Burners and burners

Abstract

The present invention provides a burner and a burner that can flexibly cope with thermal deformation using a bellows while simultaneously suppressing damage to the bellows. The present invention provides a burner having a double-tube structure comprising an outer tube and an inner tube, wherein the inner tube is configured to include: a top-side support portion fixed to the outer tube, a base-side support portion fixed to the outer tube, a main body portion supported by the top-side support portion, a bellows located between the main body portion and the base-side support portion, and a partition member installed between the top-side support portion and the base-side support portion, wherein a second gap exists between the outer peripheral surface of the partition member and the inner peripheral surface of the outer tube, which is smaller than a first gap between the outermost peripheral surface of the bellows and the inner peripheral surface of the outer tube.

Description

Technical Field

[0001] The present invention relates to a burner and a combustor used in a gas turbine engine. Background Art

[0002] There is a burner used in a combustor of a gas turbine engine that uses a bellows to allow thermal deformation in the axial direction during operation of the gas turbine engine (Patent Document 1).

[0003] Prior art literature

[0004] Patent Literature

[0005] Patent Document 1: Japanese Patent Application Laid-Open No. 2016-99107 Summary of the Invention

[0006] Problems to be solved by the invention

[0007] During gas turbine engine operation, mechanical vibrations from the engine and combustion vibrations from the combustor are transmitted to the burner nozzle. This not only causes thermal deformation but also excitation of the burner nozzle. If a bellows made of a thin metal plate is used, it may interfere with surrounding structures and cause damage. Furthermore, the bellows itself deforms radially due to heat.

[0008] An object of the present invention is to provide a burner and a combustor that can flexibly cope with thermal deformation using a bellows and can suppress damage to the bellows.

[0009] Solutions to Problems

[0010] In order to achieve the above-mentioned object, the present invention provides a burner, which is a burner with a double tube structure having an outer tube and an inner tube, wherein the inner tube is constructed to include: a top side support portion, which is fixed to the outer tube; a base side support portion, which is fixed to the outer tube; a main body, which is supported by the top side support portion; a bellows, which exists between the main body and the base side support portion; and a partition member, which is installed at a position between the top side support portion and the base side support portion, and a second gap, which is smaller than the first gap between the outermost peripheral surface of the bellows and the inner peripheral surface of the outer tube, exists between the outer peripheral surface of the partition member and the inner peripheral surface of the outer tube.

[0011] Effects of the Invention

[0012] According to the present invention, it is possible to flexibly cope with thermal deformation using the bellows while suppressing damage to the bellows. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1This is a configuration example of a gas turbine plant to which the burner according to the first embodiment of the present invention is applied.

[0014] Figure 2 This is a cross-sectional view showing the detailed structure of the burner according to the first embodiment of the present invention.

[0015] Figure 3 This is a cross-sectional view showing an extracted inner cylinder included in the burner according to the first embodiment of the present invention.

[0016] Figure 4 yes Figure 2 An enlarged view of section IV in FIG.

[0017] Figure 5 This is an enlarged cross-sectional view showing a main part of a burner according to a second embodiment of the present invention.

[0018] Description of Reference Numerals

[0019] 3…burner, 31…pilot fuel nozzle, 32…main fuel nozzle, 36…outer tube, 36h…fuel flow path, 37…inner tube, 37a…top side support portion, 37b…base side support portion, 37c…main body portion, 37d…bellows, 37e…partition wall member, 39…sealing member, G1…first gap, G2…second gap. DETAILED DESCRIPTION

[0020] Hereinafter, embodiments of the present invention will be described using the drawings.

[0021] (First embodiment)

[0022] 1. Gas turbine equipment

[0023] Figure 1 This is a diagram showing a configuration example of a gas turbine plant to which the burner according to the first embodiment of the present invention is applied. Figure 1 The gas turbine equipment 1 shown is configured to include a compressor 2, a combustor 3, a gas turbine 4, a generator 6, and a starting motor 7. The compressor 2, the combustor 3, and the gas turbine 4 constitute a gas turbine engine that drives the generator 6.

[0024] The compressor 2 is started by a starting motor 7 and compresses air a1 drawn in from an air intake (not shown), generating high-pressure compressed air a2 and supplying it to the combustor 3. The combustor 3 mixes the compressed air a2 supplied from the compressor 2 with fuel and combusts the mixture, generating high-temperature combustion gas b1 and supplying it to the gas turbine 4. The gas turbine 4 is driven by the combustion gas b1 supplied from the combustor 3. The combustion gas b1 that drives the gas turbine 4 is discharged from the gas turbine 4 as exhaust gas b2. The generator 6 is driven by the rotational power obtained by the gas turbine 4 to generate electricity. In this embodiment, the compressor 2, the gas turbine 4, and the generator 6 are interconnected by a shaft 29.

