combustion liner

Abstract

A liner for a combustor in a gas turbine engine and an associated method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a joint geometry extending through the liner body. The joint geometry includes a plurality of discrete dilution holes, an annular groove, and a plurality of dilution inserts. The dilution passage is configured to (i) combine a first dilution air flow flowing from the cold side to the hot side through the dilution passage and a second dilution air flow flowing from the cold side to the hot side through the dilution passage into a combined dilution air flow, and (ii) inject the combined dilution air flow into a core primary combustion zone of the combustor to achieve a predetermined combustion state of the combustor.

Description

Technical Field

[0001] The present disclosure relates to a combustion liner. In particular, the present disclosure relates to a combustion liner for a combustor in a gas turbine engine, the liner having dilution openings and passages surrounding the dilution openings. Background Art

[0002] A gas turbine engine includes a combustion section with a combustor that generates combustion gases, which are discharged into the turbine section of the engine. The combustion section includes a combustion liner. Current combustion liners include dilution openings therein. The dilution openings provide a dilution air flow to the combustor. The dilution air flow mixes with the primary zone product within the combustor. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] Features and advantages will become apparent from the following description of various exemplary embodiments as illustrated in the drawings, in which like reference numbers generally indicate identical, functionally similar, and / or structurally similar elements.

[0004] Figure 1 A schematic cross-sectional view of a combustion section of a gas turbine engine is shown according to an embodiment of the present disclosure.

[0005] Figure 2 Shown is a schematic side perspective view of a dilution passage through a combustion liner for a combustor, according to an embodiment of the present disclosure.

[0006] Figure 3 The embodiment according to the present disclosure is shown Figure 2 Schematic side view of the dilution channel of the lining.

[0007] Figure 4 The embodiment according to the present disclosure is shown Figure 2 A schematic side perspective view of a mirrored version of a combustion liner.

[0008] Figure 5 The embodiment according to the present disclosure is shown Figure 4 Schematic side perspective view of the dilution channel of the liner.

[0009] Figure 6 A schematic partial bottom perspective view of a dilution channel for a liner of a combustor is shown according to an embodiment of the present disclosure.

[0010] Figure 7 The embodiment of the present disclosure shows the outer lining and the inner lining. Figure 6 Schematic perspective view of the dilution channel.

[0011] Figure 8A schematic partial bottom perspective view of a dilution channel for a liner of a combustor is shown according to an embodiment of the present disclosure.

[0012] Figure 9 The embodiment of the present disclosure shows the outer lining and the inner lining. Figure 8 Schematic perspective view of the dilution channel.

[0013] Figure 10 A schematic partial bottom perspective view of a dilution channel for a liner of a combustor is shown according to an embodiment of the present disclosure.

[0014] Figure 11 The embodiment of the present disclosure shows the outer lining and the inner lining. Figure 10 Schematic perspective view of the dilution channel.

[0015] Figure 12 A schematic side view of dilution air flow through a dilution channel of a liner is shown according to an embodiment of the present disclosure.

[0016] Figure 13 A schematic top view of dilution air flow through the dilution channels of a liner is shown according to an embodiment of the present disclosure.

[0017] Figure 14 A schematic side view of a dilution channel of a combustion liner is shown according to an embodiment of the present disclosure.

[0018] Figure 15 A schematic side view of a dilution channel of a combustion liner is shown according to an embodiment of the present disclosure.

[0019] Figure 16 A schematic side view of a dilution channel of a combustion liner is shown according to an embodiment of the present disclosure.

[0020] Figure 17 A schematic side view of a dilution channel of a combustion liner is shown according to an embodiment of the present disclosure.

[0021] Figure 18 A schematic side view of a dilution passage through the outer and inner liners of a combustor is shown, according to an embodiment of the present disclosure.

[0022] Figure 19 A schematic side view of a dilution channel of a combustion liner is shown according to an embodiment of the present disclosure.

[0023] Figure 20 A schematic top view of exemplary inner and outer liner dilution channels of a combustor is shown according to an embodiment of the present disclosure.

[0024] Figure 21A schematic top view of exemplary inner and outer liner dilution channels of a combustor is shown according to an embodiment of the present disclosure.

[0025] Figure 22 A schematic flow chart of a method of passing a dilution flow through a combustor liner of a combustor is shown, according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0026] The features, advantages and embodiments of the present disclosure are set forth or apparent from consideration of the following detailed description, drawings and claims. In addition, it should be understood that the following detailed description is exemplary and is intended to provide further explanation without limiting the scope of the disclosure as claimed.

[0027] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0028] Reference will now be made in detail to the present embodiments of the disclosed subject matter, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and the description have been used to refer to like or similar parts of the disclosed subject matter. As used herein, the terms "first," "second," "third," "fourth," and "exemplary" are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of each component.

[0029] The terms "upstream" or "front" and "downstream" or "rear" refer to relative directions relative to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing. For example, "front" refers to the front end or direction of an engine, and "rear" refers to the rear end or direction of an engine.

[0030] Gas turbine engines, such as those used to power aircraft or industrial applications, include a compressor, a combustor, and a turbine arranged around a central engine axis, with the compressor positioned axially upstream of the combustor and the turbine positioned axially downstream of the combustor. The compressor pressurizes an air supply, the combustor combusts a hydrocarbon fuel in the presence of the pressurized air, and the turbine extracts energy from the resulting combustion gases. The combustor's air pressure ratio and / or outlet temperature can be varied to improve gas turbine engine cycle efficiency. Furthermore, any changes in the combustor's air pressure ratio and / or outlet temperature can impact the operability and lifespan of the turbine. Combustor outlet temperatures exceeding 1100°C are currently common in gas turbine engines, while acceptable metal temperatures for the turbine's stationary nozzles and rotating blades remain limited to 900°C or 1000°C. Furthermore, the temperature of the turbine blades affects the blades' mechanical strength (e.g., creep and fatigue) as well as their resistance to oxidation and corrosion. Maintaining combustor temperatures within an acceptable range can significantly improve the lifespan of the turbine blades and turbine nozzles. Structurally, the combustor liner is arranged inside the combustor to withstand extreme thermal loads, and extensive combustor liner cooling arrangements may reduce thermal stresses in several mechanical parts and components of the gas turbine engine.

