Adaptive trapped vortex combustor

Abstract

An adaptive trapped vortex combustor for a gas turbine engine includes a combustion chamber, a fuel injector, and one or more slots. The combustion chamber is defined by an outer liner, an inner liner, and a dome, and includes a primary combustion zone within the combustion chamber that defines a vortex chamber for trapping a vortex having a volume therein, a secondary combustion zone within the combustion chamber, and an opening from the primary combustion zone to the secondary combustion zone. The fuel injector injects fuel into the primary combustion zone. The one or more slots provide a flow of air to the primary combustion zone and / or the secondary combustion zone. The adaptive trapped vortex combustor is characterized as being controllable such that a residence time of the fuel in the vortex chamber can be controlled based on operating conditions of the gas turbine engine.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to a trapped vortex combustor. In particular, the present disclosure relates to an adaptive trapped vortex combustor for a gas turbine engine. BACKGROUND

[0002] A gas turbine engine includes a compressor for compressing air, which is mixed with fuel and ignited in a combustor to produce combustion gases. The combustion gases flow to a turbine, which extracts energy to drive a shaft, powering the compressor and producing output power. One type of combustor is a trapped vortex combustor, which traps air in a vortex to stabilize combustion. BRIEF DESCRIPTION OF DRAWINGS

[0003] The features and advantages of the present disclosure will be apparent from the following detailed description in conjunction with the various figures presented, in which like reference numbers generally refer to the same, similar, and / or analogous elements throughout.

[0004] Figure 1 A schematic cross-sectional view of a gas turbine engine taken along a centerline of the engine is shown in accordance with an embodiment of the present disclosure.

[0005] Figure 2 A schematic cross-sectional view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0006] Figure 3 A schematic view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0007] Figure 4 A schematic view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0008] Figure 5 A schematic view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0009] Figure 6 A schematic view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0010] Figure 7A A schematic view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0011] Figure 7B A schematic view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0012] Figure 7CA schematic view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0013] Figure 8 A schematic view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0014] Figure 9 A schematic view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0015] Figure 10A A partial schematic cross-sectional view of a portion of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0016] Figure 10B A partial schematic cross-sectional view of a portion of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0017] Figure 11A A schematic cross-sectional view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0018] Figure 11B A schematic cross-sectional view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0019] Figure 11C A schematic cross-sectional view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0020] Figure 11D A schematic cross-sectional view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0021] Figure 12A A schematic cross-sectional view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0022] Figure 12B A schematic cross-sectional view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0023] Figure 12C A schematic cross-sectional view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure.

[0024] Figure 12D A schematic cross-sectional view of a trapped vortex combustor for a gas turbine engine is shown in accordance with an embodiment of the present disclosure. DETAILED DESCRIPTION

[0025] The features, advantages, and embodiments of the present disclosure are illustrated or otherwise apparent through consideration of the following detailed description, accompanying drawings, and claims. Further, it is to be understood that the following detailed description is exemplary and intended to provide further explanation of the disclosure without limiting the scope of the disclosure as claimed.

[0026] Various embodiments are discussed in detail below. While specific implementations are discussed, this is simply for illustration. Those skilled in the relevant art will recognize that other components and configurations can be utilized without departing from the spirit and scope of this disclosure.

[0027] The terms "forward" and "aft" refer to relative positions within a gas turbine engine and refer to the normal operating attitude of the gas turbine engine. For example, for a gas turbine engine, forward refers to a position closer to the engine inlet and aft refers to a position closer to the engine nozzle or exhaust.

[0028] The adaptive trapped vortex combustor of the present disclosure, also referred to as an ultra-compact combustor, provides a variable volume combustor and / or a variable flow combustor that provides optimization over a range of operating conditions. The adaptive trapped vortex combustor can allow for changes or movement of the outer liner, the inner liner, the dome, the fuel injector, the slot, the cone in the slot, or any combination thereof to provide variable volume and / or variable flow. Actuators can passively and / or actively control the adaptability of the adaptive trapped vortex combustor.

[0029] Reference Figure 1 The gas turbine engine 10 has a longitudinal, axial centerline 12 extending therethrough along an axial direction A. The gas turbine engine 10 defines a radial direction R extending perpendicularly from the centerline 12, a circumferential direction C extending perpendicularly to the centerline 12 and the radial direction R (shown as in and out of the page in Figure 1 The gas turbine engine 10 can be, for example and without limitation, a gas turbine engine, a turbofan engine, an open rotor engine, a turboshaft engine, a turbojet engine, or a turboprop configuration engine, including marine and industrial turbine engines and auxiliary power units.

[0030] The gas turbine engine 10 includes a core engine 14 and a fan section 16 upstream therefrom. The core engine 14 generally includes an outer casing 18 defining an annular inlet 20. In addition, the outer casing 18 can also enclose and support a low pressure compressor 22 for increasing the pressure of air entering the core engine 14 to a first pressure level. A multi-stage high pressure compressor 24 can then receive pressurized air from the low pressure compressor 22 and further increase the pressure of such air. Pressurized air exiting the high pressure compressor 24 can then be directed to a combustor 26 where fuel is injected into the pressurized air stream, and the resulting mixture is combusted within the combustor 26. High energy combustion products 64 are directed from the combustor 26 along a hot gas path of the gas turbine engine 10 to a high pressure turbine 28 for driving the high pressure compressor 24 via a high pressure shaft 30 (also referred to as a shaft 30), and then to a low pressure turbine 32 for driving the low pressure compressor 22 and the fan section 16 via a low pressure shaft 34 that is generally coaxial with the high pressure shaft 30. After driving each of the high pressure turbine 28 and the low pressure turbine 32, the combustion products 64 can be exhausted from the core engine 14 via an exhaust nozzle 36 to provide propulsive jet thrust.

