15. The transition duct according to claim 14, wherein: The non-convex portion has a curve defined by a second-order polynomial.

16. The transition duct according to claim 12, wherein: The height of the intermediate protrusion is measured from a projection of a radial peak of the intermediate protrusion to the inner edge below the radial peak, wherein the radial peak is in the same plane as the inner diameter panel, and wherein the height is between 3 mm and 30 mm.

17. The transition duct according to claim 16, wherein: The depth of the middle protrusion is measured from a lateral peak of the middle protrusion to the outlet frame, wherein the lateral peak is disposed on the liner, and wherein the depth of the middle protrusion is greater than the depth of the left protrusion.

18. The transition duct according to claim 17, wherein: The depth of the left protrusion is equal to the depth of the right protrusion.

19. The transition duct according to claim 17, wherein: The intermediate projection has a tapered surface that tapers from the radial peak to the lateral peak.

20. The transition duct according to claim 11, wherein: The inner peripheral edge includes an outer edge and a first side edge, wherein the outer edge and the first side edge are connected by a first outer edge fillet, and wherein the first outer edge fillet is defined by a non-circular elliptical curve.

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