[0031] In the combustor of a gas turbine engine, air generally flows through outer and inner passages surrounding the combustor liner. The air flows from the upstream end of the combustor liner to the downstream end of the combustor liner. Some of the air flowing through the outer and inner passages is diverted through a plurality of dilution holes provided in the combustor liner and enters the core primary combustion zone as dilution air. One purpose of the dilution air flow is to cool (i.e., quench) the combustion gases in the core primary combustion zone before the gases enter the turbine section. However, the combustion products from the core primary combustion zone of the combustor must be quenched quickly and efficiently to minimize the high temperature areas and thereby reduce NO from the combustion system. x emission.

[0032] It is known to use discrete dilution holes (also referred to as "discrete holes") and annular dilution slots (also referred to as "annular slots") through the liner, which essentially form flow channels through the liner. In the case of discrete dilution, high turbulence is introduced from multiple discrete jets into the core primary combustion zone of the combustor. As a result, good mixing of the combustion products is achieved after dilution. However, due to the low jet penetration, some high temperature areas still exist within the combustor core. Further, the wake regions formed behind the discrete dilution jets and between the discrete dilution jets cause low cooling and low mixing of the dilution air with the primary combustion products. On the other hand, in annular dilution, the jet penetration level is high, but the turbulence generated is low, resulting in a low level of mixing of the dilution air with the primary zone products after the dilution flow enters, causing potentially higher temperatures in the core of the combustion chamber after dilution, thereby causing a higher outlet temperature profile / pattern and potentially negatively affecting combustion efficiency.

[0033] The present disclosure provides a method for synergistically combining the advantages of discrete dilution and annular dilution. A combustor includes a liner body having a cold side and a hot side. The liner body includes a dilution channel having a concatenated geometry extending through the liner body. A first dilution air flow and a second dilution air flow pass through the dilution channel from the cold side of the combustion liner to the hot side of the combustor liner. The dilution channel also includes a protruding dilution insert extending radially inward from each discrete dilution hole. The dilution channel merges the first dilution air flow and the second dilution air flow within the concatenated geometry into a combined dilution air flow, and injects the combined dilution air flow into a core primary combustion zone of the combustor to achieve a predetermined combustion state of the combustor.

[0034] Figure 1 A schematic cross-sectional view of a combustion section 100 of a gas turbine engine according to an embodiment of the present disclosure is shown. The combustion section 100 includes a combustor 112 that generates combustion gases that are discharged into the turbine section (not shown) of the engine. The combustor 112 includes a core primary combustion zone 114. The core primary combustion zone 114 is defined by an outer liner 116, an inner liner 118, and a shroud 120. Additionally, a diffuser 122 is positioned upstream of the core primary combustion zone 114. The diffuser 122 receives airflow from the compressor section (not shown) of the engine and provides a flow of compressed air to the combustor 112. The diffuser 122 provides the flow of compressed air to the shroud 120 of the swirler 124. The air flows through an outer passage 126 and an inner passage 128.

[0035] Figure 2 and Figure 3 is a schematic representation of a liner for a combustor according to an embodiment of the present disclosure. Figure 2, a side perspective view 210 schematically illustrates a dilution passage 211 extending through a combustion liner for a combustor. Figure 3 , reference numeral 220 indicates a display Figure 2 The dilution channel 211 has a geometric structure formed by joining the exemplary first geometric structure and the exemplary second geometric structure (or physically joining two adjacent entities end to end so that they are fused into one entity). Figure 2 and Figure 3 A first geometric structure, embodied as a plurality of discrete dilution holes 212 , and a second geometric structure, embodied as an annular groove 214 extending through the combustor liner, are joined to form a dilution passage 211 .

[0036] The discrete dilution holes 212 and the annular groove 214 are connected at predetermined relative positions. Figure 2 and Figure 3 , the discrete dilution holes 212 are positioned forward or upstream, and the annular groove 214 is positioned rearward or downstream. The discrete dilution holes 212 have a semicircular cross-section. Although not shown, a bridge structure can connect the discrete holes 212 to the annular groove 214 to allow control of the dilution gap between the annular groove 214 and the discrete holes 212. The bridge structure can be connected to the rear of the liner forming the annular groove 214 (e.g., Figure 14 In some examples, the bridge structure can be welded to the annular groove 214. The bridge structure can support and control the dilution gap.

[0037] In the connected geometry of the dilution passage 211, the first dilution air flow 213 passing through the discrete dilution holes 212 is combined with the second dilution air flow 215 passing through the annular groove 214 to form a combined dilution air flow 217. Further, the combined dilution air flow 217 is injected into the Figure 1 The primary combustion zone 114 of the burner 112 is formed to achieve a predetermined combustion state of the burner 112 .

[0038] The combined dilution air flow 217 improves multiple desired combustion conditions of the combustor. The second dilution air flow 215 provides hydraulic support for the first dilution air flow 213, improving jet penetration in the process. The combined dilution air flow 217 reduces Figure 1 The temperature in the core primary combustion zone 114 of the combustor 112 is reduced, and the nitrogen oxides (NO x) emission levels comply with regulatory guidelines. Further, the air split ratio or distribution or portion of the first dilution air flow 213 and the second dilution air flow 215 in the combined dilution air flow 217 is adjusted to reduce the temperature in the core primary combustion zone 114. In addition, the portion of the second dilution air flow 215 of the combined dilution air is kept closer to the liner around the circumference of the liner and maintains a lower liner temperature behind the combined dilution structure.

[0039] The combined dilution air flow 217 facilitates rapid quenching and rapid mixing of the first dilution air flow 213 and the second dilution air flow 215 with the many combustion products in the core primary combustion zone 114 of the combustor 112. The increased mixing results in a uniform temperature distribution within the core primary combustion zone 114 of the combustor 112 and further results in a combustor liner temperature that conforms to the reference combustor liner temperature.

