Combustion Lining

Abstract

A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution array having a plurality of dilution channels, each of the plurality of dilution channels having a connecting geometry that repeats in a predetermined pattern and extends circumferentially around the liner body. The dilution channels (i) merge a first dilution air flow flowing from the cold side to the hot side through the dilution channels and a second dilution air flow flowing from the cold side to the hot side through the dilution channels into a combined dilution air flow, and (ii) inject the combined dilution air flow into the core primary combustion zone of the combustor to achieve a predetermined combustion state of the combustor. The dilution array repeats along the axial length of the liner body.

Description

Technical Field

[0001] This disclosure relates to combustion liners. Specifically, this disclosure relates to combustion liners for combustors in gas turbine engines, the liners having dilution openings and channels surrounding the dilution openings. Background Technology

[0002] A gas turbine engine includes a combustion section with a combustor that generates combustion gases, which are then exhausted into the turbine section of the engine. The combustion section includes a combustion liner. The combustion liner includes dilution openings within the liner. These dilution openings supply a dilution airflow to the combustor. The dilution airflow mixes with primary zone products within the combustor. Attached Figure Description

[0003] Features and advantages will become apparent from the following description of various exemplary embodiments as shown in the accompanying drawings, wherein similar reference numerals generally indicate the same, functionally similar and / or structurally similar elements.

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

[0005] Figure 2 A schematic side perspective view of a dilution channel for a combustion liner of a burner, according to an embodiment of the present disclosure, is shown.

[0006] Figure 3 The following illustrations show embodiments according to the present disclosure. Figure 2 A schematic side view of the dilution channel in the lining.

[0007] Figure 4 The following illustrations show embodiments according to the present disclosure. Figure 2 A schematic side perspective view of a mirrored version of the burning lining.

[0008] Figure 5 The following illustrations show embodiments according to the present disclosure. Figure 4 A schematic side perspective view of the dilution channel of the lining.

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

[0010] Figure 7A The following illustrations show embodiments according to the present disclosure. Figure 6 A schematic partial bottom perspective view of the dilution channel in the lining.

[0011] Figure 7B The following illustrations show embodiments according to the present disclosure. Figure 6 A schematic partial bottom perspective view of the dilution channel in the lining.

[0012] Figure 8 A schematic partial top perspective view of a dilution channel for a burner liner according to an embodiment of the present disclosure is shown.

[0013] Figure 9 A schematic side cross-sectional view of a dilution channel in a combustion liner according to an embodiment of the present disclosure is shown.

[0014] Figure 10 A schematic side cross-sectional view of a dilution channel in a combustion liner according to an embodiment of the present disclosure is shown.

[0015] Figure 11 A schematic side cross-sectional view of a dilution channel in a combustion liner according to an embodiment of the present disclosure is shown.

[0016] Figure 12 A schematic side cross-sectional view of a dilution channel in a combustion liner according to an embodiment of the present disclosure is shown.

[0017] Figure 13 A schematic side cross-sectional view of a dilution passage through the outer and inner linings of a burner, according to an embodiment of the present disclosure, is shown.

[0018] Figure 14 The following illustrations show embodiments according to the present disclosure. Figure 2 A schematic side cross-sectional view of the dilution channel of the lining.

[0019] Figure 15 A schematic top view of the dilution channels of an exemplary inner and outer liner of a burner according to an embodiment of the present disclosure is shown.

[0020] Figure 16 A schematic top view of the dilution channels of an exemplary inner and outer liner of a burner according to an embodiment of the present disclosure is shown.

[0021] Figure 17 A schematic flowchart of a method for passing a dilution stream through a burner liner according to an embodiment of the present disclosure is shown. Detailed Implementation

[0022] The features, advantages, and embodiments of this disclosure are set forth or become apparent from the following detailed description, drawings, and claims. Furthermore, it should be understood that the following detailed description is exemplary and intended to provide further explanation, without limiting the scope of the claimed disclosure.

[0023] Various embodiments are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from the spirit and scope of this disclosure.

[0024] Reference will now be made in detail to current embodiments of the disclosed subject matter, one or more examples of which are illustrated in the accompanying drawings. Detailed description uses numerals and letter designations to refer to features in the drawings. Similar or analogous designations in the drawings and description have been used to refer to similar or analogous 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 individual components.

[0025] The terms "upstream" or "front" and "downstream" or "rear" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows. Similarly, "front" refers to the front end or direction of an engine, and "rear" refers to the rear end or direction of an engine.

[0026] Gas turbine engines, such as those used to power aircraft or industrial applications, comprise a compressor, combustor, and turbine arranged around a central engine axis, with the compressor positioned axially upstream of the combustor and the turbine axially downstream. The compressor pressurizes the air supply, the combustor burns hydrocarbon fuels in the presence of 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 the gas turbine engine cycle efficiency. Furthermore, any variation in the combustor's air pressure ratio and / or outlet temperature affects the turbine's operability and lifespan. Combustor outlet temperatures above 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 their mechanical strength (e.g., creep and fatigue) as well as their oxidation and corrosion resistance. Maintaining the combustor temperature within acceptable ranges can significantly improve the lifespan of the turbine blades and nozzles. Structurally, the burner liner is located inside the burner to withstand extreme thermal loads, and the extensive burner liner cooling arrangement may reduce thermal stress in several mechanical parts and components of the gas turbine engine.

