combustion liner

Abstract

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

Description

Technical Field

[0001] The present disclosure relates to a combustion liner. Specifically, the present disclosure relates to a liner for a combustor in a gas turbine engine, the liner having a dilution opening and a passage surrounding the dilution opening. Background Art

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

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

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

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

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

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

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

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

[0010] Figure 7 The embodiment according to the present disclosure is shown Figure 6 Schematic partial bottom perspective view of the dilution channel of the liner.

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

[0012] Figure 9 A schematic side cross-sectional view of a dilution channel of a combustion liner is shown according to an embodiment of the present disclosure.

[0013] Figure 10 A schematic side cross-sectional view of a dilution channel of a combustion liner is shown according to an embodiment of the present disclosure.

[0014] Figure 11 A schematic side cross-sectional view of a dilution channel of a combustion liner is shown according to an embodiment of the present disclosure.

[0015] Figure 12 A schematic side cross-sectional view of a dilution channel of a combustion liner is shown according to an embodiment of the present disclosure.

[0016] Figure 13 Shown is a schematic side cross-sectional view of a dilution passage through the outer and inner liners of a combustor according to an embodiment of the present disclosure.

[0017] Figure 14 The embodiment according to the present disclosure is shown Figure 2 Schematic side cross-sectional view of the dilution channel of the liner.

[0018] Figure 15 A schematic top view of exemplary inner and outer liner dilution channels of a combustor is shown according to an embodiment of the present disclosure.

[0019] Figure 16 A schematic top view of exemplary inner and outer liner dilution channels of a combustor is shown according to an embodiment of the present disclosure.

[0020] Figure 17 A schematic flow chart of a method of passing a dilution flow through a combustor liner of a combustor is shown, according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0021] The features, advantages and embodiments of the present disclosure are set forth or apparent from consideration of the following detailed description, drawings and claims. In addition, it should be understood that the following detailed description is exemplary and is intended to provide further explanation without limiting the scope of the disclosure as claimed.

[0022] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0023] Reference will now be made in detail to the present embodiments of the disclosed subject matter, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and the description have been used to refer to like or similar parts of the disclosed subject matter. As used herein, the terms "first," "second," "third," "fourth," and "exemplary" are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of each component.

[0024] The terms "upstream" or "front" and "downstream" or "rear" refer to relative directions relative to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing. For example, "front" refers to the front end or direction of an engine, and "rear" refers to the rear end or direction of an engine.

[0025] Gas turbine engines, such as those used to power aircraft or industrial applications, include a compressor, a combustor, and a turbine arranged about a central engine axis, with the compressor positioned axially upstream of the combustor and the turbine positioned axially downstream of the combustor. The compressor pressurizes an air supply, the combustor combusts a hydrocarbon fuel in the presence of the pressurized air, and the turbine extracts energy from the resulting combustion gases. The combustor's air pressure ratio and / or outlet temperature can be varied to improve gas turbine engine cycle efficiency. Furthermore, any changes in the combustor's air pressure ratio and / or outlet temperature can impact the operability and life of the turbine. Combustor outlet temperatures exceeding 1100°C are currently common in gas turbine engines, while acceptable metal temperatures for the turbine's stationary nozzles and rotating blades remain limited to 900°C or 1000°C. Furthermore, the temperature of the turbine blades affects the blades' mechanical strength (e.g., creep and fatigue) as well as their resistance to oxidation and corrosion. Maintaining combustor temperatures within an acceptable range can significantly improve the life of the turbine blades and turbine nozzles. Structurally, the combustor liner is arranged inside the combustor to withstand extreme thermal loads, and extensive combustor liner cooling arrangements may reduce thermal stresses in several mechanical parts and components of the gas turbine engine.

[0026] In the combustor of a gas turbine engine, air generally flows through outer and inner passages surrounding the combustor liner. The air flows from the upstream end of the combustor liner to the downstream end of the combustor liner. Some of the air flowing through the outer and inner passages is diverted through a plurality of dilution holes provided in the combustor liner and enters the core primary combustion zone as dilution air. One purpose of the dilution air flow is to cool (i.e., quench) the combustion gases in the core primary combustion zone before the gases enter the turbine section. However, the combustion products from the core primary combustion zone of the combustor must be quenched quickly and efficiently to minimize the high temperature areas and thereby reduce NO from the combustion system. x emission.

[0027] It is known to use discrete dilution holes (also referred to as "discrete holes") and annular dilution slots (also referred to as "annular slots") through the liner, which essentially form flow channels through the liner. In the case of discrete dilution, high turbulence is introduced from multiple discrete jets into the core primary combustion zone of the combustor. As a result, good mixing of the combustion products is achieved after dilution. However, due to the low jet penetration, some high temperature areas still exist within the combustor core. Further, the wake regions formed behind the discrete dilution jets and between the discrete dilution jets cause low cooling and low mixing of the dilution air with the primary combustion products. On the other hand, in annular dilution, the jet penetration level is high, but the turbulence generated is low, resulting in a low level of mixing of the dilution air with the primary zone products after the dilution flow enters, causing potentially higher temperatures in the core of the combustion chamber after dilution, thereby causing a higher outlet temperature profile / pattern and potentially negatively affecting combustion efficiency.

