Combustion liner

Abstract

A liner for a combustor in a gas turbine engine and related methods. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a linkage geometry extending through the liner body. The dilution passage is configured to (i) merge a first dilution air flow through the dilution passage from the cold side to the hot side and a second dilution air flow through the dilution passage from the cold side to the hot side into a merged dilution air flow, and (ii) inject the merged 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] This disclosure relates to combustion liners. Specifically, this disclosure relates to a liner for a combustor in a gas turbine engine, the liner having a dilution opening and a passageway surrounding the dilution opening. 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 Embodiments according to this disclosure are shown. Figure 2 A schematic side view of the dilution channel in the lining.

[0007] Figure 4 Embodiments according to this disclosure are shown. Figure 2 A schematic side perspective view of a mirrored version of the burning lining.

[0008] Figure 5 Embodiments according to this disclosure are shown. Figure 4 A schematic side perspective view of the dilution channel of the lining.

[0009] Figure 6 A schematic side cross-sectional view of a dilution channel in a combustion liner according to an embodiment of the present disclosure is shown.

[0010] Figure 7 A schematic side cross-sectional view of a dilution channel in a combustion liner according to an embodiment of the present disclosure is shown.

[0011] Figure 8 A schematic side cross-sectional view of a dilution channel in a combustion liner according to an embodiment of the present disclosure is shown.

[0012] 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.

[0013] Figure 10 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.

[0014] Figure 11 Embodiments according to this disclosure are shown. Figure 2 A schematic side cross-sectional view of the dilution channel of the lining.

[0015] Figure 12 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.

[0016] Figure 13 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.

[0017] Figure 14 This illustrates an embodiment of the present disclosure using... Figure 3 A schematic side perspective view of the flow dynamics of the burner lining.

[0018] Figure 15 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

[0019] 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.

[0020] 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.

[0021] 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.

[0022] 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.

[0023] 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.

[0024] The use of discrete dilution orifices (also known as “discrete orifices”) and annular dilution channels (also known as “annular 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 combustion chamber after dilution, resulting in a higher outlet temperature profile / pattern, and potentially negatively impacting combustion efficiency.

[0025] This disclosure provides a method for synergistically combining the advantages of discrete and annular dilution by providing a burner comprising 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.

[0026] 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, 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.

[0027] 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.

[0028] 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 connected to the rear of the liner forming annular groove 214 (e.g., Figure 6 (359). In some examples, the bridge structure can be welded to the annular groove 214. The bridge structure can support and control the dilution gap.

[0029] 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 1 In the core primary combustion zone 114 of the burner 112, the predetermined combustion state of the burner 112 is achieved.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] 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.

[0034] 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.

[0035] 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.

[0036] 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 x Emissions. 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.

[0037] Figure 6 A schematic side cross-sectional view of the dilution channel 311 of the combustion liner 342 is shown. The combustion liner 342 can be coupled with... Figure 2 The combustion lining is the same as or similar to that of the other materials. (Reference) Figure 6 Side view 340 schematically represents dilution channel 311, which can be connected to... Figure 2The dilution channel 211 is similar. The dilution channel 311 extends through the combustion liner 342 of the burner. The combustion liner 342 can be an inner or outer liner of the combustion chamber. The dilution channel 311 has a geometry formed by connecting a series of discrete dilution holes 344 and an annular dilution groove 354. The cross-section of each discrete dilution hole 344 can be semi-circular. For example, in a top view of the discrete dilution holes 344, the geometry 350 of the discrete dilution holes 344 can be semi-circular. The centerline of the circle formed by the two semicircles can be the centerline 346 of each discrete dilution hole 344. That is, the axis extending through the center of the diameter of the discrete dilution hole 344 is aligned with the centerline 346. The annular dilution groove 354 can have a front 358 and a rear 359.

[0038] Continue to refer to Figure 6 The centerline 346 of the discrete dilution orifice 344 is parallel to the centerline 356 of the annular dilution groove 354. The front end 358 of the annular dilution groove 354 merges with and aligns with each diameter of the discrete dilution orifice 344, which may have a semi-circular geometry. Therefore, the centerline 346 of the discrete dilution orifice 344 is aligned with the front end 358 of the annular dilution groove 354 at an axial position, as shown in the top view. Further, 10% to 90% of the total flow area of ​​the dilution channel 311 is occupied by the discrete dilution orifice 344, and the remaining portion of the total flow area is occupied by the annular dilution groove 354.