[0027] In the combustor of a gas turbine engine, air generally flows through outer and inner channels surrounding the combustor liner. Air flows from the upstream end to the downstream end of the combustor liner. Some of the air flowing through the outer and inner channels is diverted through multiple dilution orifices located 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 within the core primary combustion zone before they enter the turbine section. However, the combustion products from the core primary combustion zone must be quenched quickly and effectively to minimize the high-temperature region, thereby reducing NO from the combustion system. x emission.

[0028] The use of discrete dilution orifices (also known as "discrete orifices") and discrete dilution channels (also known as "discrete channels") through the liner is known, and these orifices and channels essentially form flow channels through the liner. In discrete dilution, high turbulence is introduced into the core primary combustion zone of the burner from multiple scattered streams. As a result, good mixing of combustion products is achieved after dilution. However, due to low jet penetration, some high-temperature regions still exist within the burner core. Furthermore, the wake regions formed behind and between 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 generated turbulence is low, resulting in low mixing of the dilution air with the primary zone products after the dilution stream enters, causing potentially higher temperatures in the core of the diluted combustion chamber, resulting in a higher outlet temperature profile / pattern, and potentially negatively impacting combustion efficiency.

[0029] This disclosure provides a method for synergistically combining the advantages of discrete dilution and annular dilution. The burner 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 airflow and a second dilution airflow pass from the cold side of the combustion liner through the dilution channel to the hot side of the burner liner. The dilution channel merges the first and second dilution airflows within the concatenated geometry into a combined dilution airflow, and injects the combined dilution airflow into the core primary combustion zone of the burner to achieve a predetermined combustion state.

[0030] Figure 1A 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, which are discharged into a 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 a compressor section (not shown) of the engine and supplies compressed air flow to the combustor 112. The diffuser 122 supplies compressed air flow to the shroud 120 of a vortex generator 124. Airflow passes through an outer passage 126 and an inner passage 128.

[0031] Figure 2 and Figure 3 This is a schematic representation of a burner liner according to an embodiment of the present disclosure. Reference Figure 2 Side perspective view 210 schematically shows a dilution channel 211 extending through the combustion liner for the burner. (Reference) Figure 3 Reference number 220 indicates Figure 2 A bottom view of the dilution channel 211. The dilution channel 211 has a geometry that connects the exemplary first geometry and the exemplary second geometry (or physically joins two adjacent entities end-to-end, fusing them into a single entity). Reference Figure 2 and Figure 3 The first geometry, which is embodied in multiple discrete holes 212, and the second geometry, which is embodied in an annular groove 214 extending through the burner liner, are connected to form a dilution channel 211.

[0032] The discrete hole 212 and the annular groove 214 are connected at predetermined relative positions. (Reference) Figure 2 and Figure 3 Discrete orifice 212 is positioned forward or upstream, and an annular groove 214 is positioned backward or downstream. Discrete orifice 212 has a semi-circular cross-section. Although not shown, a bridge structure allows discrete orifice 212 to connect to annular groove 214 to allow control of the dilution gap between annular groove 214 and discrete orifice 212. The bridge structure can be attached to the rear of the liner forming annular groove 214 (e.g., rear 459 of FIG. 114). In some examples, the bridge structure can be welded to annular groove 214. The bridge structure can support and control the dilution gap.

[0033] Within the connecting geometry of the dilution channel 211, the first dilution airflow 213 passing through the discrete orifice 212 and the second dilution airflow 215 passing through the annular groove 214 merge into a combined dilution airflow 217. Further, the combined dilution airflow 217 is injected into... Figure 1In the core primary combustion zone 114 of the burner 112, the predetermined combustion state of the burner 112 is achieved.

[0034] The combined dilution airflow 217 improves several desired combustion states of the burner. The second dilution airflow 215 provides hydraulic support for the first dilution airflow 213, improving jet penetration during processing. The combined dilution airflow 217 reduces... Figure 1 The temperature in the core primary combustion zone 114 of the burner 112 is increased, and nitrogen oxides (NOx) are reduced. x The emission levels comply with regulatory guidelines. Furthermore, the air split ratio, distribution, or share of the first dilution airflow 213 and the second dilution airflow 215 in the combined dilution airflow 217 is adjusted to reduce the temperature in the core primary combustion zone 114. Additionally, a portion of the second dilution airflow 215 of the combined dilution airflow remains closer to the liner around the liner's circumference and maintains a lower liner temperature behind the combined dilution structure.

[0035] The combined dilution airflow 217 facilitates the rapid cooling and mixing of the first dilution airflow 213 and the second dilution airflow 215 with the numerous combustion products in the core primary combustion zone 114 of the burner 112. The increased mixing results in a uniform temperature distribution within the core primary combustion zone 114 of the burner 112, and further results in a burner lining temperature that conforms to a reference burner lining temperature.