[0031] In addition, as shown, Figure 1 The fan section 16 of the gas turbine engine 10 includes a rotatable axial fan rotor 38 enclosed by an annular nacelle 42. In certain embodiments, the low pressure shaft 34 can be directly connected to the fan rotor 38 or rotor disk 40, such as in a direct drive configuration. In alternative configurations, in an indirect drive or geared drive configuration, the low pressure shaft 34 can be connected to the fan rotor 38 via a reduction device, such as a reduction gear box. Such reduction devices can be included between any suitable shafts / spools within the gas turbine engine 10 as needed or desired. In addition, the fan rotor 38 and / or rotor disk 40 can be enclosed or formed as part of a fan hub 44.

[0032] The nacelle 42 can be supported relative to the core engine 14 by a plurality of substantially radially extending, circumferentially spaced outlet guide vanes 46. Accordingly, the nacelle 42 can enclose the fan rotor 38 and a plurality of fan blades 48. Each fan blade 48 can extend between a root and a tip in a radial direction R relative to the centerline 12. A downstream section 50 of the nacelle 42 can extend over an outer portion of the core engine 14 to define a secondary air flow or bypass conduit 52 that provides additional propulsive jet thrust.

[0033] During operation of the gas turbine engine 10, an initial air flow 54 can enter the gas turbine engine 10 through an inlet 56 of the nacelle 42. The initial air flow 54 then passes through the fan blades 48 and divides into a first compressed air flow 58 that moves through the bypass duct 52 and a second compressed air flow 60 (also referred to as a core air flow 60) 58 that enters the low pressure compressor 22. The pressure of the core air flow 60 is then increased and enters the high pressure compressor 24 as an air flow 62. After mixing with fuel and combusting within the combustor 26, the combustion products 64 exit the combustor 26 and flow through the high pressure turbine 28. Thereafter, the combustion products 64 flow through the low pressure turbine 32 and exit the exhaust nozzle 36 to provide thrust for the gas turbine engine 10.

[0034] Referring to Figure 2 , the combustor 26 of the gas turbine engine 10 can be a trapped vortex combustor 100. The trapped vortex combustor 100 defines a combustion chamber 102 that can include a primary combustion zone 104 and a secondary combustion zone 106. A fuel injector 108 deposits a flow of liquid or gaseous fuel F F into the combustion chamber 102 to define the primary combustion zone 104 within the combustion chamber 102. The fuel injector 108 can extend radially inwardly from an outer liner 112 of the trapped vortex combustor 100. The primary combustion zone 104 defines an annular trapped vortex 110 in a primary cavity 120 (also referred to as a vortex cavity 120). The secondary combustion zone 106 defines a secondary cavity 122. The trapped vortex combustor 100 includes the outer liner 112, an inner liner 114, and a dome 116.

[0035] Still referring to Figure 2 , a first air flow F A1 may enter the primary cavity 120 of the combustion chamber 102 via a first slot or passage 160. The first air flow F A1 may enter the primary cavity 120 from an axially forward end of the vortex cavity 120 of the trapped vortex combustor 100. That is, the first air flow F A1 may enter proximate the dome 116. A second air flow F A2 may enter the vortex cavity 120 of the combustion chamber 102 via a second slot or passage 162. The second air flow F A2 may enter the primary cavity 120 from an axially aft end of the vortex cavity 120 of the trapped vortex combustor 100. That is, the first air flow F A2 may enter through the outer liner 212. The first air flow F A1 and the second air flow F A2 may enter the vortex cavity 120 on axially opposite sides of the vortex cavity 120. A third air flow F A3 may enter the secondary cavity 122 through the dome 116. For example, the third air flow F A3 may enter through a third slot or diffuser 164 located in or at the dome 116.

[0036] Fuel Flow F F and airflow F A1 F A2 and F A3 Combustion products can be combined in a known manner to burn in the vortex burner 100. The combustion products can flow through the vortex burner 100 to the high-pressure turbine 28.

[0037] The vortex burner disclosed herein can be an adaptive vortex burner and can have a variable volume vortex chamber and / or variable flow rate. The volume and / or flow rate can be increased or decreased to any power condition. The variable volume and / or variable flow rate can adapt to any power condition between minimum ignition conditions and maximum power conditions. Adapting to variable volume and / or variable flow rate can balance efficiency, smoke, NOx, lean blowout, reignition, and / or pressure drop.

[0038] Figures 3 to 6 Various adaptive vortex burners, which can be burner 26 and / or vortex burner 100, are shown. About Figures 3 to 6 The adaptive vortex burner described in the paper allows for variable volume in the vortex cavity. Figures 3 to 6 Any adaptive vortex burner described herein, and any of its individual components or features, may be combined with other vortex burners described herein. Figures 3 to 6 The movement described herein is the relative motion of the moving component with respect to the outer shell and / or inner shell of the adaptive vortex burner. Figures 3 to 6 The movement described herein can be driven actively and / or passively.

[0039] Figure 3 A schematic diagram of an adaptive vortex burner 200 is shown. The adaptive vortex burner 200 defines a combustion chamber 202, which may include a primary combustion zone 204 and a secondary combustion zone 206. A fuel injector 208 deposits a flow into the combustion chamber 202 to define the primary combustion zone 204 within the combustion chamber 202. The fuel injector 208 may extend radially inward from an outer liner 212 of the adaptive vortex burner 200. The primary combustion zone 204 defines a primary cavity 220, also referred to as a vortex cavity 220. The secondary combustion zone 206 defines a secondary cavity 222. The adaptive vortex burner 200 includes an outer liner 212, an inner liner 214, and a dome 216.