[0040] Figure 4 shows an embodiment of the present invention Figure 2 Schematic representation of a mirrored version of the dilution channel 211. Figure 4 , reference numeral 230 indicates a top perspective view showing a schematic representation of a dilution passage 231 through the combustion liner of the combustor. The dilution passage 231 connects a series of discrete holes 232 with an annular slot 234 in front (upstream) of the discrete holes 232. Within the connecting geometry of the dilution passage 231, a first dilution air flow 233 passing through the discrete holes 232 is combined with a second dilution air flow 235 passing through the annular slot 234 to form a combined dilution air flow 237. Further, the combined dilution air flow is injected into Figure 1 The primary combustion zone 114 of the burner 112 is formed to achieve a predetermined combustion state of the burner 112 .

[0041] refer to Figure 5 , reference numeral 240 indicates Figure 4 23. A first dilution air stream 233 passes through discrete holes 232, and a second dilution air stream 235 passes through annular slot 234. The second dilution air stream 235 provides a hydraulic shield for the first dilution air stream 233, improving jet penetration in the process.

[0042] refer to Figures 1 to 5 The core primary combustion zone 114 ( FIG. 1 ) of the combustor 112 ( FIG. 1 ) is improved by merging the first dilution air flow ( 213 , 233 ) and the second dilution air flow ( 215 , 235 ) into a combined dilution air flow ( 217 , 237 ) within the dilution passage ( 211 , 231 ). Figure 1). Specifically, by merging the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the low velocity of the combustion products generally associated with a dilution configuration having only discrete dilution holes is enhanced. Furthermore, by merging the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the high penetration of the dilution air generally associated with a dilution configuration having only an annular dilution passage is further enhanced.

[0043] Furthermore, the burner 112 is improved by merging the first dilution air flow (213, 233) and the second dilution air flow (215, 235) into a combined dilution air flow (217, 237) in the dilution passage (211, 231). Figure 1 )'s core primary combustion zone 114 ( Figure 1 ) in the core primary combustion zone 114. Specifically, by combining the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the core primary combustion zone 114 ( Figure 1 ) localization of high temperatures near the outer periphery of the annular dilution passage. Further, by merging the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the core primary combustion zone 114 ( Figure 1 ) localization of high temperature near the central part.

[0044] Furthermore, the burner 112 is improved by merging the first dilution air flow (213, 233) and the second dilution air flow (215, 235) into a combined dilution air flow (217, 237) in the dilution passage (211, 231). Figure 1 ) in the core primary combustion zone 114 ( Figure 1 ) within NO x Specifically, by combining the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the core primary combustion zone 114 ( Figure 1 ) near the outer periphery of the high NO x Further, by combining the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the dilution emissions generally associated with dilution configurations having only annular dilution passages are reduced. Figure 1 The high NO near the central portion of the core primary combustion zone 114 x emission.

[0045] Figure 6A burner 112 ( Figure 1 ) is a schematic bottom perspective view of a liner 310 of a combustor. Figure 7 6. A schematic perspective view of an outer liner 320 and an inner liner 330 is shown. The outer liner 320 and / or the inner liner 330 may include the liner 310 of FIG.

[0046] refer to Figure 6 and 7 The liner 310 has a liner body 309, a first surface 351 on a hot side 353 of the liner 310, and a second surface 355 on a cold side 357 of the liner 310. A dilution passage 311 can extend through the liner 310 from the cold side 357 to the hot side 353. The dilution passage 311 connects a plurality of discrete dilution holes 312 with an annular groove 314. That is, the dilution passage 311 is formed by a plurality of discrete dilution holes 312 that extend circumferentially around the liner 310 and are connected to an annular groove 314 that extends circumferentially around the liner 310. Although a single dilution passage 311 is shown, multiple dilution passages 311 can be repeated along the axial length of the liner 310.

[0047] Continue to refer Figure 6 and Figure 7 In the connected geometry of the dilution passage 311, the first dilution air flow 313 passing through the discrete dilution holes 312 is combined with the second dilution air flow 315 passing through the annular groove 314 to form a combined dilution air flow 317. The combined dilution air flow 317 is injected into the combustor 112 ( Figure 1 )'s core primary combustion zone 114 ( Figure 1 ) to reach the burner 112 ( Figure 1 The annular groove 314 may be positioned axially forward of the discrete dilution holes 312 .

[0048] The dilution passage 311 includes a protruding dilution insert 316 extending radially inward from each discrete dilution hole 312, such that a plurality of protruding dilution inserts 316 are present in each dilution passage 311. The plurality of dilution inserts 316 extending from the second surface 355 of the liner 310 vertically downward to the combustor 112 ( Figure 1 ) in the core primary combustion zone 114.

[0049] The plurality of discrete dilution holes 312 are coupled to the plurality of dilution inserts 316 to improve penetration of the second dilution air flow 315. The second dilution air flow 315 passes over the front side 331 of each of the plurality of dilution inserts 316 to protect the front side 331 of the dilution inserts 316 from the high temperatures prevalent in the core primary combustion zone 114. The plurality of dilution inserts 316 may be formed from metal or other structurally supportive materials and / or may be coated to reduce metal temperatures. The structural support from the plurality of dilution inserts 316 may increase penetration of the dilution jets from the discrete dilution holes 312. Thus, the improved penetration of the discrete dilution jets reduces temperatures in the core primary combustion zone 114. Portions of the second dilution air flow 315 penetrate and flow around the plurality of dilution inserts 316 to fill the wake region formed behind the jets of the first dilution air flow 313, thereby reducing the temperature behind the dilution jets. Portions of the second dilution air flow 315 are maintained circumferentially closer to the liner 310 , thereby reducing the temperature between adjacent ones of the plurality of dilution inserts 316 and also reducing the temperature of the liner 310 behind (e.g., downstream of) the incorporated dilution structure (e.g., the dilution passage 311 ).

[0050] refer to Figure 6 and Figure 7 , a first dilution air flow 313 enters the dilution passage 311 through each of the plurality of discrete dilution holes 312 and exits through a corresponding dilution insert 316. A second dilution air flow 315 enters, passes through, and exits through the annular slot 314. Within the connecting geometry of the dilution passage 311, the second dilution air flow 315 merges with the first dilution air flow 313 to form a combined dilution air flow 317. The combined dilution air flow 317 is injected into the core primary combustion zone 114 to achieve the predetermined combustion conditions of the combustor 112.