[0036] Figure 4 An embodiment of the present invention is shown. Figure 2 A schematic representation of a mirrored version of dilution channel 211. (See reference) Figure 4 Reference numeral 230 indicates a top perspective view showing a schematic representation of a dilution channel 231 through the combustion liner of the burner. The dilution channel 231 connects a series of discrete orifices 232 to an annular groove 234 upstream of the discrete orifices 232. Within the connecting geometry of the dilution channel 231, a first dilution airflow 233 passing through the discrete orifices 232 merges with a second dilution airflow 235 passing through the annular groove 234 to form a combined dilution airflow 237. Further, the combined dilution airflow is injected into… Figure 1 In the core primary combustion zone 114 of the burner 112, the predetermined combustion state of the burner 112 is achieved.

[0037] refer to Figure 5 Reference number 240 indicates Figure 4 A side perspective view of the dilution channel 231. A first dilution airflow 233 passes through a discrete orifice 232, and a second dilution airflow 235 passes through an annular groove 234. The second dilution airflow 235 provides hydraulic shielding for the first dilution airflow 233, improving jet penetration during processing.

[0038] refer to Figures 1 to 5 The burner 112 is improved by merging the first dilution air flow (213, 233) and the second dilution air flow (215, 235) into a merged dilution air flow (217, 237) within the dilution channels (211, 231). Figure 1 ) core primary combustion zone 114 ( Figure 1 The velocity distribution of combustion products within the dilution channel. Specifically, by merging the first and second dilution air flows into a merged dilution air flow within the dilution channel, the low velocity of combustion products, which is generally associated with a dilution configuration having only discrete dilution orifices, is enhanced. Furthermore, by merging the first and second dilution air flows into a merged dilution air flow within the dilution channel, the high penetration of the dilution air, which is generally associated with a dilution configuration having only annular dilution channels, is further enhanced.

[0039] 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 merged dilution air flow (217, 237) within the dilution channels (211, 231). Figure 1 ) core primary combustion zone 114 ( Figure 1 The temperature distribution of combustion products within the dilution channel. Specifically, by merging the first and second dilution air flows into a merged dilution air flow within the dilution channel, the core primary combustion zone 114, which is generally associated with a dilution configuration having only discrete dilution orifices, is reduced. Figure 1 The high temperature localization near the outer periphery of the ) is further reduced by merging the first and second dilution air flows into a merged dilution air flow within the dilution channel, thus reducing the core primary combustion zone 114 (which is generally associated with a dilution configuration having only an annular dilution channel). Figure 1 High temperatures are localized near the center of the region.

[0040] 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 merged dilution air flow (217, 237) within the dilution channels (211, 231). Figure 1 The core primary combustion zone 114 in ) Figure 1 ) within NO x Emission status. Specifically, by merging the first and second dilution air flows into a merged dilution air flow within the dilution channel, the core primary combustion zone 114, which is generally associated with a dilution configuration having only discrete dilution orifices, is reduced. Figure 1 High NO levels near the outer perimeter xEmissions. Furthermore, by merging the first and second dilution air flows into a combined dilution air flow within the dilution channel, the emissions are reduced, which is generally associated with dilution configurations having only annular dilution channels. Figure 1 The high NO content near the center of the core primary combustion zone 114 x emission.

[0041] Figure 6 A schematic partial top perspective view of the liner 310 is shown. The liner 310 may include a dilution array 318. The dilution array 318 includes a plurality of dilution channels 311. The dilution array 318 connects the plurality of dilution channels 311 together. Figure 6 As shown, multiple dilution channels 311 can be arranged in a linear array. Although a single linear arrangement of multiple dilution channels 311 is shown, the linear array can be repeated along the axial length of the liner 310.

[0042] Each dilution channel 311 includes a discrete forming hole 312, also referred to as a discrete hole 312, and a corresponding groove, embodied as a discrete groove 314. The discrete groove 314 has a groove width 372. Each discrete groove 314 may be an elongated groove adjacent to and abutting the corresponding discrete forming hole 312. The discrete groove 314 extends on either side of the periphery or boundary of the discrete hole 312, and the extension length on either side (referred to as a groove extension 374) is in the range of 0.5 to 15 times the groove width 372. The groove extension 374 may include a first groove extension 374 extending circumferentially from a first side of the discrete hole 312 in a first direction, and a second groove extension 374 extending circumferentially from a second side of the discrete hole 312 in a second direction. The first direction may be opposite to the second direction. In this way, the first groove extension 374 and the second groove extension 374 may extend circumferentially away from each other and away from the discrete hole 312.

[0043] The first dilution airflow 313 passing through the discrete orifice 312 merges with the second dilution airflow 315 passing through the discrete slot 314 to form a combined dilution airflow 317, which includes both the first dilution airflow 313 and the second dilution airflow 315. The combined dilution airflow 317 is injected into the burner 112. Figure 1 ) core primary combustion zone 114 ( Figure 1 In ), to achieve burner 112 ( Figure 1 The predetermined combustion state.