[0040] Figure 3The vortex cavity 220 can have a variable volume. That is, the outer liner 212 can move axially to adjust the volume of the vortex cavity 220. For example, the outer liner 212 can move a distance 250 from a first outer liner position 212a to a second outer liner position 212b. Thus, the volume of the vortex cavity 220 can increase and / or decrease by the volume present in the space of the distance 250. The volume can increase as the outer liner 212 moves toward the second outer liner position 212b. The volume can decrease as the outer liner 212 moves toward the first outer liner position 212a. The axial aft end 218 of the outer liner 212 can be allowed to move relatively to the high pressure turbine 28. Due to the outer liner 212 being allowed to move axially, the opening 224 of the vortex cavity 220 can be a variable opening. That is, as the outer liner 212 moves between the first outer liner position 212a and the second outer liner position 212b (any point in between), the opening 224 changes. The opening 224 gets larger as the outer liner 212 moves toward the second outer liner position 212b. The opening 224 gets smaller as the outer liner 212 moves toward the first outer liner position 212a.

[0041] Figure 4 A schematic view of an adaptive trapped vortex combustor 300 is shown. The adaptive trapped vortex combustor 300 defines a combustion chamber 302 that can include a primary combustion zone 304 and a secondary combustion zone 306. A fuel injector 308 deposits a stream into the combustion chamber 302 to define the primary combustion zone 304 within the combustion chamber 302. The fuel injector 308 can extend radially inward from an outer liner 312 of the adaptive trapped vortex combustor 300. The primary combustion zone 304 defines a primary cavity 320, also referred to as a vortex cavity 320. The secondary combustion zone 306 defines a secondary cavity 322. The adaptive trapped vortex combustor 300 includes an outer liner 312, an inner liner 314, and a dome 316. The outer liner 312 includes a first outer liner portion 326 and a second outer liner portion 328.

[0042] Figure 4The vortex cavity 320 can be variable in volume. That is, the first outer liner portion 326 can move axially to adjust the volume of the vortex cavity 320. For example, the first outer liner portion 326 can move a distance 350 from the first outer liner position 326a to the second outer liner position 326b. Thus, the volume of the vortex cavity 320 can increase and / or decrease by the volume present in the space of the distance 350. The volume can increase as the first outer liner portion 326 moves toward the second outer liner position 326b. The volume can decrease as the first outer liner portion 326 moves toward the first outer liner position 326a. The axial aft end 318 of the second outer liner portion 328 of the outer liner 312 can be allowed to move relatively to the high pressure turbine 28. Because the first outer liner portion 326 of the outer liner 312 is allowed to move axially and the second outer liner portion 328 is fixed, the opening 324 of the vortex cavity 320 can be a fixed opening. That is, as the first outer liner portion 326 of the outer liner 312 moves between the first outer liner position 326a and the second outer liner position 326b (and any point in between), the opening 224 remains unchanged or fixed.

[0043] Figure 3 An example of an adaptive trapped vortex combustor 200 is shown having a variable volume (e.g., the volume of the vortex cavity 220 can increase and / or decrease) and having a variable opening (e.g., the opening 224 can increase and / or decrease as the volume of the vortex cavity 220 increases and / or decreases). On the other hand, Figure 4 An example of an adaptive trapped vortex combustor 300 is shown having a variable volume (e.g., the volume of the vortex cavity 320 can increase and / or decrease) and having a fixed opening (e.g., the opening 224 does not change as the volume of the vortex cavity 220 changes).

[0044] Thus, as Figure 3 and 4 shown, although the primary vortex zone can change in volume, the outlet of the primary zone can be allowed to move with the volume or can be fixed. In the example of a fixed outlet Figure 4 , the area between the primary zone outlet (e.g., the opening 324) and the secondary zone (e.g., the secondary combustion zone 306) remains relatively constant. However, some area changes can occur due to thermal growth differences between the portions. In addition, Figure 3 and 4 the dome can be movable relative to the diffuser (e.g., the slot 164 of Figure 2 ). As the dome is in the first dome position and the second dome position and positions in between, the distribution of the passage or pressure recovery between the dome and the diffuser can change.

[0045] Figure 5 and 6Alternative ways of achieving a change in volume of the vortex cavity are shown. As described with respect to Figure 4 the outer liner 312 can be moved. In examples of Figure 5 the dome can be moved. In examples of Figure 6 the dome and the inner liner can be moved. Figures 3 to 6 Any or all of the ways of achieving a change in volume described in

[0046] Referring first to Figure 5 , the adaptive trapped vortex combustor 400 defines a combustion chamber 402 that can include a primary combustion zone 404 and a secondary combustion zone 406. A fuel injector 408 deposits a fuel stream into the combustion chamber 402 to define the primary combustion zone 404 within the combustion chamber 402. The fuel injector 408 can extend radially inward from an outer liner 412 of the adaptive trapped vortex combustor 400. The primary combustion zone 404 defines a primary cavity 420, also referred to as a vortex cavity 420. The secondary combustion zone 406 defines a secondary cavity 422. The adaptive trapped vortex combustor 400 includes the outer liner 412, an inner liner 414, and a dome 416.

[0047] Figure 5 The vortex cavity 420 of the adaptive trapped vortex combustor 400 of may be variable in volume. That is, the dome 416 can be moved axially to adjust the volume of the vortex cavity 420. For example, the dome 416 can be moved a distance 450 from a first dome position 416a to a second dome position 416b. Thus, the volume of the vortex cavity 420 can increase and / or decrease by the volume present in the space of the distance 450. The volume can increase as the dome 416 moves toward the second dome position 416b. The volume can decrease as the dome 416 moves toward the first dome position 416a.