[0028] The present disclosure provides a method for synergistically combining the advantages of discrete dilution and annular dilution by providing a combustor comprising a liner body having a cold side and a hot side. The liner body includes a dilution passage having a concatenated geometry extending through the liner body. A first dilution air flow and a second dilution air flow are passed through the dilution passage from the cold side of the combustion liner to the hot side of the combustor liner. The dilution passage combines the first and second dilution air flows within the concatenated geometry into a combined dilution air flow, and injects the combined dilution air flow into a core primary combustion zone of the combustor to achieve a predetermined combustion state of the combustor.

[0029] 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 that are discharged into the turbine section (not shown) of the engine. The combustor 112 includes a core primary combustion zone 114. The core primary combustion zone 114 is defined by an outer liner 116, an inner liner 118, and a shroud 120. In addition, a diffuser 122 is positioned upstream of the core primary combustion zone 114. The diffuser 122 receives airflow from the compressor section (not shown) of the engine and provides a flow of compressed air to the combustor 112. The diffuser 122 provides the flow of compressed air to the shroud 120 of the swirler 124. The air flows through an outer passage 126 and an inner passage 128.

[0030] Figure 2 and Figure 3 is a schematic representation of a liner for a combustor according to an embodiment of the present disclosure. Figure 2 , a side perspective view 210 schematically illustrates a dilution passage 211 extending through a combustion liner for a combustor. Figure 3 , reference numeral 220 indicates a display Figure 2 The dilution channel 211 has a geometric structure formed by joining the exemplary first geometric structure and the exemplary second geometric structure (or physically joining two adjacent entities end to end so that they are fused into one entity). Figure 2 and Figure 3 A first geometric structure, embodied as a plurality of discrete holes 212 , and a second geometric structure, embodied as an annular groove 214 extending through the combustor liner, are joined to form the dilution passage 211 .

[0031] The discrete holes 212 and the annular groove 214 are connected at predetermined relative positions. Figure 2 and Figure 3 , the discrete holes 212 are positioned at the front or upstream, and the annular groove 214 is positioned at the rear or downstream. The discrete holes 212 have a semicircular cross-section.

[0032] In the connecting geometry of the dilution channel 211, the first dilution air flow 213 passing through the discrete holes 212 and the second dilution air flow 215 passing through the annular groove 214 are combined into a combined dilution air flow 217. Further, the combined dilution air flow 217 is injected into the Figure 1 The primary combustion zone 114 of the burner 112 is formed to achieve a predetermined combustion state of the burner 112 .

[0033] The combined dilution air flow 217 improves multiple desired combustion conditions of the combustor. Since the second dilution air flow 215 is downstream of the first dilution air flow 213, the second dilution air flow 215 provides hydraulic support for the first dilution air flow 213, improving the jet penetration in the process. The combined dilution air flow 217 reduces Figure 1 The temperature in the core primary combustion zone 114 of the combustor 112 is reduced, and the nitrogen oxides (NO x ) emission levels comply with regulatory guidelines. Further, the air split ratio or distribution or portion of the first dilution air flow 213 and the second dilution air flow 215 in the combined dilution air flow 217 is adjusted to reduce the temperature in the core primary combustion zone 114. In addition, the portion of the second dilution air flow 215 of the combined dilution air is kept closer to the liner around the circumference of the liner and maintains a lower liner temperature behind the combined dilution structure.

[0034] The combined dilution air flow 217 facilitates rapid quenching and rapid mixing of the first dilution air flow 213 and the second dilution air flow 215 with the many combustion products in the core primary combustion zone 114 of the combustor 112. The increased mixing results in a uniform temperature distribution within the core primary combustion zone 114 of the combustor 112 and further results in a combustor liner temperature that conforms to the reference combustor liner temperature.

[0035] Figure 4 shows an embodiment of the present invention Figure 2 Schematic representation of a mirrored version of the dilution channel 211. Figure 4 , reference numeral 230 indicates a top perspective view showing a schematic representation of a dilution passage 231 through the combustion liner of the combustor. The dilution passage 231 connects a series of discrete holes 232 with an annular slot 234 in front (upstream) of the discrete holes 232. Within the connecting geometry of the dilution passage 231, a first dilution air flow 233 passing through the discrete holes 232 is combined with a second dilution air flow 235 passing through the annular slot 234 to form a combined dilution air flow 237. Further, the combined dilution air flow is injected into Figure 1 The primary combustion zone 114 of the burner 112 is formed to achieve a predetermined combustion state of the burner 112 .

[0036] refer to Figure 5 , reference numeral 240 indicates Figure 4 A side perspective view of the dilution channel 231. The first dilution air flow 233 passes through the discrete holes 232, and the second dilution air flow 235 passes through the annular groove 234. Figure 5In the embodiment shown in FIG. 2 , the second dilution air flow 235 is upstream of the first dilution air flow 233 , so the second dilution air flow 235 provides a hydraulic shield for the first dilution air flow 233 , improving jet penetration during processing.