[0044] Continue to refer to Figure 6The discrete groove 314 can be a discrete groove positioned discretely forward. The discrete forming hole 312 can be a forming hole or a flat hole positioned discretely backward. Although the discrete forming hole 312 is shown and described as being located behind the discrete groove 314 (e.g., a discrete forming hole 312 downstream of the discrete groove 314), the opposite case is also contemplated, such that the discrete forming hole 312 is located in front of the discrete groove 314 on the liner 310 (e.g., a discrete forming hole 312 upstream of the discrete groove 314).

[0045] The relative positions of the discrete forming holes 312 and the discrete grooves 314 can together improve the burner 112. Figure 1 The core primary combustion zone 114 within ) Figure 1 The turbulence level in the 114 is improved. For example, a discrete slot 314, positioned in front of (e.g., forward or upstream of) the discrete orifice 312 (also called the discrete dilution orifice 312) and extending beyond the discrete orifice 312 (e.g., slot extension 374), provides hydraulic shielding and improves the penetration of the dilution airflow into the core primary combustion zone 114. Figure 1 In the process, a portion of the second dilution air stream 315 from the discrete slot 314 is drawn in behind the off-scatter stream, which is a portion of the first dilution air stream 313 from the discrete orifice 312. This reduces the temperature behind the jet, thereby reducing NO. x Discharge. A portion of the second dilution airflow 315 from the discrete slot 314 extending beyond the discrete orifice 312 can reduce the temperature between adjacent out-of-scatter flows from the first dilution airflow 313 from the discrete orifice 312 (e.g., discrete orifices 312 positioned adjacent to each other on the liner 310 without intervening discrete orifices 312).

[0046] Figure 7A Showing Figure 6 A partial bottom perspective view of the dilution array 318 of the liner 310. The liner 310 has a liner body 309 having a hot side 353 and a cold side 357. Each of the plurality of dilution channels 311 includes a protruding dilution insert 316. The dilution insert 316 is a full-length dilution insert having the same weighted area extending from the front side of the dilution insert 316 to the rear side of the dilution insert 316. That is, the dilution insert 316 has a uniform height 376 from the front side to the rear side (e.g., the height of the dilution insert 316 on the hot side of the liner 310). In some examples, the height 376 of the dilution insert 316 may be tapered, for example, it may be zero at the front side, and the length may gradually increase to the full length at the rear side of the dilution insert. In some examples, the height 376 of the dilution insert 316 may be in discrete holes 312 ( Figure 6 The diameter D of ) Figure 6 Within 0.1 to 10 times of ) . For example Figure 7AAs shown, the first dilution airflow 313 and the second dilution airflow 315 can be combined to form a combined dilution airflow 317.

[0047] exist Figure 7B In the example, the dilution insert 316 extending from the liner body 309 may include a beveled portion 329 on the hot side of the dilution insert 316, such that the height varies from the front to the rear. The beveled portion 329 may be made at an angle θ378. The angle θ378 is defined as the angle between the discrete dilution center axis 346 and the angular cutting plane 348. The angular cutting plane 348 may be aligned with the beveled portion 329. The value of the angle θ378 may vary from zero degrees to eighty degrees.

[0048] exist Figure 8 In the example, dilution array 318 may include a plurality of dilution channels 311 arranged in an interlaced array. In this way, dilution array 318 may include a first row 319 and a second row 320. The first row 319 may be axially offset from the second row 320. For example, the first centerline 352 of the dilution channels 311 in the first row 319 and the second centerline 354 of the dilution channels 311 in the second row 320 may be axially offset 382. The length of the axial offset 382 may be in the range of zero to (+ / -) five times the diameter of the discrete holes 312. The merged dilution holes on the outer and inner liners are circumferentially opposite or interlaced with each other. Although a single dilution array 318 with a first row 319 and a second row 320 is shown, the array may be repeated along the axial length of the liner 310, such that multiple first rows 319 and second rows 320 are presented.

[0049] Figures 6 to 8 Any example can be related to Figures 6 to 8 Any or all of the example combinations.

[0050] Figure 9 A schematic side cross-sectional view of the dilution channel 411 of the combustion liner 442 is shown. The combustion liner 442 can be coupled with... Figure 2 The combustion lining is the same as or similar to that of the other materials. (Reference) Figure 9 Side view 440 schematically represents dilution channel 411, which can be connected to... Figure 2The dilution channel 411 is similar. The dilution channel 411 extends through the combustion liner 442 of the burner. The combustion liner 442 can be an inner or outer liner of the combustion chamber. The dilution channel 411 has a geometry formed by connecting a series of discrete dilution holes 444 and discrete dilution channels 454. The cross-section of each discrete dilution hole 444 can be semi-circular. For example, in a top view of the discrete dilution holes 444, the geometry 450 of the discrete dilution holes 444 can be semi-circular. The centerline of the circle formed by the two semicircles can 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 discrete dilution channels 454 can have a front 458 and a rear 459.