[0048] Figure 3 Because the dome 416 is allowed to move axially, the opening of the vortex cavity 420 can be a variable opening, such as described with respect to Figure 4 the outer liner of

[0049] Referring to Figure 6The adaptive trapped vortex combustor 500 defines a combustion chamber 502, which can include a primary combustion zone 504 and a secondary combustion zone 506. A fuel injector 508 deposits a fuel stream into the combustion chamber 502 to define the primary combustion zone 504 within the combustion chamber 502. The fuel injector 508 can extend radially inward from an outer liner 512 of the adaptive trapped vortex combustor 500. The primary combustion zone 504 defines a primary cavity 520, also referred to as a vortex cavity 520. The secondary combustion zone 506 defines a secondary cavity 522. The adaptive trapped vortex combustor 500 includes an outer liner 512, an inner liner 514, and a dome 516.

[0050] Figure 6 The vortex cavity 520 can be variable in volume. That is, the dome 516 and the inner liner 514 can move axially to adjust the volume of the vortex cavity 520. For example, the dome 516 and the inner liner 514 can move a distance 550 from a first dome position 516a and a first inner liner position 514a, respectively, to a second dome position 516b and a second inner liner position 514b, respectively. Thus, the volume of the vortex cavity 520 can increase and / or decrease by a volume present in the space of the distance 550. The volume can increase as the dome 516 and the inner liner 514 move toward the second dome position 516b and the second inner liner position 514b, respectively. The volume can decrease as the dome 516 and the inner liner 514 move toward the first dome position 516a and the first inner liner position 514a, respectively.

[0051] Because the dome 516 and the inner liner 514 are allowed to move axially, the opening of the vortex cavity 520 can be a variable opening, for example, as described with respect to the outer liner of Figure 3 Alternatively, the dome 516 and / or the inner liner 514 can be formed such that the opening is fixed, for example, as described with respect to the outer liner of Figure 4

[0052] Thus, as described with respect to the outer liner of Figure 3 and 4 the outer liner can translate to change the vortex primary zone volume (e.g., the volume of the vortex cavity) while the position of the dome and the inner liner remain fixed relative to the combustor shell. Additionally, as described with respect to the outer liner of Figure 5 and 6 the dome can translate to change the vortex primary zone volume while the outer liner remains fixed relative to the combustor shell. In some examples, the inner liner can be allowed to translate with the dome ( Figure 6 ) or can remain fixed relative to the combustor shell ( Figure 5 ). "Fixed" is a relative term meaning mounted to the inner shell and / or the outer shell, although one skilled in the art will recognize that some movement will occur due to thermal growth and / or mechanical loading (e.g., pressure drop across the liner or mechanical loading through the engine). ​

[0053] The dome near the diffuser outlet can also be used to change the pressure recovery distribution between the dome and the outer / inner channels, as a way to change the flow of the burner.

[0054] Figures 7A to 7C The fuel injector is shown in Figures 3 to 6 as well as Figures 8 to 10B The position within the adaptive vortex burner. Therefore, Figures 7A to 7C The location of the fuel injector can be included in any or all of the vortex burners described herein. For example, in Figure 7A In this combustion chamber 600a, the burner 600a includes a fuel injector 608a located at its front end. That is, the fuel injector 608a injects fuel in front of the burner 600a. The fuel injector 608a can be located within or at the dome 616. The fuel injector 608a can inject fuel into the primary combustion zone 604 of the combustion chamber 602 in the axial direction. Figure 7B In this combustion chamber 600b, the burner 600b includes a fuel injector 608b located within an outer liner 612. The fuel injector 608b injects fuel outside the burner 600b. The fuel injector 608b can be located within or at the outer liner 612. The fuel injector 608b can inject fuel radially into the primary combustion zone 604 of the combustion chamber 602. Figure 7C In the combustion chamber 600c, the burner 600c includes a fuel injector 608c located at the rear end of the primary combustion zone 604 of the combustion chamber 602 of the burner 600a. The fuel injector 608c injects fuel from behind the burner 600c. The fuel injector 608c may be located within or at the outer liner 612. The fuel injector 608c can inject fuel into the primary combustion zone 604 of the combustion chamber 602 in the axial direction.

[0055] Therefore, as Figures 7A to 7C As shown, the fuel injector can be mounted in front of, on top of, and / or behind the burner, and can be further attached to the burner housing. In examples of top mounting (e.g., Figure 7B A slot of sufficient length is used to allow for a fixed fuel injector position that is not actuated relative to the dome, although, as mentioned and known in the prior art, some relative movement may occur due to changes in thermal growth.

[0056] Although Figures 3 to 6 A variable volume burner is described. Figures 8 to 10B The variable flow rate from the vortex cavity is described. About Figures 8 to 10B Any adaptive vortex burner described herein, and any of its individual components or features, may be combined with other vortex burners described herein. Figures 3 to 6 Any variable volume burner can be paired withFigures 8 to 10B any of the variable flow combustor combinations to provide an adaptive trapped vortex combustor including variable volume and variable flow.

[0057] Referring first to Figure 8 The adaptive trapped vortex combustor 700 can include a plurality of slots or chutes that allow air to flow into the combustion chamber 702. For example, a first chute 760 can enter the combustion chamber 702 at a front side of the first cavity 720 (also referred to as the vortex cavity 720) of the combustion chamber 702. A second chute 762 can enter the combustion chamber 702 at a rear side of the vortex cavity 720 of the combustion chamber 702. A third chute 764 can enter the secondary cavity 722 at a front side of the secondary cavity 722. The fuel injector 708 injects fuel into the vortex cavity 720.