[0051] refer to Figure 6 , a gap 382 exists between the edges of two adjacent dilution inserts 316. That is, the outer edge 371 of a first dilution insert 316 may be separated from the outer edge 373 of an adjacent second dilution insert 316. Each dilution insert 316 may have an outer edge 371 opposite the outer edge 373, such that a gap 382 exists between adjacent dilution inserts 316. The gap 382 may be 0.3 to 10 times the outer diameter 375 of one of the dilution inserts 316.

[0052] Continue to refer Figure 6, a height 384 of the dilution insert 316 may be defined on the front side 331 of the dilution insert 316. The height 384 may be defined from the first surface 351 to the trailing surface 385 of the dilution insert 316. The height 384 may be the diameter 377 ( Figure 7 ) times. There may be circumferential variation in the height of the dilution inserts 316 such that there may be a height difference between one or more dilution inserts 316 of a single dilution channel 311. The height difference between the shortest dilution insert 316 and the longest dilution insert may vary from 0 to 0.9 times the average height of the dilution inserts 316. There may be a circumferential variation in the height of the dilution inserts 316 such that there may be a height difference between one or more dilution inserts 316 of a single dilution channel 311. The height difference between the shortest dilution insert 316 and the longest dilution insert may vary from 0 to 0.9 times the average height of the dilution inserts 316. Figure 1 ) can range from zero degrees to + / - sixty degrees.

[0053] Figure 8 A burner 112 ( Figure 1 ) is a schematic bottom perspective view of a liner 360 of a combustor. Figure 9 A schematic perspective view of an outer lining 365 and an inner lining 367 is shown. The outer lining 365 and / or the inner lining 367 may include the lining 360 of FIG. 8 . The lining 360 may be Figure 6 and Figure 7 The same as the lining 310. Instead of Figure 6 and 8 The constant height 384 of the dilution insert 316 from the front side to the back side, Figure 8 and Figure 9 The dilution insert 366 can be tapered. That is, the height can gradually decrease or angle from the front side 361 of the dilution insert 366 to the rear side 363 of the dilution insert 366. A bevel angle θ369 can be defined between an axis extending through the front side 361 and the trailing surface 368 of the dilution insert 366. The bevel angle θ369 can vary from zero to eighty degrees. The bevel angle θ369 can extend radially inward from the rear side 363 to the front side 361. The bevel angle θ369 can be such that the height of the dilution insert 366 at the rear side 363 can be zero or approximately zero, and can increase linearly or gradually toward the front side 361 of the dilution insert 366. The front side 361 can have the maximum height of the dilution insert 366.

[0054] Alternatively, such as Figure 10 and 11 As shown, the height of the dilution insert 366 may be zero or approximately zero at the front side 361 and may increase linearly or gradually toward the back side 363 of the dilution insert 366. Figure 10 and 11In the example of FIG. 36 , the chamfer angle θ 369 may extend radially inward from the front side 361 to the rear side 363 . The rear side 363 may have Figure 10 and 11 The maximum height of the dilution insert 366.

[0055] Figure 12 Dilution channels through the liner are shown (such as those for Figures 2 to 11 a schematic side view 350 of the dilution air flow of the dilution channel described above, and Figure 13 Dilution channels through the liner are shown (such as those for Figures 2 to 11 Schematic top view 340 of the dilution air flow of the dilution channel described. Figure 2 As a representative dilution channel, Figure 12 A second dilution air flow 215 is shown passing through the annular slot 214 flowing radially toward the core primary combustion zone 114 and acting as hydraulic support for the first dilution air flow 213 passing through the discrete dilution holes 212. This allows the first dilution air flow 213 to penetrate further into the core of the combustor, thereby reducing the temperature in the core primary combustion zone 114 of the combustor and, therefore, reducing NOx emissions.

[0056] refer to Figure 13 A portion 236 of the second dilution air flow 215 from the annular groove 214 flows around the first dilution air flow 213 passing through the discrete dilution holes 212, thereby reducing the wake behind the dilution jet formed by the first dilution air flow 213. This reduces the high temperature behind the dilution jet, thereby reducing NOx emissions.

[0057] Figure 14 A schematic side cross-sectional view of the dilution passage 411 of the combustion liner 442 is shown. The combustion liner 442 may be Figure 2 The combustion liner is the same or similar. Figure 14 , the side view 440 schematically shows the dilution channel 411, which can be connected to Figure 2 Dilution channel 411 extends through a combustion liner 442 of the combustor. Combustion liner 442 may be an inner or outer liner of the combustion chamber. Dilution channel 411 has a geometric structure formed by connecting a series of discrete dilution holes 444 and an annular dilution slot 454. The cross-section of each discrete dilution hole 444 may be semicircular. For example, in a top view of the discrete dilution holes 444, the geometric structure 450 of the discrete dilution holes 444 may be semicircular. The centerline of the circle formed by the two semicircles may be the centerline 446 of each discrete dilution hole 444. That is, the axis extending through the center of the diameter of the discrete dilution hole 444 is aligned with the centerline 446. The annular dilution slot 454 may have a front face 458 and a rear face 459.

[0058] Continue to refer Figure 14 , the centerline 446 of the discrete dilution hole 444 is parallel to the centerline 456 of the annular dilution slot 454. The front face 458 of the annular dilution slot 454 merges with and aligns with each diameter of the discrete dilution hole 444, which may have a semicircular geometry. Thus, the centerline 446 of the discrete dilution hole 444 is aligned with the front face 458 of the annular dilution slot 454 at an axial location of the front face 458 of the annular dilution slot 454, as shown in the top view. Furthermore, ten to ninety percent of the total flow area of ​​the dilution passage 411 is occupied by the discrete dilution holes 444, and the remainder of the total flow area is occupied by the annular dilution slot 454.

[0059] Figure 15 A schematic cross-sectional view of the dilution passage 431 of the combustion liner 462 is shown. The combustion liner 462 may be Figure 2 The combustion liner is the same or similar. Figure 15 , side view 460 schematically shows dilution channel 431, which can be connected to Figure 2 Dilution passage 431 extends through the combustion liner 462 of the combustor. Dilution passage 411 has a geometric structure formed by connecting a series of discrete dilution holes 464 and an annular dilution slot 474. The cross-section of each discrete dilution hole 464 can be semicircular. For example, in a top view of the discrete dilution holes 464, the geometric structure 470 of the discrete dilution holes 464 can be semicircular. The centerline of the circle formed by the two semicircles can be the centerline 466 of each discrete dilution hole 464. That is, the axis extending through the diametrical center of the discrete dilution hole 464 is aligned with the centerline 466. The annular dilution slot 474 can have a front face 478 and a rear face 479.