[0051] Continue to refer to Figure 9 The centerline 446 of the discrete dilution orifice 444 is parallel to the centerline 456 of the discrete dilution channel 454. The front end 458 of the discrete dilution channel 454 merges with and aligns with each diameter of the discrete dilution orifice 444, which may have a semi-circular geometry. Therefore, the centerline 446 of the discrete dilution orifice 444 is aligned with the front end 458 of the discrete dilution channel 454 at an axial position, as shown in the top view. Further, 10% to 90% of the total flow area of ​​the dilution channel 411 is occupied by the discrete dilution orifice 444, and the remaining portion of the total flow area is occupied by the discrete dilution channel 454.

[0052] Figure 10 A schematic side cross-sectional view of the dilution channel 431 of the combustion liner 462 is shown. The combustion liner 462 can be used with... Figure 2 The combustion lining is the same as or similar to that of the other materials. (Reference) Figure 10 Side view 460 schematically represents dilution channel 431, which can be connected to... Figure 2 The dilution channel 211 is similar. The dilution channel 431 extends through the combustion liner 462 of the burner. The dilution channel 411 has a geometry formed by connecting a series of discrete dilution holes 464 and discrete dilution channels 474. The cross-section of each discrete dilution hole 464 can be semi-circular. For example, in a top view of the discrete dilution hole 464, the geometry 470 of the discrete dilution hole 464 can be semi-circular. 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 center of the diameter of the discrete dilution hole 464 is aligned with the centerline 466. The discrete dilution channel 474 can have a front 478 and a rear 479.

[0053] Continue to refer to Figure 10The centerline 466 of the discrete dilution hole 464 is parallel to the centerline 476 of the discrete dilution tank 474. Furthermore, the centerline 466 of the discrete dilution hole 464 is aligned with the rear end 479 of the discrete dilution tank 474 at an axial position on the rear end 479 of the discrete dilution tank 474.

[0054] Figure 11 A schematic side cross-sectional view of the dilution channel 511 of the combustion liner 522 is shown. The combustion liner 522 can be coupled with... Figure 2 The combustion lining is the same as or similar to that of the other materials. (Reference) Figure 11 Side view 520 schematically represents dilution channel 511, which can be connected to... Figure 2 The dilution channel 211 is similar. The dilution channel 511 extends through the combustion liner 522 of the burner. The dilution channel 511 has a geometry formed by connecting a series of discrete dilution holes 524 and discrete dilution channels 534. The cross-section of each discrete dilution hole 524 can be semi-circular. For example, in a top view of the discrete dilution hole 524, the geometry 530 of the discrete dilution hole 524 can be semi-circular. 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 center of the diameter of the discrete dilution hole 524 is aligned with the centerline 526. The discrete dilution channel 534 can have a front 538 and a rear 539.

[0055] Continue to refer to Figure 11 The centerline 526 of the discrete dilution orifice 524 is parallel to the centerline 536 of the discrete dilution tank 534. Further, the centerline 526 of the discrete dilution orifice 524 is located axially behind the rear 539 of the discrete dilution tank 534. The offset 532 measured between the centerline 526 of the discrete dilution orifice 524 and the front 538 of the discrete dilution tank 534 is between zero and 0.3 times the diameter D of the discrete dilution orifice 524.

[0056] Figure 12 A schematic side cross-sectional view of the dilution channel 531 of the combustion liner 542 is shown. The combustion liner 542 can be coupled with... Figure 2 The combustion lining is the same as or similar to that of the other materials. (Reference) Figure 12 Side view 540 schematically represents dilution channel 531, which can be connected to... Figure 2Similar to dilution channel 211. Dilution channel 531 extends through the combustion liner 542 of the burner. Dilution channel 531 has a geometry formed by connecting a series of discrete dilution holes 544 and discrete dilution channels 554. The cross-section of each discrete dilution hole 544 may be semi-circular. For example, in a top view of the discrete dilution hole 544, the geometry 550 of the discrete dilution hole 544 may be semi-circular. The centerline of the circle formed by the two semicircles may be the centerline 546 of each discrete dilution hole 524. That is, the axis extending through the center of the diameter of the discrete dilution hole 544 is aligned with the centerline 546. Discrete dilution channels 554 may have a front 558 and a rear 559.

[0057] Continue to refer to Figure 12 The centerline 546 of the discrete dilution orifice 544 is parallel to the centerline 556 of the discrete dilution tank 554. Further, the centerline 546 of the discrete dilution orifice 544 is positioned axially in front of the front of the discrete dilution tank 554 at a position 558 in front of the front of the discrete dilution tank 534. The offset 552 measured between the centerline 546 of the discrete dilution orifice 544 and the front of the discrete dilution tank 534 at a distance between zero and one times the diameter D of the discrete dilution orifice 544.