[0058] Figure 8 Further shown are support arms 766 and cones 768 directed toward each of the first chute 760, the second chute 762, and the third chute 764. The support arms 766 are coupled to the cones 768 to support them. The cones 768 can be flow actuation devices. The cones 768 can be actuated by the respective support arms 766 to change the flow area through the first chute 760, the second chute 762, and / or the third chute 764. That is, the cones 768 can move linearly relative to the respective chutes to adjust the opening therein through which air can flow. One or more actuators 770 can be mounted in the housing 790. The one or more actuators 770 can be activated to actuate movement of the cones 768. The cones 768 can be actuated simultaneously and / or independently.

[0059] Although shown schematically as arrows and triangles, the cones 768 can allow flow therethrough such that air can flow therethrough and through the respective chutes. Although each chute including a cone 768 is shown and described, only one chute or a combination of chutes can include a cone 768.

[0060] The support arms 766 and the cones 768 can form a chute with a cone and / or a drive slot that traverses into and out of the respective chute (e.g., the first chute 760, the second chute 762, the third chute 764) to change the flow therethrough. In some examples, the cones 768 can be radial and / or axial flappers that can change the inlet blockage to the respective chutes. The support arms 766 and / or the cones 768 can be actively or passively actuated, similar to the liner actuation methods described with respect to Figures 11A to 12D

[0061] ​Although a cone 768 is shown, this is just one example, other methods or configurations to provide selective obstruction of the slot can include, but are not limited to, rotational obstruction and / or radial obstruction. For example, one such method can include a perforated plate in front of the drive hole that rotates to open or close the drive hole area. For example, another method can include a segment that translates radially to open and / or close the drive hole area.

[0062] Figure 9 10A and 10B show example structures that can implement selective air flow through a slot (as described with respect to Figure 8 In the burner 800 of Figure 9 , a first slot can allow flow into the primary combustion zone 804, as described with respect to the previous figures. The enlarged portion 890 shown in detail in Figure 10A and 10B includes a cone 868 that extends into the slot 860. The cone 868 can move between a first position 868a and a second position 868b to selectively control air flow through the slot 860. The cone 868 can have the profile of the outer liner 812 that is configured to translate relative to the slot 860. Although shown with respect to the slot 860, the cone 868 can be provided in other air slots in the burner.

[0063] As described above, the cone can be passively actuated. That is, conditions of the burner or operation of the engine can control movement of the cone. For example, in Figure 10A , the cone 868 can open as the vortex cavity volume increases. In Figure 10B , the cone 868 can open as the vortex cavity volume decreases. The slot and / or drive slot can be conical or can be translation of the profile of the liner. This can also achieve a varying flow rate that is proportional or inversely proportional to the cavity volume.

[0064] Figures 11A to 11D Various example actuation methods and locations that can be used for actuation of the outer liner, inner liner, dome, and / or slot as previously described herein are shown. For example, in Figure 11A , the actuator 970 can be mounted to the inner surface 980 at the front end 992 of the housing 990. In Figure 11B , the actuator 970 can be mounted to the outer surface 982 at the front end 992 of the housing 990. In Figure 11C , the actuator 970 can be mounted to the inner surface 980 at the rear end 994 of the housing 990. In Figure 11D ​In this embodiment, actuator 970 can be mounted to the outer surface 982 at the rear end 994 of housing 990. Although shown as being mounted to an outer liner, actuator 970 can be mounted to any feature described herein that is configured to move. Furthermore, actuator 970 can also be applied to housing 996 at any location.

[0065] Therefore, as Figures 11A to 11D As shown, the actuator can be mounted to the housing 990 and / or the inner housing 996, on the inner side (e.g., on the inner surface 980) or on the outer side (e.g., on the outer surface 982). The actuator 970 can be connected to the liner support arm. The actuator 970 can be independent. The actuator 970 can be driven by a single-point linkage. The actuator 970 can be mechanically geared by any suitable mechanism. The actuator 970 can be driven by fuel or oil hydraulic, electrical, mechanical, and / or magnetic means. The actuator 970 can be passively driven by a spring force driven by a pressure drop through the liner. The actuator 970 can be actively or passively driven.

[0066] Figures 12A to 12D Various exemplary actuation methods and locations are shown that can be used for actuating outer liners, inner liners, domes, and / or grooves as previously described herein. For example, in Figure 12A and 12B In this context, the actuator 1070, also known as the support 1070, can be mounted to the inner surface 1080 of the housing 1090. Figure 12A In this case, the installation can be located at the front end 1092 of the burner, and... Figure 12B In this configuration, the installation can be located at the rear end 1094 of the burner. The support member 1070 can be an integral support actuation member. Figure 12C and 12D In this configuration, the outer lining support 1070a can be mounted to the inner surface 1080 of the outer shell 1090, and the inner lining support 1070b can be mounted to the inner surface 1096 of the inner lining 1098. Figure 12C In the middle, the installation can be at the front end 1092, and... Figure 12D In this case, the installation can be performed at backend 1094.

[0067] The support member 1070, including the outer lining support member 1070a and the inner lining support member 1070b, can be an actuator driven by a shape memory material or a material with different thermal growth characteristics, such as, but not limited to, shape memory alloys. Therefore, the support member 1070 can be implemented as a compact actuator. Figures 11A to 11D ) and / or through the material of the support arm ( Figures 12A to 12D). Actuation of the memory material or materials with different thermal growth characteristics can be controlled by relative growth between the inner liner to the inner shell and / or the outer liner to the outer shell and / or relative growth between the shells and the liners, which results in relative movement and, thus, a change in the primary combustion chamber (e.g., vortex cavity) volume.