[0037] refer to Figures 1 to 5 The burner 112 ( Figure 1 )'s core primary combustion zone 114 ( Figure 1 ). Specifically, by merging the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the low velocity of the combustion products generally associated with a dilution configuration having only discrete dilution holes is enhanced. Furthermore, by merging the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the high penetration of the dilution air generally associated with a dilution configuration having only an annular dilution passage is further enhanced.

[0038] Furthermore, the burner 112 is improved by merging the first dilution air flow (213, 233) and the second dilution air flow (215, 235) into a combined dilution air flow (217, 237) in the dilution passage (211, 231). Figure 1 )'s core primary combustion zone 114 ( Figure 1 ) in the core primary combustion zone 114. Specifically, by combining the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the core primary combustion zone 114 ( Figure 1 ) localization of high temperatures near the outer periphery of the annular dilution passage. Further, by merging the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the core primary combustion zone 114 ( Figure 1 ) localization of high temperature near the central part.

[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 combined dilution air flow (217, 237) in the dilution passage (211, 231). Figure 1 ) in the core primary combustion zone 114 ( Figure 1 ) within NO xSpecifically, by combining the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the core primary combustion zone 114 ( Figure 1 ) near the outer periphery of the high NO x Further, by combining the first dilution air flow and the second dilution air flow into a combined dilution air flow within the dilution passage, the dilution emissions generally associated with dilution configurations having only annular dilution passages are reduced. Figure 1 The high NO near the central portion of the core primary combustion zone 114 x emission.

[0040] Figure 6 A schematic top perspective view of a liner 310 for a combustor is shown. Figure 7 Shows Figure 6 Schematic bottom perspective view of liner 310. Figure 6 and 7 The liner 310 has a liner body 309, a first surface 351 on a hot side 353 of the liner 310, and a second surface 355 on a cold side 357 of the liner 310. A dilution passage 311 can extend through the liner 310 from the cold side 357 to the hot side 353. The dilution passage 311 connects a plurality of discrete dilution holes 312 with an annular groove 314. That is, the dilution passage 311 is formed by a plurality of discrete dilution holes 312 that extend circumferentially around the liner 310 and are connected to an annular groove 314 that extends circumferentially around the liner 310. Although a single dilution passage 311 is shown, multiple dilution passages 311 can be repeated along the axial length of the liner 310.

[0041] Continue to refer Figure 6 and Figure 7 In the connected geometry of the dilution passage 311, the first dilution air flow 313 passing through the discrete dilution holes 312 is combined with the second dilution air flow 315 passing through the annular groove 314 to form a combined dilution air flow 317. The combined dilution air flow 317 is injected into the combustor 112 ( Figure 1 )'s core primary combustion zone 114 ( Figure 1 ) to reach the burner 112 ( Figure 1 ) of the predetermined combustion state.

[0042] The dilution channel 311 includes a protruding dilution insert 316, also referred to as a fence 316. The fence 316 has a thickness 352. The fence 316 faces toward the burner (such as Figure 1The fence 316 extends radially inwardly from the centerline of the combustor 112 of FIG. 31. The fence may be continuous in the circumferential direction from a first distal side of the liner 310 to a second distal side of the liner 310. The fence 316 extends radially inwardly between the annular groove 314 and the discrete dilution holes 312. The fence 316 is a full-length fence that extends from and connects to the discrete dilution holes 312 and reaches the combustor 112 ( FIG. Figure 1 )'s core primary combustion zone 114 ( Figure 1 ). That is, the fence 316 extends along the entire length of the body 307 of the discrete dilution hole 312. The fence 316 extends into the hot side 353 of the liner 310. The annular groove 314 is positioned forward of the fence 316. That is, the annular groove 314 is axially upstream of the fence 316. The discrete dilution holes 312 are positioned aft of the fence 316. That is, the discrete dilution holes 312 are axially downstream of the fence 316. Positioning the discrete dilution holes 312 behind (e.g., behind or downstream of) the fence 316 improves the performance of the combustor 112 ( Figure 1 )'s core primary combustion zone 114 ( Figure 1 ) in the combined dilution air stream 317. The fence 316 further helps increase the penetration of the first dilution air stream 313 and the second dilution air stream 315 to improve the turbulence level, thereby achieving uniform mixing of the dilution air with the primary zone products, resulting in uniform temperatures within the combustor and reduced NO x Horizontal. The fence centerline offset distance 354 defined between the fence axis 371 and the discrete hole insert centerline 373 can be between zero and three times the thickness 352 of the fence 316. The fence axis 371 can be defined along the frontmost surface 375 of the fence 316. The discrete hole insert centerline 373 can be an axis extending through the center point of a complete circle of discrete dilution holes 312. An angle θ 356 defined between the fence 316 and the discrete dilution holes 312 can vary from zero to fifty degrees. Angle θ 356 is defined by the fence axis 371 and the discrete hole insert centerline 373.