[0060] Continue to refer Figure 15 , the centerline 466 of the discrete dilution hole 464 is parallel to the centerline 476 of the annular dilution slot 474. Further, the centerline 466 of the discrete dilution hole 464 is aligned with the rear face 479 of the annular dilution slot 474 at an axial position of the rear face 479 of the annular dilution slot 474.

[0061] Figure 16 A schematic side cross-sectional view of the dilution passage 511 of the combustion liner 522 is shown. The combustion liner 522 may be Figure 2 The combustion liner is the same or similar. Figure 16 , the side view 520 schematically shows the dilution channel 511, which can be connected to Figure 2The dilution passage 511 is similar to the dilution passage 211 of the combustor. The dilution passage 511 extends through the combustion liner 522 of the combustor. The dilution passage 511 has a geometric structure formed by connecting a series of discrete dilution holes 524 and an annular dilution slot 534. The cross-section of each discrete dilution hole 524 can be semicircular. For example, in a top view of the discrete dilution holes 524, the geometric structure 530 of the discrete dilution holes 524 can be semicircular. The centerline of the circle formed by the two semicircles can be the centerline 526 of each discrete dilution hole 524. That is, the axis extending through the diametrical center of the discrete dilution hole 524 is aligned with the centerline 526. The annular dilution slot 534 can have a front face 538 and a rear face 539.

[0062] Continue to refer Figure 16 , the centerline 526 of the discrete dilution hole 524 is parallel to the centerline 536 of the annular dilution slot 534. Further, the centerline 526 of the discrete dilution hole 524 is rearward of the rear face 539 of the annular dilution slot 534 at an axial position of the rear face 539 of the annular dilution slot 534. The offset 532 measured between the centerline 526 of the discrete dilution hole 524 and the front face 538 of the annular dilution slot 534 is between zero and 0.3 times the diameter D of the discrete dilution hole 524.

[0063] Figure 17 A schematic side cross-sectional view of the dilution passage 531 of the combustion liner 542 is shown. The combustion liner 542 may be Figure 2 The combustion liner is the same or similar. Figure 17 , side view 540 schematically shows dilution channel 531, which can be connected to Figure 2 Dilution channel 531 extends through the combustion liner 542 of the combustor. Dilution channel 531 has a geometric structure formed by connecting a series of discrete dilution holes 544 and an annular dilution slot 554. The cross-section of each discrete dilution hole 544 can be semicircular. For example, in a top view of the discrete dilution holes 544, the geometric structure 550 of the discrete dilution holes 544 can be semicircular. The centerline of the circle formed by the two semicircles can be the centerline 546 of each discrete dilution hole 524. That is, the axis extending through the diametrical center of the discrete dilution hole 544 is aligned with the centerline 546. The annular dilution slot 554 can have a front face 558 and a rear face 559.

[0064] Continue to refer Figure 17, the centerline 546 of the discrete dilution hole 544 is parallel to the centerline 556 of the annular dilution slot 554. Further, the centerline 546 of the discrete dilution hole 544 is forward of the front face 558 of the annular dilution slot 534 at an axial position of the front face 558 of the annular dilution slot 554. The offset 552 measured between the centerline 546 of the discrete dilution hole 544 and the front face 558 of the annular dilution slot 534 is between zero and one times the diameter D of the discrete dilution hole 544.

[0065] Figure 18 A schematic side cross-sectional view 560 of a first dilution passage 551 through an outer liner 562 of a combustor and a second dilution passage 561 through an inner liner 582 of the combustor is shown, according to an embodiment of the present disclosure. The first dilution passage 551 has a geometry formed by joining a series of discrete dilution holes 564 and an annular dilution slot 574. The centerlines 566 of the discrete dilution holes 564 are parallel to the centerline 576 of the annular dilution slot 574 and are aligned with the front face 578 of the annular dilution slot 574 at an axial location at the front face 578 of the annular dilution slot 574. The second dilution passage 561 has a geometry formed by joining a series of discrete dilution holes 584 and an annular dilution slot 594. The centerlines 586 of the discrete dilution holes 584 are parallel to the centerline 596 of the annular dilution slot 594 and are aligned with the front face 598 of the annular dilution slot 594 at an axial location at the front face 598 of the annular dilution slot 594. The offset 580 measured between the centerline 566 of the discrete dilution hole 564 on the outer liner 562 and the centerline 586 of the discrete dilution hole 584 on the inner liner 582 is between zero and + / - six times the diameter of the discrete dilution hole 564 or 584 .

[0066] Figure 19 A schematic side cross-sectional view 620 of a dilution channel 611 of a combustion liner 622 is shown. The dilution channel 611 has a geometric structure formed by connecting a series of discrete dilution holes 624 and annular dilution slots 634. The centerline 626 of the discrete dilution holes 624 is parallel to the centerline 636 of the annular dilution slots 634. The centerline 626 of the discrete dilution holes 624 and / or the centerline 636 of the annular dilution slots 634, i.e., the flow direction of the discrete and annular flows can be tilted at an angle θ 632, which is defined relative to an axis 630 that is orthogonal to the combustion liner 622. The angle θ can be from negative sixty degrees (tilted forward) to positive sixty degrees (tilted rearward). The centerline 626 of the discrete dilution holes 624 can be orthogonal to the centerline 636 of the combustion liner 622 and the annular dilution slots 634 tilted at angle θ, or vice versa. Although shown as aligned with the centerline 636, the centerline 626 can be tilted relative to Figures 14 to 18 The description of is offset in any way from the previous description.