[0068] The volume can be increased to accommodate lower power conditions and maximize fuel residence time in the vortex to optimize reignition and lean blowout capability. Increasing the volume can also optimize low power efficiency without changing the pressure drop in the combustor. The adaptive trapped vortex combustor of the present disclosure can have a variable flow vortex cavity or secondary zone that can be adapted to low power conditions to maximize fuel residence time in the vortex to optimize reignition and lean blowout capability. This increases the pressure drop in the combustor.

[0069] The volume can be decreased to accommodate high power conditions and minimize residence time in the vortex cavity. This can minimize NOx emissions and smoke without changing the pressure drop in the combustor. The adaptive trapped vortex combustor of the present disclosure can have a variable flow vortex cavity or secondary zone that can be adapted to high power conditions to minimize NOx emissions and smoke while also optionally reducing the pressure drop in the combustor.

[0070] In some examples, the adaptive trapped vortex combustor of the present disclosure allows the vortex primary zone to have a variable geometry in which the volume of the vortex is variable in order to optimize combustor performance over a wide range of operating conditions without affecting combustor pressure loss or split.

[0071] In some examples, the adaptive trapped vortex combustor of the present disclosure allows a variable geometry that allows variable split in the combustor without changing the combustor volume in order to optimize combustor performance over a wide range of operating conditions with the option of affecting or not affecting pressure loss through the combustor.

[0072] In some examples, the adaptive trapped vortex combustor of the present disclosure allows a variable geometry that is capable of changing both volume and split. The adaptive trapped vortex combustor that provides a variable volume combustor allows performance optimization over a range of operating conditions. For example, the adaptive trapped vortex combustor can provide a variable volume that optimizes combustor volume operability (e.g., ignition and / or blowout conditions at lower power conditions, and NOx and / or smoke conditions at high power conditions). The adaptive trapped vortex combustor of the present disclosure that provides a variable flow combustor allows performance optimization over a range of operating conditions (e.g., combustor split and internal split operability (e.g., ignition and blowout) at lower power conditions, and NOx and / or smoke conditions at high power conditions).

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

[0074] According to one aspect of the present disclosure, an adaptive trapped vortex combustor for a gas turbine engine includes a combustion chamber defined by an outer liner, an inner liner, and a dome, the combustion chamber including a primary combustion zone within the combustion chamber defining a vortex cavity for trapping a vortex having a volume therein, a secondary combustion zone within the combustion chamber, and an opening from the primary combustion zone to the secondary combustion zone. The combustion chamber includes a fuel injector configured to inject fuel into the primary combustion zone, and one or more slots configured to provide a flow of air to the primary combustion zone, the secondary combustion zone, or both the primary combustion zone and the secondary combustion zone. The adaptive trapped vortex combustor is characterized by a feature that is controllable such that a residence time of the fuel in the vortex cavity is controllable based on operating conditions of the gas turbine engine.

[0075] The adaptive trapped vortex combustor according to any of the preceding clauses, wherein the feature controls a volume of the vortex cavity, a flow rate of air through the one or more slots, or a size of the opening, or any combination thereof.

[0076] The adaptive trapped vortex combustor according to any of the preceding clauses, wherein the feature is the dome, the dome being movable between a first dome position and a second dome position such that the volume of the vortex cavity is a variable volume.

[0077] The adaptive trapped vortex combustor according to any of the preceding clauses, wherein the feature is the inner liner and the dome, the inner liner and the dome being movable together between a first inner liner position and a second inner liner position and between a first dome position and a second dome position, respectively, such that the volume of the vortex cavity is a variable volume.

[0078] The adaptive trapped vortex combustor according to any of the preceding clauses, wherein the one or more slots include a diffuser, wherein the feature is the dome, the dome being movable between a first dome position relative to the diffuser and a second dome position relative to the diffuser, and wherein a passage between the dome and the diffuser changes between the first dome position and the second dome position.

[0079] The adaptive trapped vortex combustor according to any of the preceding clauses, wherein the fuel injector is located on a front side of the vortex cavity and is configured to inject fuel into the primary combustion zone in an axial direction.

[0080] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the fuel injector is located at a back side of the vortex chamber and is configured to inject fuel into the primary combustion zone in an axial direction.

[0081] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the fuel injector is located at an outer liner radially outward of the vortex chamber and is configured to inject fuel into the primary combustion zone in a radial direction.

[0082] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the feature is a cone located in each of the one or more slots, the cone being capable of controlling the flow of air into and out of the respective one or more slots to control the flow of air through the respective one or more slots.

[0083] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the feature is actively actuated or passively actuated.

[0084] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the feature controls the volume, the volume increasing to increase a residence time of the fuel in the vortex chamber and the volume decreasing to decrease the residence time of the fuel in the vortex chamber.

[0085] The adaptive trapped vortex combustor of any of the preceding clauses, wherein a pressure drop in the combustor does not change with control of the feature.

[0086] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the feature is the outer liner, the outer liner being capable of moving between a first outer liner position and a second outer liner position such that the volume of the vortex chamber is a variable volume.

[0087] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the opening is variable such that a size of the opening changes with changes in the variable volume.

[0088] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the opening is fixed such that a size of the opening is fixed with changes in the variable volume.

[0089] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the outer liner comprises a first outer liner portion and a second outer liner portion, the first outer liner portion moving to change the volume of the vortex chamber and the second outer liner portion being fixed such that a size of the opening is fixed.

[0090] The adaptive trapped vortex combustor of any of the preceding clauses, further comprising an actuator to control movement of the feature.

[0091] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the actuator is driven hydraulically by fuel or oil, electrically, mechanically, and / or magnetically.

[0092] The adaptive trapped vortex combustor of any of the preceding clauses, wherein the actuator is a memory material or a material having different thermal growth characteristics than a component in which the actuator is installed.