[0043] Figure 8 A schematic top perspective view of the liner 330 is shown. The liner 330 is Figure 6 and 7 The liner 310 is identical to that described and has a liner body 309. However, instead of having a body 307 ( Figure 7 ) In the case of a combined fence 316, the fence 336 is only partially connected to a portion of the discrete dilution hole 332. That is, the body of the discrete dilution hole 332 only partially extends along the length of the full-length fence 316. Due to the partial extension of the body, the body is Figure 8 For example, the body 307 of the discrete dilution hole ( Figure 6) can extend a distance unequal to the length of the fence 316. In this way, the body 307 ( Figure 6 ) may terminate before the fence 316 (e.g., the distal surface of the discrete dilution hole body may not be aligned with the distal surface of the fence 316 and / or may end before the distal surface of the fence 316). Thus, the plurality of discrete dilution holes may terminate on the hot side of the liner body (e.g., as Figure 6 The first surface 351 shown may not extend radially inward from the hot side of the liner toward the combustor axis.

[0044] The fence 316 and the fence 336 may each have a height 362. The height 362 may extend from the first surface 351 of the hot side 353 of the combustion liner to the trailing edge 337 of the fence 316 and the fence 336. The height 362 may be 0.1 to 10 times the diameter of the discrete dilution hole 312.

[0045] The bridge structure 323 may connect the discrete holes 312 to the annular groove 314 to allow control of the dilution gap between the annular groove 314 and the discrete holes 312. The bridge structure 323 may be connected to the front face of the liner forming the annular groove 314 (e.g., Figure 9 In some examples, the bridge structure 323 can be welded to the annular groove 214. The bridge structure 323 can support and control the dilution gap. Although not shown, a bridge structure similar to the bridge structure 323 can be provided relative to the annular groove 214. Figures 1 to 5 In the lining described.

[0046] Figures 6 to 8 Any example can be compared with Figures 6 to 8 Any or all example combinations of .

[0047] Figure 9 A schematic side cross-sectional view of the dilution passage 411 of the combustion liner 442 is shown. The combustion liner 442 may be Figure 2 The combustion liner is the same or similar. Figure 9 , the side view 440 schematically shows the dilution channel 411, which can be connected to Figure 2Dilution channel 411 extends through a combustion liner 442 of the combustor. Combustion liner 442 can be an inner or outer liner of the combustion chamber. Dilution channel 411 has a geometric structure formed by connecting a series of discrete dilution holes 444, an annular dilution slot 454, and a fence 416. The fence 416 can be any fence described herein. The cross-section of each discrete dilution hole 444 can be semicircular. For example, in a top view of the discrete dilution holes 444, the geometry 450 of the discrete dilution holes 444 can be semicircular. 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 annular dilution slot 454 can have a front face 458 and a rear face 459.

[0048] Continue to refer Figure 9 , the centerline 446 of the discrete dilution hole 444 is parallel to the centerline 456 of the annular dilution slot 454. The front face 458 of the annular dilution slot 454 merges with and is aligned with each diameter of the discrete dilution hole 444, which may have a semicircular geometry. Thus, the centerline 446 of the discrete dilution hole 444 is aligned with the front face 458 of the annular dilution slot 454 at an axial position of the front face 458 of the annular dilution slot 454, as shown in the top view. Furthermore, ten to ninety percent of the total flow area of ​​the dilution passage 411 is occupied by the discrete dilution holes 444, and the remainder of the total flow area is occupied by the annular dilution slot 454.

[0049] Figure 10 A schematic side cross-sectional view of the dilution passage 431 of the combustion liner 462 is shown. The combustion liner 462 may be Figure 2 The combustion liner is the same or similar. Figure 10 , side view 460 schematically shows dilution channel 431, which can be connected to Figure 2 Dilution passage 431 extends through the combustion liner 462 of the combustor. Dilution passage 411 has a geometric structure formed by connecting a series of discrete dilution holes 464, annular dilution slot 474, and fence 416. The cross-section of each discrete dilution hole 464 can be semicircular. For example, in a top view of the discrete dilution holes 464, the geometric structure 470 of the discrete dilution holes 464 can be semicircular. The centerline of the circle formed by the two semicircles can be the centerline 466 of each discrete dilution hole 464. That is, the axis extending through the center of the diameter of the discrete dilution hole 464 is aligned with the centerline 466. The annular dilution slot 474 can have a front face 478 and a rear face 479.

[0050] Continue to refer Figure 10, the centerline 466 of the discrete dilution hole 464 is parallel to the centerline 476 of the annular dilution slot 474. Further, the centerline 466 of the discrete dilution hole 464 is aligned with the rear face 479 of the annular dilution slot 474 at an axial position of the rear face 479 of the annular dilution slot 474.

[0051] Figure 11 A schematic side cross-sectional view of the dilution passage 511 of the combustion liner 522 is shown. The combustion liner 522 may be Figure 2 The combustion liner is the same or similar. Figure 11 , the side view 520 schematically shows the dilution channel 511, which can be connected to Figure 2 The dilution passage 511 extends through the combustion liner 522 of the combustor. The dilution passage 511 has a geometric structure formed by connecting a series of discrete dilution holes 524, an annular dilution slot 534, and a fence 516. The fence 516 can be any fence described herein. The cross-section of each discrete dilution hole 524 can be semicircular. For example, in a top view of the discrete dilution holes 524, the geometric structure 530 of the discrete dilution holes 524 can be semicircular. The centerline of the circle formed by the two semicircles can be the centerline 526 of each discrete dilution hole 524. That is, the axis extending through the center of the diameter of the discrete dilution hole 524 is aligned with the centerline 526. The annular dilution slot 534 can have a front face 538 and a rear face 539.