[0025] 2. Burner

[0026] The combustor 3 includes an outer tube 10 , an inner tube 12 , an end cover 13 , a burner 8 , a main fuel system 26 , and a pilot fuel system 27 .

[0027] 2-1.Outer cylinder, inner cylinder, end cover

[0028] The inner cylinder 12 is positioned downstream of the burner 8 in the direction of flow of the combustion gas b1. The inner cylinder 12 is cylindrical and separates the compressed air a2 flowing in the outer annular flow path 24 (described later) from the combustion gas b1 flowing in the inner combustion chamber 5. The outer cylinder 10 is cylindrical and positioned to cover the outer circumference of the inner cylinder 12. The compressed air a2 supplied from the compressor 2 to the combustor 3 flows through the annular flow path 24, which has an annular cross section and is formed between the outer cylinder 10 and the inner cylinder 12. The end cover 13 is positioned downstream of the burner 8 in the direction of flow of the compressed air a2 flowing in the annular flow path 24, and closes one end of the outer cylinder 10 (the downstream end in the direction of flow of the compressed air a2 flowing in the annular flow path 24).

[0029] The compressed air a2 flowing through the annular flow path 24 provides convection cooling to the inner tube 12 from its outer circumferential surface. Furthermore, the inner tube 12 is provided with a plurality of air holes 25 on its wall surface. A portion of the compressed air a2 flowing through the annular flow path 24 flows into the inner tube 12 through the air holes 25 as cooling air a3, forming a thin film cooling film along the inner wall surface of the inner tube 12. The compressed air a2 that does not flow through the air holes 25 but flows through the annular flow path 24 is supplied to the burner 8 as combustion air a4. The combustion air a4 flowing into the burner 8 is injected into the combustion chamber 5 along with the fuel supplied to the burner 8 from the main fuel system 26, where it mixes with the fuel and burns.

[0030] 2-2. Burner

[0031] The burner 8 is configured to include a single pilot burner 30 (described later) disposed on the center line of the inner tube 12 , and a plurality of main burners 40 provided so as to surround the pilot burner 30 .

[0032] -Pilot burner-

[0033] The pilot burner 30 is configured to include a single pilot fuel nozzle 31, a plurality of main fuel nozzles 32, a fuel header (cavity) 33, and a swirler 34. The pilot burner 30 is fixed to the end cover 13 by bolts or the like.

[0034] The pilot fuel nozzle 31 supplies pilot fuel to the combustion chamber 5 . The pilot fuel can be oil fuel such as diesel, kerosene, or heavy oil A, or gas fuel such as natural gas or propane. The pilot fuel nozzle 31 is located on the center line of the inner tube 12 .

[0035] The main fuel nozzles 32 supply main fuel to the combustion chamber 5. In addition to natural gas and propane, gaseous fuels containing hydrogen and carbon monoxide, such as coke oven gas, refinery off-gas, and coal gasification gas, can be used as the main fuel. Multiple main fuel nozzles 32 are arranged to surround the pilot fuel nozzle 31 and are connected to a fuel manifold 33, which serves as a fuel distributor. The swirler 34 is provided with multiple air holes 35 corresponding to the main fuel nozzles 32. The main fuel is injected from each main fuel nozzle 32 toward the corresponding air hole 35, and the main fuel is ejected from each air hole 35 into the combustion chamber 5 along with the combustion air a4.

[0036] The detailed structure of the pilot burner 30 will be described later.

[0037] -Main burner-

[0038] Each main burner 40 is configured to include a plurality of main fuel nozzles 41 , fuel headers (cavities) 42 b and 42 b , and an air hole plate 43 .

[0039] A plurality of main fuel nozzles 41 are concentrically provided in each main burner 40. The plurality of annular rows of the concentric main fuel nozzles 41 are referred to as the first row, the second row, and the third row in order from the inner peripheral side.

[0040] The fuel headers 42a and 42b are fuel distributors and are supported by the end cover 13. The first row of main fuel nozzles 41 are connected to the inner circumferential fuel header 42a, while the second and third rows of main fuel nozzles 41 are connected to the outer circumferential fuel header 42b.

[0041] The air hole plate 43 is an annular plate having a plurality of air holes 44 and is located between the main fuel nozzles 41 and the combustion chamber 5. This air hole plate 43 is shared by each main burner 40 and has a plurality of air holes 44 in first to third rows corresponding to the main fuel nozzles 41 in the region constituting each main burner 40.