[0093] According to an aspect of the disclosure, a gas turbine engine includes an outer casing and an inner casing, and an adaptive trapped vortex combustor installed within the outer casing and the inner casing. The adaptive trapped vortex combustor includes a combustion chamber defined by an outer liner, an inner liner, and a dome, the combustion chamber having a primary combustion zone within the combustion chamber defining a vortex cavity for a trapped vortex having a volume therein, a secondary combustion zone within the combustion chamber, and an opening from the primary combustion zone to the secondary combustion zone. The adaptive trapped vortex combustor includes a fuel injector configured to inject fuel into the primary combustion zone, and one or more slots configured to provide a flow of air to the primary combustion zone, the secondary combustion zone, or both the primary combustion zone and the secondary combustion zone. The gas turbine engine includes a turbine coupled downstream of the adaptive trapped vortex combustor. A feature of the adaptive trapped vortex combustor is controllable such that a residence time of the fuel in the vortex cavity can be controlled based on operating conditions of the gas turbine engine.

[0094] The gas turbine engine of the preceding clause, wherein the feature controls the volume of the vortex cavity, a flow rate of air through the one or more slots, a size of the opening, or any combination thereof.

[0095] The gas turbine engine of any of the preceding clauses, wherein the feature controls the volume of the vortex cavity, a flow rate of air through the one or more slots, or a size of the opening, or any combination thereof.

[0096] The gas turbine engine of any of the preceding clauses, wherein the feature is the dome, the dome being movable between a first dome position and a second dome position such that the volume of the vortex cavity is a variable volume.

[0097] The gas turbine engine of any of the preceding clauses, wherein the feature is the inner liner and the dome, the inner liner and the dome being movable together between a first inner liner position and a second inner liner position and between a first dome position and a second dome position, respectively, such that the volume of the swirl cavity is a variable volume.

[0098] The gas turbine engine of any of the preceding clauses, wherein the one or more slots comprise a diffuser, wherein the feature is the dome, the dome being movable between a first dome position relative to the diffuser and a second dome position relative to the diffuser, and wherein a passage between the dome and the diffuser changes between the first dome position and the second dome position.

[0099] The gas turbine engine of any of the preceding clauses, wherein the fuel injector is located at a forward side of the swirl cavity and is configured to inject fuel into the primary combustion zone in an axial direction.

[0100] The gas turbine engine of any of the preceding clauses, wherein the fuel injector is located at an aft side of the swirl cavity and is configured to inject fuel into the primary combustion zone in an axial direction.

[0101] The gas turbine engine of any of the preceding clauses, wherein the fuel injector is located at an outer liner radially outward of the swirl cavity and is configured to inject fuel into the primary combustion zone in a radial direction.

[0102] The gas turbine engine of any of the preceding clauses, wherein the feature is a taper located in each of the one or more slots, the taper being controllable to control the flow of air into and out of the respective one or more slots to control the flow of air through the respective one or more slots.

[0103] The gas turbine engine of any of the preceding clauses, wherein the feature is actively actuated or passively actuated.

[0104] The gas turbine engine of any of the preceding clauses, wherein the feature controls the volume, the volume being increased to increase the residence time of the fuel in the swirl cavity and decreased to decrease the residence time of the fuel in the swirl cavity.

[0105] The gas turbine engine of any of the preceding clauses, wherein a pressure drop in the combustor does not change with control of the feature.

[0106] The gas turbine engine of any of the preceding clauses, wherein the feature is the outer liner, the outer liner being movable between a first outer liner position and a second outer liner position such that the volume of the swirl cavity is a variable volume.

[0107] The gas turbine engine of any of the preceding clauses, wherein the opening is variable such that a size of the opening changes as the variable volume changes.

[0108] The gas turbine engine of any of the preceding clauses, wherein the opening is fixed such that a size of the opening is fixed as the variable volume changes.

[0109] The gas turbine engine of any of the preceding clauses, wherein the outer liner comprises a first outer liner portion and a second outer liner portion, the first outer liner portion moving to change the volume of the swirl cavity and the second outer liner portion being fixed such that the size of the opening is fixed.

[0110] The gas turbine engine of any of the preceding clauses, further comprising an actuator to control movement of the feature.

[0111] The gas turbine engine of any of the preceding clauses, wherein the actuator is driven by fuel or oil hydraulics, electricity, mechanically, and / or magnetically.

[0112] The gas turbine engine of any of the preceding clauses, wherein the actuator is a material that is a memory material or has different thermal growth characteristics than a component on which the actuator is mounted.

[0113] While the foregoing description has been made in terms of preferred embodiments, 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 the disclosure. Furthermore, features described in conjunction with one embodiment can be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. An adaptive trapped vortex combustor for a gas turbine engine characterized by, The adaptive trapped vortex combustor comprises: (A) a combustion chamber defined by an outer liner, an inner liner, and a dome, the combustion chamber comprising: (a) a primary combustion zone within the combustion chamber, the primary combustion zone defining a vortex cavity for a trapped vortex, the vortex cavity having a volume therein; (b) a secondary combustion zone within the combustion chamber; (c) an opening from the primary combustion zone to the secondary combustion zone; (B) a fuel injector configured to inject fuel into the primary combustion zone; and (C) one or more slots configured to provide an air flow to the primary combustion zone, the secondary combustion zone, or both the primary combustion zone and the secondary combustion zone, wherein the adaptive trapped vortex combustor is characterized by a feature that is controllable such that a residence time of the fuel in the vortex cavity is controllable based on an operating condition of the gas turbine engine, wherein the operating condition is a power condition of the gas turbine engine, and wherein the feature controls the volume of the vortex cavity, a flow rate of the air through the one or more slots, or a size of the opening, or any combination thereof.

2. The adaptive trapped vortex combustor of claim 1 wherein, wherein the feature is the dome, the dome being movable between a first dome position and a second dome position such that the volume of the vortex cavity is a variable volume.