[0052] Continue to refer Figure 11 , the centerline 526 of the discrete dilution hole 524 is parallel to the centerline 536 of the annular dilution slot 534. Further, the centerline 526 of the discrete dilution hole 524 is rearward of the rear face 539 of the annular dilution slot 534 at an axial position of the rear face 539 of the annular dilution slot 534. The offset 532 measured between the centerline 526 of the discrete dilution hole 524 and the front face 538 of the annular dilution slot 534 is between zero and 0.3 times the diameter D of the discrete dilution hole 524.

[0053] Figure 12 A schematic side cross-sectional view of the dilution passage 531 of the combustion liner 542 is shown. The combustion liner 542 may be Figure 2 The combustion liner is the same or similar. Figure 12 , side view 540 schematically shows dilution channel 531, which can be connected to Figure 2The dilution passage 531 extends through the combustion liner 542 of the combustor. The dilution passage 531 has a geometric structure formed by connecting a series of discrete dilution holes 544, an annular dilution slot 554, and a fence 516. The cross-section of each discrete dilution hole 544 can be semicircular. For example, in a top view of the discrete dilution holes 544, the geometric structure 550 of the discrete dilution holes 544 can be semicircular. The centerline of the circle formed by the two semicircles can be the centerline 546 of each discrete dilution hole 524. That is, the axis extending through the center of the diameter of the discrete dilution hole 544 is aligned with the centerline 546. The annular dilution slot 554 can have a front face 558 and a rear face 559.

[0054] Continue to refer Figure 12 , the centerline 546 of the discrete dilution hole 544 is parallel to the centerline 556 of the annular dilution slot 554. Further, the centerline 546 of the discrete dilution hole 544 is forward of the front face 558 of the annular dilution slot 534 at an axial position of the front face 558 of the annular dilution slot 554. The offset 552 measured between the centerline 546 of the discrete dilution hole 544 and the front face 558 of the annular dilution slot 534 is between zero and one times the diameter D of the discrete dilution hole 544.

[0055] Figure 13 A schematic side cross-sectional view 560 of a first dilution passage 551 through an outer liner 562 of a combustor and a second dilution passage 561 through an inner liner 582 of the combustor is shown, according to an embodiment of the present disclosure. The first dilution passage 551 has a geometry formed by joining a series of discrete dilution holes 564, an annular dilution slot 574, and a fence 516. The centerline 566 of the discrete dilution hole 564 is parallel to the centerline 576 of the annular dilution slot 574 and is aligned with the front face 578 of the annular dilution slot 574 at an axial position at the front face 578 of the annular dilution slot 574. The second dilution passage 561 has a geometry formed by joining a series of discrete dilution holes 584, an annular dilution slot 594, and a fence 516. The centerline 586 of the discrete dilution hole 584 is parallel to the centerline 596 of the annular dilution slot 594 and is aligned with the front face 598 of the annular dilution slot 594 at an axial position at the front face 598 of the annular dilution slot 594. The offset 580 measured between the centerline 566 of the discrete dilution hole 564 on the outer liner 562 and the centerline 586 of the discrete dilution hole 584 on the inner liner 582 is between zero and + / - six times the diameter of the discrete dilution hole 564 or 584 .

[0056] Figure 14A schematic side cross-sectional view 620 of a dilution channel 611 of a combustion liner 622 is shown. Dilution channel 611 has a geometric structure formed by connecting a series of discrete dilution holes 624, annular dilution slots 634, and fences 616. Fences 616 can be any fence described herein. The centerline 626 of the discrete dilution holes 624 is parallel to the centerline 636 of the annular dilution slots 634. The centerline 626 of the discrete dilution holes 624 and / or the centerline 636 of the annular dilution slots 634, i.e., the flow direction of the discrete and annular flows, can be tilted at an angle θ 632, defined relative to an axis 630 orthogonal to the combustion liner 622. Angle θ can range from negative sixty degrees (forward tilt) to positive sixty degrees (rearward tilt). The centerline 626 of the discrete dilution holes 624 can be orthogonal to the centerline 636 of the combustion liner 622 and the annular dilution slots 634 tilted at angle θ, and vice versa. Although shown aligned with centerline 636, centerline 626 may be aligned with respect to Figures 9 to 13 The description of is offset in any way from the previous description.

[0057] Figure 15 and 16 Each shows a burner such as burner 112 ( Figure 1 ) is a schematic top view of the dilution channels of an exemplary inner and outer liner of a combustor having a liner structure similar to that of FIG. A schematic outline of the dilution holes of the outer liner is shown as being positioned over the dilution holes of the inner liner. That is, when the liner is viewed from a top view, the outlines of the dilution holes of the inner and outer liners may appear as follows: Figure 15 or any one of 16.