[0067] exist Figures 6 to 11 and Figures 14 to 19 In an example, the annular groove providing the annular second dilution flow is located before the discrete dilution holes providing the first dilution flow, for example, downstream or after the discrete dilution holes providing the first dilution flow. The second dilution flow provides hydraulic shielding for the discrete first dilution flow passing through the discrete dilution holes. In an example where the annular groove is located after the discrete dilution holes providing the first dilution flow, for example, upstream or before the discrete dilution holes providing the first dilution flow, the second dilution flow provides hydraulic support for the first dilution flow.

[0068] Figure 20 and 21 Each shows a burner such as burner 112 ( Figure 1 ) is a schematic top view of the dilution channels of an exemplary inner and outer liner of a combustor having a liner structure similar to that of FIG. A schematic outline of the dilution holes of the outer liner is shown as being positioned over the dilution holes of the inner liner. That is, when the liner is viewed from a top view, the outlines of the dilution holes of the inner and outer liners may appear as follows: Figure 20 or any one of 21.

[0069] For example, Figure 20 A top view 640 of an outer liner 642 and an inner liner 652 is shown. The outer liner 642 has a series of outer liner discrete dilution holes, including outer liner discrete dilution holes 644 and outer liner discrete dilution holes 646. While two outer liner discrete dilution holes are shown, more may be provided. The inner liner 652 has a series of inner liner discrete dilution holes, including inner liner discrete dilution holes 654 and inner liner discrete dilution holes 656. While two inner liner discrete dilution holes are shown, more may be provided.

[0070] The outer liner discrete dilution holes 644 and the outer liner discrete dilution holes 646 can be directly opposite or can be staggered at an angle to the inner liner discrete dilution holes 654 and the inner liner discrete dilution holes 656. In this manner, when the series of outer liner discrete dilution holes and inner liner discrete dilution holes are axially aligned, the inner liner discrete dilution holes 654 are circumferentially between the outer liner discrete dilution holes 644 and the outer liner discrete dilution holes 646. The inner liner discrete dilution holes 656 can be located between the outer liner discrete dilution holes 646 and an adjacent outer liner discrete dilution hole (not shown). Each inner liner discrete dilution hole can be midway between adjacent outer liner discrete dilution holes.

[0071] Although shown and described as being staggered, other offsets between the outer liner discrete dilution holes 644 and 646 and the inner liner discrete dilution holes 654 and 656 are contemplated. For example, Figure 21A top view 660 of an outer liner 662 and an inner liner 672 is shown. The outer liner 662 has a series of outer liner discrete dilution holes, including outer liner discrete dilution holes 664 and outer liner discrete dilution holes 666. While two outer liner discrete dilution holes are shown, more may be provided. The inner liner 672 has a series of inner liner discrete dilution holes, including inner liner discrete dilution holes 674 and inner liner discrete dilution holes 676. While two inner liner discrete dilution holes are shown, more may be provided. Figure 21 The top lining can be Figure 20 However, with Figure 20 Inner liner discrete dilution holes 674 and inner liner discrete dilution holes 676 can be positioned circumferentially closer to outer liner discrete dilution holes 664 and outer liner discrete dilution holes 666, respectively, than shown in FIG. That is, the distance between an inner liner discrete dilution hole, such as inner liner discrete dilution hole 674, and a first outer liner discrete dilution hole, such as outer liner discrete dilution hole 666, can be less than the distance between the same inner liner discrete dilution hole (e.g., inner liner discrete dilution hole 674) and an outer liner discrete dilution hole adjacent to the first outer liner discrete dilution hole (e.g., outer liner discrete dilution hole 666). However, this relationship can be reversed, and any distance between the dilution holes can be set.

[0072] In addition to or as an alternative to the two positions described above, other positioning of the inner liner discrete dilution holes relative to the outer liner discrete dilution holes is possible. Furthermore, the outer liner discrete holes can be aligned with the center of the cyclone or angled relative to the cyclone. The angle can depend on the number of discrete holes in each cyclone cup liner.

[0073] Figure 22 A schematic flow chart of a method 700 for flowing a dilution flow through a combustor liner according to an embodiment of the present disclosure is shown. The method 700 includes providing a combustor having (i) a combustor liner body with a hot side and a cold side and (ii) a core primary combustion zone of the combustor, as shown in step 712. The method 700 also includes extending a dilution passage having a connecting geometry through the combustor liner body, as shown in step 714. The method 700 further includes flowing a first dilution air from the cold side to the hot side of the combustor liner through the dilution passage, as shown in step 716. The method also includes flowing a second dilution air from the cold side to the hot side of the combustor liner through the dilution passage, as shown in step 718.

[0074] The combined geometry of the dilution passage is formed by joining a first geometric structure and a second geometric structure at predetermined relative positions, such that the first dilution air and the second dilution air are combined within the combined geometry of the dilution passage. The first geometric structure can be positioned forward or upstream, while the second geometric structure is positioned aft or downstream. The second geometric structure can be positioned forward or upstream, while the first geometric structure is positioned aft or downstream.

[0075] The first geometric structure includes at least one discrete hole, and the second geometric structure includes at least one discrete annular groove. The size of the discretely positioned discrete features (such as holes and annular grooves) can vary circumferentially or can have a specific pattern along the circumference. The discrete holes can have a semicircular cross-section, or a triangular cross-section, an elliptical cross-section, a semi-elliptical cross-section with a major axis in the transverse direction (e.g., a racetrack-shaped) cross-section, or a semi-elliptical cross-section with a major axis in the axial direction (e.g., a racetrack-shaped) cross-section, or any combination thereof.

[0076] The dilution channels' interconnected geometry can repeat in a predetermined pattern, such as in a generally circumferential linear array or in a staggered array relative to the combustor. The dilution channels can be oriented at varying angles relative to the combustor in a predetermined orientation. The dilution channels can be arranged orthogonal to the axis of the liner, or they can be inclined at an angle to the axis of the swirler.

[0077] Method 700 further includes providing a third geometric structure and coupling the third geometric structure to the first geometric structure such that the first dilution air flows through the third geometric structure. The third geometric structure is a protruding dilution insert extending into the hot side of the liner. The protruding dilution insert can be a full-length insert, a corner-cut (or beveled) dilution insert, or a fence. The length of the protruding dilution insert can be longer on one side than on the other side, such that the weighted area decreases from one side to the other. The precise dimensions of the protruding dilution insert can be adjusted for efficient performance.