3. The adaptive trapped vortex combustor of claim 1 wherein, wherein the feature is the inner liner and the dome, the inner liner and the dome being movable together between a first inner liner position and a second inner liner position and between a first dome position and a second dome position, respectively, such that the volume of the vortex cavity is a variable volume.

4. The adaptive vortex combustor of claim 1, wherein, wherein the one or more slots comprise a diffuser, wherein the feature is the dome, the dome being movable between a first dome position relative to the diffuser and a second dome position relative to the diffuser, and wherein a passage between the dome and the diffuser changes between the first dome position and the second dome position.

5. The adaptive vortex combustor of claim 1, wherein, wherein the fuel injector is located at a front side of the vortex cavity and is configured to inject fuel into the primary combustion zone in an axial direction.

6. The adaptive vortex combustor of claim 1, wherein, wherein the fuel injector is located at a back side of the vortex cavity and is configured to inject fuel into the primary combustion zone in an axial direction.

7. The adaptive vortex combustor of claim 1, wherein, wherein the fuel injector is located at the outer liner radially outward of the vortex cavity and is configured to inject fuel into the primary combustion zone in a radial direction.

8. The adaptive vortex combustor of claim 1, wherein, wherein the feature is a taper located in each slot of the one or more slots, the taper being controllable to control the air flow in and out of the respective slot to control the air flow through the respective slot.

9. The adaptive vortex combustor of claim 1, wherein, wherein the feature is actively actuated or passively actuated.

10. The adaptive vortex combustor of claim 1, wherein, wherein the feature controls the volume, the volume increasing to increase the residence time of the fuel in the vortex cavity and the volume decreasing to decrease the residence time of the fuel in the vortex cavity.

11. The adaptive vortex combustor of claim 1, wherein, wherein a pressure drop in the adaptive trapped vortex combustor does not change with control of the feature. wherein the feature is a dome, the dome being movable between a first dome position and a second dome position such that the volume of the vortex cavity is a variable volume. wherein the feature is the inner liner and the dome, the inner liner and the dome being movable together between a first inner liner position and a second inner liner position and between a first dome position and a second dome position, respectively, such that the volume of the vortex cavity is a variable volume. wherein the one or more slots comprise a diffuser, wherein the feature is the dome, the dome being movable between a first dome position relative to the diffuser and a second dome position relative to the diffuser, and wherein a passage between the dome and the diffuser changes between the first dome position and the second dome position. wherein the fuel injector is located at a front side of the vortex cavity and is configured to inject fuel into the primary combustion zone in an axial direction. wherein the fuel injector is located at a back side of the vortex cavity and is configured to inject fuel into the primary combustion zone in an axial direction. wherein the fuel injector is located at the outer liner radially outward of the vortex cavity and is configured to inject fuel into the primary combustion zone in a radial direction. wherein the feature is a taper located in each slot of the one or more slots, the taper being controllable to control the air flow in and out of the respective slot to control the air flow through the respective slot. wherein the feature is actively actuated or passively actuated. wherein the feature controls the volume, the volume increasing to increase the residence time of the fuel in the vortex cavity and the volume decreasing to decrease the residence time of the fuel in the vortex cavity. wherein a pressure drop in the adaptive trapped vortex combustor does not change with control of the feature.

12. The adaptive vortex combustor of claim 1, wherein, wherein the feature is the outer liner, the outer liner being movable between a first outer liner position and a second outer liner position such that the volume of the vortex cavity is a variable volume.

13. The adaptive vortex combustor of claim 12, wherein, wherein the opening is variable such that a size of the opening changes as the variable volume changes.

14. The adaptive vortex combustor of claim 12, wherein, wherein the opening is fixed such that a size of the opening is fixed as the variable volume changes.

15. The adaptive vortex combustor of claim 12, wherein, wherein the outer liner includes a first outer liner portion and a second outer liner portion, the first outer liner portion being moved to change the volume of the vortex cavity and the second outer liner portion being fixed such that the size of the opening is fixed.

16. The adaptive vortex combustor of claim 1, wherein, further comprising an actuator to control movement of the feature.

17. The adaptive vortex combustor of claim 16, wherein, wherein the actuator is driven hydraulically by fuel or oil, electrically, mechanically, and / or magnetically.

18. The adaptive vortex combustor of claim 16, wherein, wherein the actuator is a memory material or a material having different thermal growth properties than a component on which the actuator is mounted.

19. A gas turbine engine characterized by, comprising: (A) an outer shell and an inner shell; (B) an adaptive trapped vortex combustor mounted within the outer shell and the inner shell, the adaptive trapped vortex combustor comprising: (a) a combustion chamber defined by an outer liner, an inner liner, and a dome, the combustion chamber having: (i) a primary combustion zone within the combustion chamber, the primary combustion zone defining a vortex cavity for trapping a vortex, the vortex cavity having a volume therein; (ii) a secondary combustion zone within the combustion chamber; (iii) an opening from the primary combustion zone to the secondary combustion zone; (b) a fuel injector configured to inject fuel into the primary combustion zone; and (c) one or more scoops configured to provide a flow of air to the primary combustion zone, the secondary combustion zone, or both the primary combustion zone and the secondary combustion zone; and (C) a turbine coupled downstream of the adaptive trapped vortex combustor, wherein a feature of the adaptive trapped vortex combustor is controllable such that a residence time of the fuel in the vortex cavity is controllable based on an operating condition of the gas turbine engine, wherein the operating condition is a power condition of the gas turbine engine, and wherein the feature controls the volume of the vortex cavity, a flow rate of the air through the one or more scoops, or a size of the opening, or any combination thereof.

Images