[0058] For example, Figure 15 A top view 640 of an outer liner 642 and an inner liner 652 is shown. The outer liner 642 has a series of outer liner discrete dilution holes, including outer liner discrete dilution holes 644 and outer liner discrete dilution holes 646. While two outer liner discrete dilution holes are shown, more may be provided. The inner liner 652 has a series of inner liner discrete dilution holes, including inner liner discrete dilution holes 654 and inner liner discrete dilution holes 656. While two inner liner discrete dilution holes are shown, more may be provided.

[0059] The outer liner discrete dilution holes 644 and the outer liner discrete dilution holes 646 can be directly opposite or can be staggered at an angle to the inner liner discrete dilution holes 654 and the inner liner discrete dilution holes 656. In this manner, when the series of outer liner discrete dilution holes and inner liner discrete dilution holes are axially aligned, the inner liner discrete dilution holes 654 are circumferentially between the outer liner discrete dilution holes 644 and the outer liner discrete dilution holes 646. The inner liner discrete dilution holes 656 can be located between the outer liner discrete dilution holes 646 and an adjacent outer liner discrete dilution hole (not shown). Each inner liner discrete dilution hole can be midway between adjacent outer liner discrete dilution holes.

[0060] Although shown and described as being staggered, other offsets between the outer liner discrete dilution holes 644 and 646 and the inner liner discrete dilution holes 654 and 656 are contemplated. For example, Figure 16 A top view 660 of an outer liner 662 and an inner liner 672 is shown. The outer liner 662 has a series of outer liner discrete dilution holes, including outer liner discrete dilution holes 664 and outer liner discrete dilution holes 666. While two outer liner discrete dilution holes are shown, more may be provided. The inner liner 672 has a series of inner liner discrete dilution holes, including inner liner discrete dilution holes 674 and inner liner discrete dilution holes 676. While two inner liner discrete dilution holes are shown, more may be provided. Figure 16 The top lining can be Figure 15 The lining is the same, however, with Figure 15 In contrast, inner liner discrete dilution holes 674 and inner liner discrete dilution holes 676 can be positioned circumferentially closer to outer liner discrete dilution holes 664 and outer liner discrete dilution holes 666, respectively. That is, the distance between an inner liner discrete dilution hole, such as inner liner discrete dilution hole 674, and a first outer liner discrete dilution hole, such as outer liner discrete dilution hole 666, can be less than the distance between the same inner liner discrete dilution hole (e.g., inner liner discrete dilution hole 674) and an outer liner discrete dilution hole adjacent to the first outer liner discrete dilution hole (e.g., outer liner discrete dilution hole 666). This relationship can be reversed, and any distance between dilution holes can be set.

[0061] In addition to or as an alternative to the two positions described above, other positioning of the inner liner discrete dilution holes relative to the outer liner discrete dilution holes is possible. Furthermore, the outer liner discrete holes can be aligned with the center of the cyclone or angled relative to the cyclone. The angle can depend on the number of discrete holes in each cyclone cup liner.

[0062] Figure 17A schematic flow chart of a method 700 for flowing a dilution flow through a combustor liner according to an embodiment of the present disclosure is shown. The method 700 includes providing a combustor having (i) a combustor liner body with a hot side and a cold side and (ii) a core primary combustion zone of the combustor, as shown in step 712. The method 700 also includes extending a dilution passage having a connecting geometry through the combustor liner body, as shown in step 714. The method 700 further includes flowing a first dilution air from the cold side to the hot side of the combustor liner through the dilution passage, as shown in step 716. The method also includes flowing a second dilution air from the cold side to the hot side of the combustor liner through the dilution passage, as shown in step 718.

[0063] The combined geometry of the dilution passage is formed by joining a first geometric structure and a second geometric structure at predetermined relative positions, such that the first dilution air and the second dilution air are combined within the combined geometry of the dilution passage. The first geometric structure can be positioned forward or upstream, while the second geometric structure is positioned aft or downstream. The second geometric structure can be positioned forward or upstream, while the first geometric structure is positioned aft or downstream.

[0064] The first geometric structure includes at least one discrete hole, and the second geometric structure includes at least one discrete annular groove. The size of the discretely positioned discrete features (such as holes and annular grooves) can vary circumferentially or have a specific pattern along the circumference. The discrete holes can have a semicircular cross-section, or a triangular cross-section, or a semi-elliptical cross-section with a major axis in the transverse direction (e.g., racetrack-shaped), or a semi-elliptical cross-section with a major axis in the axial direction (e.g., racetrack-shaped), or any combination thereof.

[0065] The dilution channels' interconnected geometry can repeat in a predetermined pattern, such as in a generally circumferential linear array or in a staggered array relative to the combustor. The dilution channels can be oriented at varying angles relative to the combustor in a predetermined orientation. The dilution channels can be arranged orthogonal to the axis of the liner, or they can be inclined at an angle to the axis of the swirler.