[0078] The method 700 further includes combining the first dilution air flow and the second dilution air flow to provide a combined dilution air flow to increase mixing with the plurality of combustion products in the primary combustion zone of the combustor, as shown in step 722. The method 700 also includes injecting the combined dilution air flow into the combustor to achieve a predetermined combustion state of the combustor, as shown in step 724.

[0079] The burner's predetermined combustion state includes compliant NO xEmission levels. The predetermined combustion state of the burner further includes reducing the temperature in the core primary combustion zone of the burner. The predetermined combustion state of the burner further includes reducing the temperature in the core primary combustion zone of the burner. The predetermined combustion state of the burner further includes reducing the temperature in the wake region of the dilution jet or dilution insert. The predetermined combustion state of the burner further includes reducing the temperature between the dilution jet or dilution insert. The predetermined combustion state of the burner also includes a uniform temperature distribution within the primary combustion zone of the burner and the secondary combustion zone of the burner. The predetermined combustion state of the burner includes a burner outlet temperature profile that conforms to a reference temperature profile. The predetermined combustion state of the burner also includes rapid quenching and rapid and increased mixing of the first dilution air flow and the second dilution air flow with the combustion products in the primary combustion zone of the burner. Further, the predetermined combustion state of the burner includes a balance of predetermined air split ratios (relative distribution or shares) of the first dilution air flow and the second dilution air flow.

[0080] The disclosed liner for a gas turbine engine combustor provides a dilution passage having a joining geometry that combines a first dilution air flow and a second dilution air flow into a combined dilution air flow.

[0081] When the second dilution air flow is downstream of the first dilution air flow, the second dilution air flow can provide hydraulic support for the first dilution air flow. When the second dilution air flow is upstream of the first dilution air flow, the second dilution air flow can provide hydraulic shielding for the first dilution air flow. In both cases, the hydraulic support and / or hydraulic shielding can penetrate between the scattered airflows of the first dilution air flow and enhance the penetration of the first dilution air flow into the core primary combustion zone of the combustor.

[0082] The combined dilution air flow increases the rapid quenching and mixing of the dilution air flow with the multiple combustion products in the primary combustion zone of the combustor, resulting in a uniform temperature distribution within the primary combustion zone of the combustor and a combustor outlet temperature profile that meets the reference temperature profile. The combined dilution air flow reduces nitrogen oxides (NO x ) emission levels.

[0083] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0084] A liner for a combustor in a gas turbine engine comprises: a liner body having a cold side and a hot side; and a dilution passage having a connecting geometry extending through the liner body, the dilution passage being configured to (a) combine a first dilution air flow flowing from the cold side to the hot side through the dilution passage and a second dilution air flow flowing from the cold side to the hot side through the dilution passage into a combined dilution air flow, and (b) inject the combined dilution air flow into a core primary combustion zone of the combustor to achieve a predetermined combustion state of the combustor. The connecting geometry comprises: a plurality of discrete dilution holes through which the first dilution air flow flows; annular slots through which the second dilution air flow flows; and a plurality of dilution inserts through which the first dilution air flow flows, each of the plurality of dilution inserts being connected to a corresponding discrete dilution hole of the plurality of dilution holes, the plurality of dilution inserts being configured to assist the first dilution air flow and the second dilution air flow in penetrating into the core primary combustion zone of the combustor.

[0085] A liner according to the preceding clause, wherein the second dilution air flow (i) provides hydraulic shielding for the first dilution air flow and enhances penetration of the first dilution air flow into the core primary combustion zone of the combustor, (ii) fills a wake region formed behind a plurality of discrete air streams of the first dilution air flow, and (iii) penetrates between the plurality of discrete air streams of the first dilution air flow and prevents the generation of high temperature zones near the liner and between the plurality of discrete air streams.

[0086] The liner of any of the preceding clauses, wherein the first dilution air flow generates turbulence in the core primary combustion zone of the combustor.

[0087] A liner according to any of the preceding clauses, wherein the predetermined combustion state of the combustor includes (i) a reduced temperature in the core primary combustion zone of the combustor, (ii) compliant NOx emission levels, (iii) a uniform temperature distribution within the core primary combustion zone of the combustor, (iv) a combustor outlet temperature profile that conforms to a reference temperature profile, (v) increased mixing of the first dilution air flow and the second dilution air flow with multiple combustion products in the core primary combustion zone of the combustor, (vi) rapid quenching and rapid mixing of the first dilution air flow and the second dilution air flow with the combustion products in the core primary combustion zone of the combustor, (vii) a predetermined air split ratio of the first dilution air flow and the second dilution air flow, or (viii) any combination thereof.

[0088] The liner of any of the preceding clauses, wherein each of the plurality of discrete dilution holes has a semicircular cross-section, an elliptical cross-section, or a racetrack-shaped cross-section.

[0089] The liner of any of the preceding clauses, wherein the first dilution air flow is ten to ninety percent of the total flow through the dilution passage.

[0090] A liner according to any of the preceding clauses, wherein the first dilution air flow is located axially rearward of the second dilution air flow.

[0091] A liner according to any of the preceding clauses, wherein the first dilution air flow is located axially forward of the second dilution air flow.

[0092] A liner according to any of the preceding clauses, wherein the plurality of discrete dilution holes and the plurality of dilution inserts extend circumferentially in series around the liner body and are coupled to the annular groove.

[0093] A liner according to any of the preceding clauses, wherein each dilution insert of the plurality of dilution inserts comprises a semi-circular body.

[0094] The liner of any of the preceding clauses, wherein each dilution insert of the plurality of dilution inserts extends radially inwardly towards a centerline axis of the combustor.

[0095] A liner according to any of the preceding clauses, wherein a gap exists between adjacent ones of the plurality of dilution inserts, the gap ranging from about 0.3 times to about 10 times the outer diameter of a dilution insert of the plurality of dilution inserts.

[0096] A liner according to any of the preceding clauses, wherein the plurality of dilution inserts have a trailing surface that is angled relative to an axis normal to a centreline axis of the combustor, the angle being between zero and sixty degrees.

[0097] A liner according to any of the preceding clauses, wherein each dilution insert of the plurality of dilution inserts has a front side and a rear side, and the front side of the dilution insert defines a height between an inner surface of the liner body and a rear surface of the dilution insert.