[0042] 2-3. Main fuel system

[0043] The main fuel system 26 is constructed from a fuel supply source 26a and fuel pipes 26b to 26e. Fuel pipe 26b has a fuel shutoff valve (on / off valve) 26f and extends from fuel supply source 26a. It branches into fuel pipes 26c to 26e downstream of fuel shutoff valve 26f. Fuel pipe 26c is connected to the fuel manifold 33. Fuel pipe 26d is connected to fuel manifold 42a. Fuel pipe 26e is connected to fuel manifold 42b. Fuel pipe 26c is equipped with a fuel flow control valve 26g, fuel pipe 26d is equipped with a fuel flow control valve 26h, and fuel pipe 26e is equipped with a fuel flow control valve 26i.

[0044] The main fuel supplied from fuel supply source 26a to fuel manifold 33 via fuel pipes 26b and 26c is distributed from fuel manifold 33 to each main fuel nozzle 32 and ejected from each main fuel nozzle 32 into combustion chamber 5. Similarly, the main fuel supplied from fuel supply source 26a to fuel manifolds 42a and 42b via fuel pipes 26b, 26d, and 26e is distributed from fuel manifolds 42a and 42b to each main fuel nozzle 41 and ejected from each main fuel nozzle 41 into combustion chamber 5. The flow rate of the main fuel through fuel pipe 26d is regulated by fuel flow control valve 26g. The flow rate of the main fuel through fuel pipe 26d is regulated by fuel flow control valve 26h. The flow rate of the main fuel through fuel pipe 26e is regulated by fuel flow control valve 26i. This fuel flow rate regulation controls the power generation of the gas turbine facility 1.

[0045] 2-4. Pilot fuel system

[0046] The pilot fuel system 27 includes a fuel supply source 27a and a fuel pipe 27b. The fuel pipe 27b has a fuel shutoff valve (on / off valve) 27c and a fuel flow control valve 27d, and connects the fuel supply source 27a to the pilot fuel nozzle 31. Pilot fuel from the fuel supply source 27a is supplied to the pilot fuel nozzle 31 via the fuel pipe 27b and ejected from the pilot fuel nozzle 31 into the combustion chamber 5. The flow rate of the pilot fuel is regulated by the fuel flow control valve 27d.

[0047] 3. Pilot burner

[0048] Figure 2 is a cross-sectional view showing the detailed structure of the pilot burner 30. Figure 3 This is a cross-sectional view showing the inner tube of the pilot burner 30 being extracted. Figure 4 yes Figure 2 An enlarged view of section IV in FIG. Figures 3 to 5 In the figure, the pilot fuel nozzle 31 is omitted for simplicity of the drawing.

[0049] As shown in these figures, the pilot burner 30 includes an outer cylinder 36 and an inner cylinder 37 in addition to the components already described. The pilot burner 30 has a double-tube structure composed of the outer cylinder 36 and the inner cylinder 37 .

[0050] -Outer barrel-

[0051] The outer cylinder 36 is the outer shell (body) of the pilot burner 30 , and is configured to include a body 36 a , a flange 36 b , and a fuel port 36 c .

[0052] The main body 36a of the outer tube 36 is cylindrical and contains a cylindrical space 36d inside, which houses the inner tube 37. Within this space 36d, the area outside the inner tube 37, from the fuel port 36c on the combustion chamber 5 side, constitutes the aforementioned fuel manifold 33. In other words, the fuel manifold 33 is an annular space formed between the outer tube 36 and the inner tube 37. Furthermore, the area of ​​the space 36d on the side opposite the combustion chamber 5, sandwiching the fuel port 36c, constitutes a bellows chamber 38 (described later).

[0053] The flange 36b is a part of the outer cylinder 36 and is a disc-shaped portion that protrudes radially outward from the outer circumference of the cylindrical main body 36a. In other words, the main body 36a and the flange 36b are perpendicular to each other and the main body 36a passes through the center of the disc-shaped flange 36b. The outer cylinder 36 is passed through the end cap 13 ( Figure 1 ), the flange 36b is fixed to the end cover 13 by bolts, thereby supporting the pilot burner 30. The main body 36a of the outer cylinder 36 is a long piece that extends across the flange 36b, penetrates the end cover 13, and extends to the position where fuel is injected into the combustion chamber 5 (i.e., near the combustion chamber 5).