[0058] Figure 13 A schematic side cross-sectional view 560 shows a first dilution channel 551 through the outer liner 562 of the burner and a second dilution channel 561 through the inner liner 582 of the burner, according to an embodiment of the present disclosure. The first dilution channel 551 has a geometry formed by connecting a series of discrete dilution holes 564 and discrete dilution channels 574. The centerline 566 of the discrete dilution holes 564 is parallel to the centerline 576 of the discrete dilution channels 574 and is aligned with the front end 578 of the discrete dilution channels 574 at an axial position. The second dilution channel 561 has a geometry formed by connecting a series of discrete dilution holes 584 and discrete dilution channels 594. The centerline 586 of the discrete dilution holes 584 is parallel to the centerline 596 of the discrete dilution channels 594 and is aligned with the front end 598 of the discrete dilution channels 594 at an axial position. 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.

[0059] Figure 14A schematic side cross-sectional view 620 of the dilution channel 611 of the combustion liner 622 is shown. The dilution channel 611 has a geometry formed by connecting a series of discrete dilution holes 624 and discrete dilution channels 634. The centerline 626 of the discrete dilution holes 624 is parallel to the centerline 636 of the discrete dilution channels 634. The flow direction of the discrete dilution holes 624 and / or the discrete dilution channels 634, i.e., the flow direction of the discrete holes and channels, can be inclined at an angle θ 632, which is defined relative to an axis 630 orthogonal to the combustion liner 622. The angle θ can range from negative 60 degrees (forward inclination) to positive 60 degrees (backward inclination). The centerline 626 of the discrete dilution holes 624 can be orthogonal to the combustion liner 622 and the centerline 636 of the discrete dilution channels 634 inclined at angle θ, and vice versa. Although shown aligned with the centerline 636, the centerline 626 can be relative to... Figures 9 to 13 The description is offset in any way previously described.

[0060] Figure 15 and 16 Each shows an embodiment of the present disclosure, such as burner 112 ( Figure 1 A schematic top view of the dilution channels in an exemplary inner and outer liner of a burner. A schematic outline of the dilution orifices in the outer liner is shown positioned over the dilution orifices in the inner liner. That is, when viewed from the top view, the outlines of the dilution orifices in the inner and outer liners may appear as follows: Figure 15 Or any one of 16 as shown.

[0061] For example, Figure 15 A top view 640 shows an outer liner 642 and an inner liner 652. The outer liner 642 has a series of outer liner discrete dilution holes, including outer liner discrete dilution holes 644 and 646. Although two outer liner discrete dilution holes are shown, more can be provided. The inner liner 652 has a series of inner liner discrete dilution holes, including inner liner discrete dilution holes 654 and 656. Although two inner liner discrete dilution holes are shown, more can be provided.

[0062] The outer liner discrete dilution holes 644 and 646 can be directly opposite each other, or they can be angled and staggered with the inner liner discrete dilution holes 654 and 656. In this way, when a series of outer and inner liner discrete dilution holes are axially aligned, the inner liner discrete dilution holes 654 are circumferentially located between the outer liner discrete dilution holes 644 and 646. The inner liner discrete dilution holes 656 can be located between the outer liner discrete dilution holes 646 and adjacent outer liner discrete dilution holes (not shown). Each inner liner discrete dilution hole can be midway between adjacent outer liner discrete dilution holes.

[0063] Although the display and description are interleaved, additional offsets can be expected between the outer liner discrete dilution orifices 644 and 646 and the inner liner discrete dilution orifices 654 and 656. For example, Figure 16 A top view 660 shows an outer liner 662 and an inner liner 672. The outer liner 662 has a series of outer liner discrete dilution holes, including outer liner discrete dilution holes 664 and 666. Although two outer liner discrete dilution holes are shown, more can be provided. The inner liner 672 has a series of inner liner discrete dilution holes, including inner liner discrete dilution holes 674 and 676. Although two inner liner discrete dilution holes are shown, more can be provided. Figure 16 The top lining can be with Figure 15 The lining is the same, however, with Figure 15 In contrast, the inner liner discrete dilution holes 674 and 676 can be positioned circumferentially closer to the outer liner discrete dilution holes 664 and 666, respectively. That is, the distance between an inner liner discrete dilution hole such as the inner liner discrete dilution hole 674 and a first outer liner discrete dilution hole such as the outer liner discrete dilution hole 666 can be smaller than the distance between the same inner liner discrete dilution hole (e.g., inner liner discrete dilution hole 674) and the outer liner discrete dilution hole adjacent to the first outer liner discrete dilution hole (e.g., outer liner discrete dilution hole 666). This relationship can be reversed, and any distance between the dilution holes can be set.

[0064] In addition to, or as an alternative to, the two positions described above, the inner liner discrete dilution holes may have other positioning positions relative to the outer liner discrete dilution holes. Furthermore, the outer liner discrete holes may be aligned with the center of the hydrocyclone or at an angle relative to the hydrocyclone. This angle may depend on the number of discrete holes in each hydrocyclone cup liner.