[0098] The liner of any of the preceding clauses, wherein each discrete dilution hole of the plurality of discrete dilution holes has a diameter, and the height of the dilution insert is 0.1 to 10 times the diameter.

[0099] A liner according to any of the preceding clauses, wherein the height is constant from the front side to the back side of the dilution insert.

[0100] A liner according to any of the preceding clauses, wherein the height tapers from the front side to the rear side of the dilution insert.

[0101] The liner according to any of the preceding clauses, wherein the height of the rear side is shorter than the height of the front side, the heights tapering linearly from the rear side to the front side.

[0102] The liner according to any of the preceding clauses, wherein the height of the front side is shorter than the height of the rear side, the heights tapering linearly from the front side to the rear side.

[0103] A liner according to any of the preceding clauses, wherein the dilution insert has a chamfer angle such that the height tapers along the trailing surface of the dilution insert, the chamfer angle being between zero and eighty degrees.

[0104] Although the foregoing description is directed to preferred embodiments, it is to be noted that other variations and modifications are apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, features described with respect to one embodiment may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A liner for a combustor in a gas turbine engine, characterized in that The lining comprises: a liner body having a first surface on a cold side and a second surface on a hot side; and a dilution passage having a junction geometry extending through the liner body, the dilution passage being configured to (a) combine a first dilution air flow flowing from the cold side to the hot side through the dilution passage and a second dilution air flow flowing from the cold side to the hot side through the dilution passage into a combined dilution air flow, and (b) inject the combined dilution air flow into a core primary combustion zone of the combustor to achieve a predetermined combustion state of the combustor, the junction geometry having: (i) a plurality of discrete dilution holes extending from the first surface to the second surface, the first dilution air flow flowing through the plurality of discrete dilution holes; (ii) an annular groove extending from the first surface to the second surface, the second dilution air flow flowing through the annular groove; and (iii) a plurality of dilution inserts extending radially inward from the second surface and adjacent the annular groove, the first dilution air flow flowing through the plurality of dilution inserts, each of the plurality of dilution inserts being coupled to a corresponding discrete dilution hole of the plurality of discrete dilution holes, the plurality of dilution inserts being configured to assist penetration of the first dilution air flow and the second dilution air flow into the core primary combustion zone of the combustor.

2. The lining according to claim 1, characterized in that wherein the annular groove is located upstream of the plurality of discrete dilution holes such that the second dilution air flow is configured to (i) provide hydraulic shielding for the first dilution air flow and enhance penetration of the first dilution air flow into the core primary combustion zone of the combustor, (ii) fill a wake region formed behind a plurality of discrete air streams of the first dilution air flow, and (iii) penetrate between the plurality of discrete air streams of the first dilution air flow and prevent the formation of a high temperature zone adjacent to the liner and between the plurality of discrete air streams.

3. The lining according to claim 1, characterized in that The first dilution air flow generates turbulence in the core primary combustion zone of the combustor.

4. The lining according to claim 1, characterized in that wherein the predetermined combustion conditions of the burner include (i) a reduced temperature in the core primary combustion zone of the burner, (ii) a compliant NO x emissions levels, (iii) a uniform temperature distribution within the core primary combustion zone of the combustor, (iv) a combustor outlet temperature profile that conforms to a reference temperature profile, (v) increased mixing of the first dilution air flow and the second dilution air flow with a plurality of combustion products in the core primary combustion zone of the combustor, (vi) rapid quenching and rapid mixing of the first dilution air flow and the second dilution air flow with the combustion products in the core primary combustion zone of the combustor, (vii) a predetermined air split ratio of the first dilution air flow and the second dilution air flow, or (viii) any combination thereof.

5. The lining according to claim 1, wherein Each of the plurality of discrete dilution holes has a semicircular cross section, an elliptical cross section, or a racetrack-shaped cross section.

6. The lining according to claim 1, characterized in that The first dilution air flow is ten percent to ninety percent of the total flow through the dilution passage.

7. The lining according to claim 1, wherein The first dilution air flow is located axially rearward of the second dilution air flow.

8. The lining according to claim 1, wherein The first dilution air flow is located axially ahead of the second dilution air flow.

9. The lining according to claim 1, characterized in that wherein the plurality of discrete dilution holes and the plurality of dilution inserts extend circumferentially in series around the liner body and are coupled to the annular groove.

10. The liner according to claim 1, wherein Wherein each dilution insert of the plurality of dilution inserts comprises a semi-circular body.

11. The liner according to claim 1, wherein Wherein the plurality of dilution inserts extend radially inwardly toward a centerline axis of the combustor.

12. The liner according to claim 1, wherein Wherein a gap exists between adjacent ones of the plurality of dilution inserts, the gap ranges from 0.3 times to 10 times an outer diameter of a dilution insert of the plurality of dilution inserts.

13. The liner according to claim 1, wherein Each of the plurality of dilution inserts has a trailing surface that is angled between zero and sixty degrees relative to an axis orthogonal to a centerline axis of the combustor.

14. The liner according to claim 13, characterized in that wherein each dilution insert of the plurality of dilution inserts has a front side and a rear side, and wherein the front side of the dilution insert defines a height between an inner surface of the liner body and the rear surface of the dilution insert.

15. The liner according to claim 14, characterized in that The dilution insert has a chamfer angle such that the height gradually decreases along the trailing surface of the dilution insert, the chamfer angle being between zero and eighty degrees.

16. The liner according to claim 14, wherein Wherein each discrete dilution hole of the plurality of discrete dilution holes has a diameter, and the height of the dilution insert is 0.1 to 10 times the diameter.

17. The liner according to claim 14, wherein Wherein the height is constant from the front side to the back side of the dilution insert.

18. The liner according to claim 14, wherein wherein the height gradually decreases from the front side to the back side of the dilution insert.

19. The liner according to claim 18, characterized in that The height of the rear side is shorter than the height of the front side, and the height gradually decreases linearly from the rear side to the front side.

20. The liner according to claim 18, wherein The height of the front side is shorter than the height of the rear side, and the height gradually decreases linearly from the front side to the rear side.

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