[0054] The fuel port 36c is constructed by a piping portion 36c1 extending radially outward from the outer circumference of the flange 36b, and a flange portion 36c2 provided at the end of the piping portion 36c1. The piping portion 36c1 is a straight tube, and internally passes a fuel flow path 36h connected to the fuel manifold 33. The fuel flow path 36h is connected to the fuel manifold 33 from the radially outer side. However, the piping portion 36c1 may also be configured as an L-shaped tube. In this case, by connecting the piping portion 36c1 to the outer circumference of the flange 36b, the fuel flow path 36h is also connected to the fuel manifold 33 from the radially outer side.

[0055] -Inner tube-

[0056] The inner cylinder 37 is constructed to include a top side support portion 37a, a base side support portion 37b, a main body portion 37c, a bellows 37d, and a bulkhead member 37e. Like the main body 36a of the outer cylinder 36, the inner cylinder 37 is also an elongated object, and the inner cylinder 37 is smaller in diameter than the main body 36a of the outer cylinder 36. Furthermore, the top side support portion 37a, the base side support portion 37b, the main body portion 37c, the bellows 37d, and the bulkhead member 37e are coaxially connected annular or cylindrical members, with their center lines aligned in design. It should be noted that the shape of the bulkhead member is not limited to a circle and may also be a rectangle.

[0057] The top-side support portion 37a is provided on the top side of the inner tube 37 (the side closest to the combustion chamber 5 when the pilot burner 30 is mounted on the end cover 13, the same applies hereinafter) and is fixed to the outer tube 36. In this embodiment, a disc-shaped member integrally formed with the main body 37c and projecting radially outward from the outer circumference of the main body 37c is used as an example of the top-side support portion 37a. However, the structure of the top-side support portion 37a can be modified as appropriate, and an annular plate material other than the main body 37c can also be used as the top-side support portion 37a. Furthermore, the top-side support portion 37a exists between the outer circumferential surface of the main body 37c of the inner tube 37 and the inner circumferential surface of the main body 36a of the outer tube 36, without a gap, and also serves as an end cover that seals the top end of the space 36d, i.e., the top end of the fuel manifold 33. Each of the main fuel nozzles 32 is arranged in an annular shape so as to surround the main body portion 37 c of the inner tube 37 , is supported by the top side support portion 37 a , and is connected to the fuel header 33 .

[0058] The base-side support portion 37b is provided on the base side of the inner tube 37 (the side facing away from the combustion chamber 5 when the pilot burner 30 is attached to the end cover 13; the same applies hereinafter) and is fixed to the outer tube 36. In this embodiment, a separate annular member, serving as the base-side support portion 37b, is attached to the base-side end of the bellows 37d. However, the structure of the base-side support portion 37b can be modified as appropriate; for example, a structure in which the base-side support portion 37b and the bellows 37d are integrally formed can also be employed. Furthermore, the base-side support portion 37b exists without a gap between the outer circumferential surface of the inner tube 37 (bellows 37d) and the inner circumferential surface of the outer tube 36 (main body 36a). The inner tube 37 is supported on the outer tube 36 solely by the base-side support portion 37b and the top-side support portion 37a. The gap between the base-side support portion 37b and the top-side support portion 37a is relatively long, for example exceeding 300 mm.

[0059] The main body 37c is an inner side of the pilot fuel nozzle 31 ( Figure 1) passes through. The top-side support portion 37a is located near the front end of the main body portion 37c, and the main body portion 37c is supported by the outer cylinder 36 via the top-side support portion 37a. The aforementioned cyclone 34 is provided at the top end of the main body portion 37c.

[0060] The bellows 37d is connected to the base-side end of the main body 37c and is housed in the bellows chamber 38, located between the main body 37c and the base-side support portion 37b. The base-side end of the bellows 37d is restrained by the outer cylinder 36 via the base-side support portion 37b. The bellows 37d is a thin metal plate member formed into an accordion-shaped structure. It expands and contracts in response to axial thermal deformation of the main body 37c, originating from the top-side support portion 37a, thereby absorbing axial thermal deformation of the main body 37c. The maximum outer diameter of the bellows 37d (the outer diameter of the outermost circumference of the accordion-shaped structure) is larger than the outer diameter of the main body 37c of the inner cylinder 37. The distance between the outermost circumference of the bellows 37d and the inner wall surface of the space 36d of the outer cylinder 36 is shorter than the outer circumference of the main body 37c.

[0061] The bulkhead member 37e is attached to the bellows-side portion of the main body 37c and is positioned between the top-side support portion 37a and the base-side support portion 37b. In this embodiment, the bulkhead member 37e is located at the portion of the inner tube 37 where the main body 37c and the bellows 37d face each other, and engages with the base-side end of the main body 37c and the top-side end of the bellows 37d. The outer diameter of the bulkhead member 37e is larger than the outer diameter of the main body 37c and the outer diameter (maximum outer diameter) of the bellows 37d. Furthermore, the bulkhead member 37e is located between the outlet 36i of the fuel flow path 36h, which opens into the fuel manifold 33, and the bellows 37d, thereby separating the fuel manifold 33 from the bellows chamber 38.