[0039] Figure 7 A schematic side view cross-section of the dilution channel 331 of the combustion liner 362 is shown. The combustion liner 362 can be used with... Figure 2 The combustion lining is the same as or similar to that of the other materials. (Reference) Figure 7 The side view 360 schematically represents the dilution channel 331, which can be connected with... Figure 2 The dilution channel 211 is similar. The dilution channel 331 extends through the combustion liner 362 of the burner. The dilution channel 311 has a geometry formed by connecting a series of discrete dilution holes 364 and an annular dilution groove 374. The cross-section of each discrete dilution hole 364 can be semi-circular. For example, in a top view of the discrete dilution hole 364, the geometry 370 of the discrete dilution hole 364 can be semi-circular. The centerline of the circle formed by the two semicircles can be the centerline 366 of each discrete dilution hole 364. That is, the axis extending through the center of the diameter of the discrete dilution hole 364 is aligned with the centerline 366. The annular dilution groove 374 can have a front 378 and a rear 379.

[0040] Continue to refer to Figure 7The centerline 366 of the discrete dilution hole 364 is parallel to the centerline 376 of the annular dilution groove 374. Furthermore, the centerline 366 of the discrete dilution hole 364 is aligned with the rear end 379 of the annular dilution groove 374 at an axial position on the rear end 379 of the annular dilution groove 374.

[0041] Figure 8 A schematic side cross-sectional view of the dilution channel 411 of the combustion liner 422 is shown. The combustion liner 422 can be connected with... Figure 2 The combustion lining is the same as or similar to that of the other materials. (Reference) Figure 8 Side view 420 schematically represents dilution channel 411, which can be connected to... Figure 2 The dilution channel 211 is similar. The dilution channel 411 extends through the combustion liner 422 of the burner. The dilution channel 411 has a geometry formed by connecting a series of discrete dilution holes 424 and an annular dilution groove 434. The cross-section of each discrete dilution hole 424 may be semi-circular. For example, in a top view of the discrete dilution hole 424, the geometry 430 of the discrete dilution hole 424 may be semi-circular. The centerline of the circle formed by the two semicircles may be the centerline 426 of each discrete dilution hole 424. That is, the axis extending through the center of the diameter of the discrete dilution hole 424 is aligned with the centerline 426. The annular dilution groove 434 may have a front 438 and a rear 439.

[0042] Continue to refer to Figure 8 The centerline 426 of the discrete dilution orifice 424 is parallel to the centerline 436 of the annular dilution groove 434. Further, the centerline 426 of the discrete dilution orifice 424 is located axially behind the rear 439 of the annular dilution groove 434. The offset 432 measured between the centerline 426 of the discrete dilution orifice 424 and the front 438 of the annular dilution groove 434 is between zero and 0.3 times the diameter D of the discrete dilution orifice 424.

[0043] Figure 9 A schematic side cross-sectional view of the dilution channel 431 of the combustion liner 442 is shown. The combustion liner 442 can be connected 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 431, which can be connected to... Figure 2Similar to dilution channel 211. Dilution channel 431 extends through the combustion liner 442 of the burner. Dilution channel 431 has a geometry formed by connecting a series of discrete dilution holes 444 and an annular dilution groove 454. The cross-section of each discrete dilution hole 444 may be semi-circular. For example, in a top view of the discrete dilution hole 444, the geometry 450 of the discrete dilution hole 444 may be semi-circular. The centerline of the circle formed by the two semicircles may be the centerline 446 of each discrete dilution hole 424. 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 groove 454 may have a front 458 and a rear 459.

[0044] Continue to refer to Figure 9 The centerline 446 of the discrete dilution orifice 444 is parallel to the centerline 456 of the annular dilution groove 454. Further, the centerline 446 of the discrete dilution orifice 444 is positioned axially in front of the annular dilution groove 434 at a position 458 in front of the annular dilution groove 454. The offset 452 measured between the centerline 446 of the discrete dilution orifice 444 and the front of the annular dilution groove 434 at a distance between zero and one times the diameter D of the discrete dilution orifice 444.