[0065] Figure 17 A schematic flowchart of a method 700 for passing a dilution flow through a burner liner according to an embodiment of the present disclosure is shown. Method 700 includes providing a burner having (i) a burner liner body with hot and cold sides and (ii) a core primary combustion zone of the burner, as shown in step 712. Method 700 further includes extending a dilution channel having a connecting geometry through the burner liner body, as shown in step 714. Method 700 further includes flowing a first dilution air through the dilution channel from the cold side to the hot side of the burner liner, as shown in step 716. The method further includes flowing a second dilution air through the dilution channel from the cold side to the hot side of the burner liner, as shown in step 718.

[0066] The connecting geometry of the dilution channel is formed by connecting a first geometry and a second geometry at predetermined relative positions, such that the first and second dilution airs merge within the combined geometry of the dilution channel. The first geometry can be positioned forward or upstream, while the second geometry is positioned backward or downstream.

[0067] The first geometry includes at least one discrete hole, and the second geometry includes at least one discrete dilution groove. The size of the discrete features (such as holes and discrete grooves) of the discrete positioning can vary circumferentially, or can have a specific pattern along the circumference. The discrete hole can have a semi-circular cross-section, or a triangular cross-section, or a semi-elliptical cross-section with a principal axis in the transverse direction, or a semi-elliptical cross-section with a principal axis in the axial direction, or any combination thereof.

[0068] The connecting geometry of the dilution channels can be repeated in a predetermined pattern, such as in a linear array generally circumferentially relative to the burner or in an alternating array. The dilution channels can be oriented at a predetermined angle relative to the burner. The dilution channels can be arranged orthogonal to the axis of the liner, or the dilution channels can be angled toward the axis of the cyclone separator.

[0069] Method 700 further includes providing a third geometry and connecting the third geometry to the first geometry, such that the first dilution air flows through the third geometry. The third geometry 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, such that the weighted area decreases from one side to the other. The precise dimensions of the protruding dilution insert can be adjusted for effective performance.

[0070] Method 700 further includes merging the first and second dilution air streams to provide a merged dilution air stream, thereby increasing mixing with multiple combustion products in the main combustion zone of the burner, as shown in step 722. Method 700 also includes injecting the merged dilution air stream into the burner to achieve a predetermined combustion state of the burner, as shown in step 724.

[0071] 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 and secondary combustion zones of the burner. The predetermined combustion state of the burner includes a burner outlet temperature profile conforming to a reference temperature profile. The predetermined combustion state of the burner also includes rapid quenching and rapid and increased mixing of the first and second dilution air streams 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 distributions or shares) of the first and second dilution air streams.

[0072] The liner for a gas turbine engine combustor disclosed herein provides a dilution channel with a connecting geometry that merges a first dilution airflow and a second dilution airflow into a merged dilution airflow.

[0073] When the second dilution air flow is downstream of the first dilution air flow, it can provide hydraulic support for the first dilution air flow. When the second dilution air flow is upstream of the first dilution air flow, it 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 flows of the first dilution air flow and enhance the penetration of the first dilution air flow into the core primary combustion zone of the burner.

[0074] The combined dilution airflow increases the rapid cooling and mixing of the dilution airflow with multiple combustion products in the primary combustion zone of the burner, resulting in a more uniform temperature distribution within the primary combustion zone and a burner outlet temperature profile that conforms to the reference temperature profile. The combined dilution airflow also reduces nitrogen oxides (NOx) in the core primary combustion zone of the burner, in accordance with regulatory guidelines. x ) emission levels.

[0075] Further aspects of this disclosure are provided by the subject matter of the following provisions.

[0076] A liner for a combustor in a gas turbine engine. The liner has: a liner body having a cold side and a hot side; and a dilution array having a plurality of dilution channels. Each of the plurality of dilution channels includes a connecting geometry that repeats in a predetermined pattern and extends circumferentially around the liner body. The dilution channels are configured to (i) merge a first dilution airflow flowing from the cold side to the hot side through the dilution channels and a second dilution airflow flowing from the cold side to the hot side through the dilution channels into a merged dilution airflow, and (ii) inject the merged dilution airflow into the core primary combustion zone of the combustor to achieve a predetermined combustion state of the combustor. The dilution array repeats along the axial length of the liner body.

[0077] According to the liner described in the foregoing clause, the second dilution airflow fills the wake region formed behind the plurality of off-scattered flows of the first dilution airflow.

[0078] According to any one of the foregoing clauses, the first dilution airflow is 10% to 90% of the total flow through the plurality of dilution channels.

[0079] The lining according to any one of the foregoing clauses, wherein the first dilution airflow is located axially rearward of the second dilution airflow.

[0080] According to any one of the foregoing clauses, the first dilution airflow is located axially ahead of the second dilution airflow.

[0081] According to any one of the foregoing clauses, each of the plurality of dilution channels includes discrete grooves and discrete holes.

[0082] According to any one of the foregoing clauses, the discrete groove has a first groove extension extending circumferentially from a first side of the discrete hole in a first direction, and a second groove extension extending circumferentially from a second side of the discrete hole in a second direction, wherein the first direction is opposite to the second direction.