[0066] Method 700 further includes providing a third geometric structure and coupling the third geometric structure to the first geometric structure such that the first dilution air flows through the third geometric structure. The third geometric structure is a protruding dilution insert extending into the hot side of the liner. The protruding dilution insert can be a full-length insert, a corner-cut (or beveled) dilution insert, or a fence. The length of the protruding dilution insert can be longer on one side than on the other side such that the weighted area decreases from one side to the other. The exact dimensions of the protruding dilution insert can be adjusted for efficient performance.

[0067] The method 700 further includes combining the first dilution air flow and the second dilution air flow to provide a combined dilution air flow to increase mixing with the plurality of combustion products in the primary combustion zone of the combustor, as shown in step 722. The method 700 also includes injecting the combined dilution air flow into the combustor to achieve a predetermined combustion state of the combustor, as shown in step 724.

[0068] 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 combustion zone and the secondary combustion zone of the burner. The predetermined combustion state of the burner includes a burner outlet temperature profile that conforms to the reference temperature profile. The predetermined combustion state of the burner also includes rapid quenching and rapid and increased mixing of the first dilution air flow and the second dilution air flow with the 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 distribution or shares) of the first dilution air flow and the second dilution air flow.

[0069] The disclosed liner for a gas turbine engine combustor provides a dilution passage having a joining geometry that combines a first dilution air flow and a second dilution air flow into a combined dilution air flow.

[0070] When the second dilution air flow is downstream of the first dilution air flow, the second dilution air flow can provide hydraulic support for the first dilution air flow. When the second dilution air flow is upstream of the first dilution air flow, the second dilution air flow can provide hydraulic shielding for the first dilution air flow. In both cases, the hydraulic support and / or hydraulic shielding can penetrate between the scattered airflows of the first dilution air flow and enhance the penetration of the first dilution air flow into the core primary combustion zone of the combustor.

[0071] The second dilution air flow is configured to flow over the trailing edge of the fence to form a film of air flow, thereby preventing the trailing edge of the fence from overheating and / or oxidation due to high core combustor temperatures. The second dilution air flow is configured to flow over the front surface of the fence to form a film of air flow that cools the fence. The fence of the present disclosure protects the rear or upstream side of the discrete dilution inserts from the high temperatures of the combustor by directing flow in the center of the combustor.

[0072] The combined dilution air flow increases the rapid quenching and mixing of the dilution air flow with the multiple combustion products in the primary combustion zone of the combustor, resulting in a uniform temperature distribution within the primary combustion zone of the combustor and a combustor outlet temperature profile that meets the reference temperature profile. The combined dilution air flow reduces nitrogen oxides (NO x ) emission levels.

[0073] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0074] A liner for a combustor in a gas turbine engine. The liner comprises: a liner body having a cold side and a hot side; and a dilution passage having a connecting geometry extending through the liner body. The dilution passage is configured to (a) merge a first dilution air flow flowing from the cold side to the hot side through the dilution passage and a second dilution air flow flowing from the cold side to the hot side through the dilution passage into a combined dilution air flow, and (b) inject the combined dilution air flow into a core primary combustion zone of the combustor to achieve a predetermined combustion state of the combustor. The connecting geometry comprises: a plurality of discrete dilution holes through which the first dilution air flow flows; annular grooves through which the second dilution air flow flows; and a fence connected to the plurality of discrete dilution holes and extending radially inward from the hot side of the liner body toward the central axis of the combustor. The fence is configured to help the first dilution air flow and the second dilution air flow penetrate into the core primary combustion zone of the combustor.

[0075] A liner according to the preceding clause, wherein the second dilution air flow provides hydraulic support for the first dilution air flow and the fence provides hydraulic shielding for the first dilution air flow, such that the second dilution air flow and the fence enhance penetration of the first dilution air flow into the core primary combustion zone of the combustor.

[0076] The liner of any of the preceding clauses, wherein the first dilution air flow generates turbulence in the core primary combustion zone of the combustor.

[0077] A liner according to any of the preceding clauses, wherein the second dilution air flow is configured to flow over the trailing edge of the fence so as to form a film of air flow to prevent the trailing edge of the fence from overheating and oxidation due to high core combustor temperatures, and the second dilution air flow is configured to flow over the front surface of the fence so as to form a film of air flow that cools the fence.

[0078] A liner according to any of the preceding clauses, wherein the predetermined combustion state of the combustor has (i) a reduced temperature in the core primary combustion zone of the combustor, (ii) a compliant NOx emission level, (iii) a uniform temperature distribution within the core primary combustion zone of the combustor, (iv) a combustor outlet temperature profile that conforms to a reference temperature profile, (v) increased mixing of the first dilution air flow and the second dilution air flow with multiple combustion products in the core primary combustion zone of the combustor, (vi) rapid quenching and rapid mixing of the first dilution air flow and the second dilution air flow with multiple combustion products in the core primary combustion zone of the combustor, (vii) a predetermined air split ratio of the first dilution air flow and the second dilution air flow, or (viii) any combination thereof.

[0079] The liner of any of the preceding clauses, wherein each discrete dilution hole of the plurality of discrete dilution holes has a semicircular cross-section, an elliptical cross-section, or a racetrack-shaped cross-section.