[0045] Figure 10 A schematic side cross-sectional view 460 shows a first dilution channel 451 through the outer liner 462 of the burner and a second dilution channel 461 through the inner liner 482 of the burner according to an embodiment of the present disclosure. The first dilution channel 451 has a geometry formed by connecting a series of discrete dilution holes 464 and an annular dilution groove 474. The centerline 466 of the discrete dilution holes 464 is parallel to the centerline 476 of the annular dilution groove 474 and is aligned with the front end 478 of the annular dilution groove 474 at an axial position. The second dilution channel 461 has a geometry formed by connecting a series of discrete dilution holes 484 and annular dilution groove 494. The centerline 486 of the discrete dilution holes 484 is parallel to the centerline 496 of the annular dilution groove 494 and is aligned with the front end 498 of the annular dilution groove 494 at an axial position. The offset 480 measured between the centerline 466 of the discrete dilution orifice 464 on the outer liner 462 and the centerline 486 of the discrete dilution orifice 484 on the inner liner 482 is between zero and + / - six times the diameter of the discrete dilution orifice 464 or 484.

[0046] Figure 11A schematic side cross-sectional view 520 of the dilution channel 511 of the combustion liner 522 is shown. The dilution channel 511 has a geometry formed by connecting a series of discrete dilution holes 524 and annular dilution grooves 534. The centerline 526 of the discrete dilution holes 524 is parallel to the centerline 536 of the annular dilution grooves 534. The centerline 526 of the discrete dilution holes 524 and / or the centerline 536 of the annular dilution grooves 534, i.e., the flow direction of the discrete and annular flows, can be inclined at an angle θ 532, which is defined relative to an axis 530 orthogonal to the combustion liner 522. The angle θ can range from -60 degrees (forward inclination) to +60 degrees (backward inclination). The centerline 526 of the discrete dilution holes 524 can be orthogonal to the centerline 536 of the combustion liner 522 and the annular dilution grooves 534 inclined at angle θ, and vice versa. Although shown aligned with the centerline 536, the centerline 526 can be relative to... Figures 7 to 10 The description is offset in any way previously described.

[0047] Figure 12 and 13 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 12 Or any one of 13 as shown.

[0048] For example, Figure 12 A top view 540 shows an outer liner 542 and an inner liner 552. The outer liner 542 has a series of outer liner discrete dilution holes, including outer liner discrete dilution holes 544 and 546. Although two outer liner discrete dilution holes are shown, more can be provided. The inner liner 552 has a series of inner liner discrete dilution holes, including inner liner discrete dilution holes 554 and 556. Although two inner liner discrete dilution holes are shown, more can be provided.

[0049] The outer liner discrete dilution holes 544 and 546 can be directly opposite each other, or they can be angled and staggered with the inner liner discrete dilution holes 554 and 556. In this way, when a series of outer and inner liner discrete dilution holes are axially aligned, the inner liner discrete dilution holes 554 are circumferentially located between the outer liner discrete dilution holes 544 and 546. The inner liner discrete dilution holes 556 can be located between the outer liner discrete dilution holes 546 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.

[0050] Although the display and description are interleaved, additional offsets between the outer liner discrete dilution holes 544 and 546 and the inner liner discrete dilution holes 554 and 556 can be expected. For example, Figure 13 A top view 560 shows an outer liner 562 and an inner liner 572. The outer liner 562 has a series of outer liner discrete dilution holes, including outer liner discrete dilution holes 564 and 566. Although two outer liner discrete dilution holes are shown, more can be provided. The inner liner 572 has a series of inner liner discrete dilution holes, including inner liner discrete dilution holes 574 and 576. Although two inner liner discrete dilution holes are shown, more can be provided. Figure 13 The top lining can be with Figure 12 The lining is the same, however, with Figure 13 In contrast, the inner liner discrete dilution holes 574 and 576 can be positioned circumferentially closer to the outer liner discrete dilution holes 564 and 566, respectively. That is, the distance between an inner liner discrete dilution hole such as the inner liner discrete dilution hole 574 and a first outer liner discrete dilution hole such as the outer liner discrete dilution hole 566 can be smaller than the distance between the same inner liner discrete dilution hole (e.g., inner liner discrete dilution hole 574) and the outer liner discrete dilution hole adjacent to the first outer liner discrete dilution hole (e.g., outer liner discrete dilution hole 566). This relationship can be reversed, and any distance between the dilution holes can be set.