[0083] According to any one of the foregoing clauses, the first groove extension and the second groove extension are each in the range of 0.5 to 15 times the groove width of the discrete groove.

[0084] According to any one of the foregoing clauses, each of the plurality of dilution channels includes a dilution insert that extends radially inward from the hot side of the liner body toward the centerline of the burner.

[0085] The lining according to any one of the foregoing clauses, wherein the dilution insert has a constant height from the front side of the dilution insert to the rear side of the dilution insert.

[0086] The lining according to any one of the foregoing clauses, wherein the dilution insert has a variable height from the front side of the dilution insert to the rear side of the dilution insert.

[0087] According to any one of the foregoing clauses, each of the plurality of dilution channels further includes a discrete groove and a discrete hole, and the dilution insert has a height in the range of 0.1 to 10 times the diameter of the discrete hole.

[0088] The lining according to any one of the foregoing clauses, wherein the dilution insert has a beveled portion along the front side of the dilution insert.

[0089] According to any one of the foregoing clauses, the connecting geometry includes at least a first geometry and a second geometry connected at predetermined relative positions, and wherein a first dilution airflow flows through the first geometry and a second dilution airflow flows through the second geometry.

[0090] The lining according to any one of the foregoing clauses, wherein the first geometry includes discrete holes having a semi-circular cross-section.

[0091] The lining according to any one of the foregoing clauses, wherein the first geometry includes at least one discrete hole, and the second geometry includes at least one discrete groove.

[0092] The lining according to any one of the foregoing clauses, wherein the predetermined pattern is a linear array.

[0093] According to any one of the foregoing clauses, the linear array includes the plurality of dilution channels arranged circumferentially around the lining body along a common axis.

[0094] The lining according to any one of the foregoing clauses, wherein the predetermined pattern comprises an interlaced array.

[0095] According to any one of the foregoing clauses, the staggered array includes a first row of the plurality of dilution channels and a second row of the plurality of dilution channels, wherein the centerline of the plurality of dilution channels in the first row is axially offset from the centerline of the plurality of dilution channels in the second row.

[0096] While the foregoing description pertains to preferred embodiments, it should be noted that other variations and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of this disclosure. Furthermore, 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 includes: Lining body, the lining body having a cold side and a hot side; and A dilution array having a plurality of dilution channels, each of the plurality of dilution channels including a connecting geometry that repeats in a predetermined pattern and extends circumferentially around the lining body, each of the plurality of dilution channels further including; Discrete orifice, the discrete orifice having a first dilution airflow, the first dilution airflow flowing through the discrete orifice from the cold side to the hot side; and A discrete channel having a second dilution airflow flowing from the cold side to the hot side through the discrete channel, wherein the discrete orifice is located downstream of the discrete channel such that the first dilution airflow is downstream of the second dilution airflow; The dilution array is configured to (i) merge the first dilution air flow and the second dilution air flow into a combined dilution air flow, and (ii) inject the combined dilution air flow into the core primary combustion zone of the burner to achieve a predetermined combustion state of the burner. The dilution array repeats along the axial length of the lining body.

2. The lining according to claim 1, characterized in that, The second dilution airflow fills the wake region formed behind the plurality of outscattered flows of the first dilution airflow.

3. The lining according to claim 1, characterized in that, The first dilution airflow is between 10% and 90% of the total flow through the plurality of dilution channels.

4. The lining according to claim 1, characterized in that, The discrete groove has a first groove extension extending circumferentially from a first side of the discrete hole in a first direction, and a second groove extension extending circumferentially from a second side of the discrete hole in a second direction, wherein the first direction is opposite to the second direction.

5. The lining according to claim 4, characterized in that, The first groove extension and the second groove extension are each within the range of 0.5 to 15 times the width of the discrete groove.

6. The lining according to claim 1, characterized in that, Each of the plurality of dilution channels includes a dilution insert that extends radially inward from the hot side of the liner body toward the centerline of the burner.

7. The lining according to claim 6, characterized in that, The dilution insert has a constant height from the front side of the dilution insert to the rear side of the dilution insert.

8. The lining according to claim 6, characterized in that, The dilution insert has a variable height from the front side of the dilution insert to the rear side of the dilution insert.

9. The lining according to claim 6, characterized in that, The dilution insert has a height ranging from 0.1 to 10 times the diameter of the discrete aperture.

10. The lining according to claim 6, characterized in that, The dilution insert has a beveled portion along the front side of the dilution insert.

11. The lining according to claim 1, characterized in that, The discrete holes described therein have a semi-circular cross-section.

12. The lining according to claim 1, characterized in that, The predetermined pattern is a linear array.

13. The lining according to claim 12, characterized in that, The linear array includes the plurality of dilution channels arranged circumferentially around the lining body along a common axis.

14. The lining according to claim 1, characterized in that, The predetermined pattern includes an interlaced array.

15. The lining according to claim 14, characterized in that, The staggered array includes a first row and a second row of the plurality of dilution channels, wherein the centerline of the plurality of dilution channels in the first row is axially offset from the centerline of the plurality of dilution channels in the second row.

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