[0080] The liner of any of the preceding clauses, wherein the first dilution air flow is ten to ninety percent of the total flow through the dilution passage.

[0081] A liner according to any of the preceding clauses, wherein the first dilution air flow is located axially rearward of the second dilution air flow.

[0082] A liner according to any of the preceding clauses, wherein the first dilution air flow is located axially forward of the second dilution air flow.

[0083] A liner according to any of the preceding clauses, wherein the plurality of discrete dilution holes extend circumferentially in series around the liner body and are coupled to the annular groove.

[0084] A liner as in any preceding clause, wherein the fence extends radially inwardly between the annular groove and the plurality of discrete dilution holes.

[0085] The liner of any of the preceding clauses, wherein the fence has a height defined between a surface of the hot side of the liner body and a trailing edge of the fence, wherein the height is equal to a height of a body of the plurality of discrete dilution holes.

[0086] A liner according to any of the preceding clauses, wherein the fence has a height, the height being defined between a surface of the hot side of the liner body and a trailing edge of the fence, wherein the height is 0.1 to 10 times the diameter of a discrete dilution hole of the plurality of discrete dilution holes.

[0087] A liner as described in any preceding clause, wherein the fence has a height that extends beyond a height of the body of the plurality of discrete dilution holes.

[0088] A liner according to any of the preceding clauses, wherein the plurality of discrete dilution holes terminate at the hot side of the liner body and do not extend radially inwardly therefrom.

[0089] A liner according to any of the preceding clauses, wherein the annular groove is positioned axially forward of the fence, the fence being positioned axially forward of the plurality of discrete dilution holes such that the position of the fence allows mixing of the first and second dilution air flows.

[0090] The liner of any of the preceding clauses, wherein the fence is angled relative to a centerline of the plurality of discrete dilution holes, and wherein the angle is between zero and fifty degrees.

[0091] A liner according to any of the preceding clauses, wherein the fence is continuous in a circumferential direction from a first distal side of the liner body to a second distal side of the liner body.

[0092] The liner of any of the preceding clauses, wherein the fence has a thickness, the thickness being defined between an axial forward side of the fence and an axial rearward side of the fence, and wherein the fence is offset from a centerline of the plurality of discrete dilution holes by a distance that is between zero and three times the thickness.

[0093] A liner according to any of the preceding clauses, wherein the fence is offset in an axial forward direction of the plurality of discrete dilution holes.

[0094] Although the foregoing description is directed to preferred embodiments, it is to be noted that other variations and modifications are apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, features described with respect to one embodiment may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

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

2. The lining according to claim 1, characterized in that The second dilution air flow provides hydraulic support for the first dilution air flow, and the fence provides hydraulic shielding for the first dilution air flow, such that the second dilution air flow and the fence enhance penetration of the first dilution air flow into the core primary combustion zone of the combustor.

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

4. The lining according to claim 1, characterized in that wherein the second dilution air flow is configured to flow over the trailing edge of the fence so as to form a film of air flow to prevent the trailing edge of the fence from overheating and oxidation due to high core combustor temperatures, and the second dilution air flow is configured to flow over the front surface of the fence so as to form a film of air flow that cools the fence.

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

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

7. The lining according to claim 1, wherein The first dilution air flow is ten percent to ninety percent of the total flow through the dilution passage.

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

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

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

11. The liner according to claim 1, wherein The fence extends radially inwardly between the annular groove and the plurality of discrete dilution holes.

12. The liner according to claim 1, wherein The fence has a height defined between a surface of the hot side of the liner body and a trailing edge of the fence, wherein the height is equal to a height of a body of the plurality of discrete dilution holes.

13. The liner according to claim 1, wherein The fence has a height defined between a surface of the hot side of the liner body and a trailing edge of the fence, wherein the height is 0.1 to 10 times a diameter of a discrete dilution hole of the plurality of discrete dilution holes.

14. The liner according to claim 1, wherein Wherein the fence has a height that extends beyond a height of the bodies of the plurality of discrete dilution holes.

15. The liner according to claim 1, wherein wherein the plurality of discrete dilution holes terminate at the hot side of the liner body and do not extend radially inwardly therefrom.

16. The liner according to claim 1, wherein The annular groove is positioned axially forward of the fence, and the fence is positioned axially forward of the plurality of discrete dilution holes such that the position of the fence allows mixing of the first dilution air flow and the second dilution air flow.

17. The liner according to claim 1, wherein Wherein the fence is angled relative to a centerline of the plurality of discrete dilution holes, and wherein the angle is between zero and fifty degrees.

18. The liner according to claim 1, wherein The fence is continuous in a circumferential direction from a first distal side of the liner body to a second distal side of the liner body.

19. The liner according to claim 1, wherein wherein the fence has a thickness defined between an axial front side of the fence and an axial rear side of the fence, and wherein the fence is offset from a centerline of the plurality of discrete dilution holes by a distance that is zero to three times the thickness.

20. The liner according to claim 19, wherein Wherein the fence is offset in an axial forward direction of the plurality of discrete dilution holes.

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