[0051] 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.

[0052] Figure 14 This illustrates an embodiment of the present disclosure using... Figure 3 A schematic bottom perspective view of the flow dynamics of the burner lining. Figure 14 Is with Figure 3 A schematic representation of the flow dynamics associated with dilution channel 211. (See reference) Figure 14 Reference number 220 indicates Figure 2 A bottom view of the dilution channel 211, which connects the discrete orifice 212 to the annular groove 214. Within the connecting geometry of the dilution channel 211, a first dilution airflow 213 passing through the discrete orifice 212 and a second dilution airflow 215 passing through the annular groove 214 merge into a combined dilution airflow 217. Further, the combined dilution airflow 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.

[0053] The first dilution airflow 213 is in Figure 1 Turbulence is generated in the core primary combustion zone 114 of the burner 112. A first dilution air flow 213 through discrete dilution orifices can create a wake region after the first dilution air flow 213 exiting each discrete dilution orifice. A second dilution air flow 215 fills the wake region formed after the multiple scattering flows of the first dilution air flow 213. Further, the second dilution air flow 215 provides hydraulic support for the first dilution air flow 213 and enhances the penetration of the first dilution air flow 213 into the core primary combustion zone 114 of the burner 112. Further, the second dilution air flow 215 permeates between the scattering flows of the first dilution air flow 213 and prevents the generation of any high-temperature zones in the region near the liner and between the scattering flows of the first dilution air flow 213. Although relative to Figures 1 to 3 Described, but Figure 15 It can also be described Figures 4 to 14 The flow in the dilution channel.

[0054] Figure 15 A schematic flowchart of a method 600 for passing a dilution flow through a burner liner according to an embodiment of the present disclosure is shown. Method 600 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 612. Method 600 further includes extending a dilution channel having a connecting geometry through the burner liner body, as shown in step 614. Method 600 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 616. The method also 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 618.

[0055] 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.

[0056] The first geometry includes at least one discrete hole, and the second geometry includes at least one discrete annular groove. The size of the discrete features (such as the hole and the annular groove) 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 with one side of the triangle aligned with and parallel to the annular groove, or a semi-elliptical cross-section with a principal axis in the transverse direction (e.g., racetrack-shaped), or a semi-elliptical cross-section with a principal axis in the axial direction (e.g., racetrack-shaped), or any combination thereof.

[0057] 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.

[0058] Method 600 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 622. Method 600 also includes injecting the merged dilution air stream into the burner to achieve a predetermined combustion state of the burner, as shown in step 624.

[0059] The burner's predetermined combustion state includes compliant NO x Emission 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 multiple 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.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] Further aspects of this disclosure are provided by the subject matter of the following provisions.

[0064] A liner for a combustor in a gas turbine engine, comprising: a liner body having a cold side and a hot side; and a dilution channel having a connecting geometry extending through the liner body, the dilution channel being configured to (i) merge a first dilution air flow flowing from the cold side to the hot side through the dilution channel and a second dilution air flow flowing from the cold side to the hot side through the dilution channel into a merged dilution air flow, and (ii) inject the merged dilution air flow into the core primary combustion zone of the combustor to achieve a predetermined combustion state of the combustor.

[0065] According to the liner described in the foregoing clause, the second dilution airflow provides hydraulic support to the first dilution airflow and enhances the penetration of the first dilution airflow into the core primary combustion zone of the burner.

[0066] According to any one of the foregoing clauses, the first dilution airflow generates turbulence in the core primary combustion zone of the burner, and the second dilution airflow fills the wake region formed behind a plurality of off-scattered flows of the first dilution airflow.

[0067] According to any one of the foregoing clauses, the second dilution airflow permeates between the plurality of scattering flows of the first dilution airflow and prevents the formation of high-temperature zones near the lining and between the plurality of scattering flows.

[0068] According to any one of the foregoing clauses, the predetermined combustion state of the burner includes (i) a reduced temperature in the core primary combustion zone of the burner, (ii) a compliant NOx emission level, (iii) a uniform temperature distribution in the core primary combustion zone of the burner, (iv) a burner outlet temperature profile conforming to a reference temperature profile, (v) increased mixing of the first and second dilution air streams with a plurality of combustion products in the core primary combustion zone of the burner, (vi) rapid quenching and rapid mixing of the first and second dilution air streams with a plurality of combustion products in the core primary combustion zone of the burner, (vii) a predetermined air split ratio of the first and second dilution air streams, or (viii) any combination thereof.

[0069] According to any one of the foregoing clauses, the first dilution airflow is 10% to 90% of the total flow through the dilution channel.

[0070] 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.

[0071] According to any one of the foregoing clauses, the second geometry includes an annular groove, and the first geometry includes discrete holes having a semi-circular cross-section, an elliptical cross-section, a racetrack-shaped cross-section, or a triangular cross-section, wherein one side of the triangular cross-section is aligned with and parallel to the annular groove.

[0072] The lining according to any one of the foregoing clauses, wherein the first geometry includes a plurality of discrete holes, and the second geometry includes an annular groove.

[0073] The lining according to any one of the foregoing clauses, wherein the annular dilution groove is downstream of the plurality of discrete dilution holes.

[0074] According to any one of the foregoing clauses, the lining wherein the dilution channel includes a plurality of discrete dilution holes through which the first dilution airflow flows, and an annular dilution groove through which the second dilution airflow flows.

[0075] According to any one of the preceding clauses, each of the plurality of discrete dilution holes has a first center line, and the annular dilution groove has a second center line, wherein the first center line is parallel to the second center line.

[0076] The lining according to any one of the foregoing clauses, wherein the first center line is offset in front of the second center line and aligned with the front surface of the annular dilution groove.

[0077] The lining according to any one of the foregoing clauses, wherein the first center line is offset in front of the second center line and in front of the front surface of the annular dilution groove.

[0078] The lining according to any one of the foregoing clauses, wherein the first centerline is offset behind the second centerline and aligned with the rear surface of the annular dilution groove.

[0079] The lining according to any one of the foregoing clauses, wherein the first centerline is offset behind the second centerline and behind the rear surface of the annular dilution groove.

[0080] The lining according to any one of the foregoing clauses, wherein the first center line and the second center line are at an angle relative to an axis orthogonal to the lining.

[0081] The lining according to any one of the foregoing clauses, wherein the lining body comprises an outer lining and an inner lining, the outer lining and the inner lining each comprising the dilution channel, such that the outer lining comprises an outer lining first dilution airflow and an outer lining second dilution airflow, and the inner lining comprises an inner lining first dilution airflow and an inner lining second dilution airflow.

[0082] The lining according to any one of the foregoing clauses, wherein, in a top view, the first dilution airflow of the outer lining is offset from the first dilution airflow of the inner lining.

[0083] A method for diluting a flow through a burner includes: diverting a first diluting air flow from a cold side of a combustion liner to a hot side of the combustion liner; diverting a second diluting air flow from the cold side of the combustion liner to the hot side of the combustion liner; merging the first and second diluting air flows to provide a merged diluting air flow; injecting the merged diluting air flow into the burner to achieve a predetermined combustion state of the burner; generating turbulence in the core primary combustion zone of the burner using the first diluting air flow; and filling a wake region formed behind the first diluting air flow using the second diluting air flow, wherein the merged diluting air flow is formed by a connecting geometry through the combustion liner.

[0084] 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 channel having a connecting geometry extending through the liner body, the dilution channel being configured to (i) merge a first dilution air flow flowing from the cold side to the hot side through the dilution channel and a second dilution air flow flowing from the cold side to the hot side through the dilution channel 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 connecting geometry having: Multiple discrete dilution orifices through which the first dilution airflow flows; and An annular dilution channel through which the second dilution airflow flows, the annular dilution channel having a constant width from its front surface to its rear surface. The annular dilution groove's front surface extends along a radial plane parallel to the front surface, the radial plane extending through the centerline of each of the plurality of discrete dilution holes. The plurality of discrete dilution holes are located entirely in front of the annular dilution groove, such that the first dilution airflow flowing through the plurality of discrete dilution holes forms a wake region behind the first dilution airflow flowing out of each of the plurality of discrete dilution holes, and the second dilution airflow fills the wake region and provides hydraulic support for the first dilution airflow.

2. The lining according to claim 1, characterized in that, The second dilution airflow enhances the penetration of the first dilution airflow into the core primary combustion zone of the burner.

3. The lining according to claim 1, characterized in that, The second dilution airflow permeates between the plurality of scattering flows of the first dilution airflow and prevents the formation of high-temperature zones near the lining and between the plurality of scattering flows.

4. The lining according to claim 1, characterized in that, The predetermined combustion state of the burner includes (i) a reduced temperature in the core primary combustion zone of the burner, and (ii) compliant NO. x The emission level, (iii) the uniform temperature distribution within the core primary combustion zone of the burner, (iv) the burner outlet temperature profile conforming to a reference temperature profile, (v) the increased mixing of the first and second dilution air streams with a plurality of combustion products in the core primary combustion zone of the burner, (vi) the rapid cooling and rapid mixing of the first and second dilution air streams with a plurality of combustion products in the core primary combustion zone of the burner, (vii) the predetermined air split ratio of the first and second dilution air streams, or (viii) any combination thereof.

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

6. The lining according to claim 1, characterized in that, Each discrete dilution orifice has a semi-circular cross-section, an elliptical cross-section, a racetrack-shaped cross-section, or a triangular cross-section, wherein one side of the triangular cross-section is aligned with and parallel to the annular dilution groove.

7. The lining according to claim 1, characterized in that, Each of the plurality of discrete dilution holes has a first center line, and the annular dilution groove has a second center line, wherein the first center line is parallel to the second center line.

8. The lining according to claim 7, characterized in that, The first centerline is offset in front of the second centerline and aligned with the front surface of the annular dilution tank.

9. The lining according to claim 7, characterized in that, The first center line is located in front of the second center line and offset in front of the front surface of the annular dilution tank.

10. The lining according to claim 7, characterized in that, The first centerline and the second centerline are at an angle relative to an axis orthogonal to the lining.

11. The lining according to claim 1, characterized in that, The lining body includes an outer lining and an inner lining, each of the outer lining and the inner lining including the dilution channel, such that the outer lining includes a first dilution airflow and a second dilution airflow, and the inner lining includes a first dilution airflow and a second dilution airflow.

12. The lining according to claim 11, characterized in that, In the top view, the first dilution airflow of the outer lining is offset from the first dilution airflow of the inner lining.

13. A method for diluting a stream passing through a burner, characterized in that, The method includes: The first dilution airflow is directed from the cold side of the combustion liner to the hot side of the combustion liner; The second dilution airflow is directed from the cold side of the combustion liner to the hot side of the combustion liner; The first and second dilution air flows are combined to provide a combined dilution air flow; The combined dilution air stream is injected into the burner to achieve the predetermined combustion state of the burner; The first dilution airflow generates turbulence in the core primary combustion zone of the burner; and The second dilution airflow fills the wake region formed behind the first dilution airflow. The combined dilution airflow is formed by a connecting geometry through the combustion liner, the connecting geometry having: Multiple discrete dilution orifices through which the first dilution airflow flows; and An annular dilution channel through which the second dilution airflow flows, the annular dilution channel having a constant width from its front surface to its rear surface. The annular dilution groove's front surface extends along a radial plane parallel to the front surface, the radial plane extending through the centerline of each of the plurality of discrete dilution holes. The plurality of discrete dilution holes are located entirely in front of the annular dilution groove, such that the first dilution airflow flowing through the plurality of discrete dilution holes forms a wake region behind the first dilution airflow flowing out of each of the plurality of discrete dilution holes, and the second dilution airflow fills the wake region and provides hydraulic support for the first dilution airflow.

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