[0062] However, a small gap G2 ( Figure 4 The gap G2 is larger than the gap G1 between the outermost peripheral surface of the bellows 37d and the inner peripheral surface of the outer cylinder 36 (i.e., the inner wall surface of the bellows chamber 38) facing the outermost peripheral surface. Figure 4 ) is small, for example, approximately 0.5 mm to 1 mm. There is no gap between the partition wall member 37e and the structure (main body 37c or bellows 37d) in contact with the inner circumferential surface of the partition wall member 37e. The gap G2 is set to allow for a certain radial thermal expansion difference of the bellows 37d relative to the outer cylinder 36 and to suppress interference between the bellows 37d and the inner wall of the bellows chamber 38 during excitation of the pilot burner 30.

[0063] 4. Effect

[0064] (1) The pilot burner 30 has a double-tube structure comprising an outer tube 36 and an inner tube 37. The elongated inner tube 37 is supported on the outer tube 36 only at two locations: a top support portion 37a and a base support portion 37b. For example, during startup, when low-temperature fuel is supplied after being heated by the combustion air a4, the difference in elongation between the outer tube 36 and the inner tube 37 varies depending on the situation. The difference in elongation between the outer tube 36 and the inner tube 37 occurs primarily in the axial direction, and the bellows 37d can flexibly absorb this difference in elongation.

[0065] Furthermore, during operation of the gas turbine engine, the pilot burner 30 is excited by mechanical and combustion vibrations, generating vibrations in the inner cylinder 37 with nodes of vibration at the top support portion 37a and the base support portion 37b as the amplitude. The main body 37c of the inner cylinder 37 has a space between it and the inner wall of the outer cylinder 36 (main body 36a), so in principle, there is no interference with the inner wall of the outer cylinder 36. However, the bellows 37d of the inner cylinder 37 has a smaller space between it and the inner wall of the outer cylinder 36 (the inner wall of the bellows chamber 38) than the fuel manifold 33. If the amplitude of the vibration of the inner cylinder 37 increases, there is a risk of interference with the inner wall of the outer cylinder 36. In particular, since the bellows 37d is made of a relatively thin metal plate, interference with other structures is undesirable.

[0066] Therefore, in this embodiment, a partition member 37e is attached to the main body 37c of the inner tube 37 between the top-side support portion 37a and the base-side support portion 37b. A gap G2, as previously described, exists between the outer circumferential surface of the partition member 37e and the inner circumferential surface of the outer tube 36. This gap G2 allows for a certain difference in radial thermal expansion between the bellows 37d and the outer tube 36, thereby protecting the bellows 37d. Furthermore, this gap G2 is appropriately set within a range smaller than the gap G1 between the outermost circumferential surface of the bellows 37d and the inner circumferential surface of the outer tube 36. Consequently, the partition member 37e interferes with the inner circumferential surface of the outer tube 36 between the top-side support portion 37a and the base-side support portion 37b, acting as a stopper to suppress the vibration amplitude of the inner tube 37. This effectively suppresses radial movement of the bellows 37d, thereby also preventing interference between the bellows 37d and the outer tube 36. By arranging the partition wall member 37e near the bellows 37d, vibration of the bellows 37d can be effectively reduced.

[0067] As described above, according to the pilot burner 30 of the present embodiment, it is possible to flexibly cope with thermal deformation using the bellows 37 d and also to effectively suppress damage to the bellows 37 d.

[0068] (2) In this embodiment, a partition wall member 37e is disposed between the outlet 36i of the fuel flow path 36h, which opens into the fuel manifold 33, and the bellows 37d, thereby dividing the fuel manifold 33 from the bellows chamber 38. The bellows 37d thus acts as an obstacle and damper, preventing the fuel supplied from the fuel flow path 36h to the fuel manifold 33 from violently flowing into the bellows chamber 38. Even if foreign matter enters the pilot burner 30 along with the fuel supplied to the fuel manifold 33, this foreign matter is prevented from entering the bellows chamber 38 and interfering with the bellows 37d, thereby protecting the bellows 37d from the foreign matter accompanying the fuel. Furthermore, exposure of the bellows 37d to the flow of low-temperature fuel is prevented, thereby minimizing any differences in elongation between the bellows 37d and surrounding structures, which is another advantage.

[0069] (Second embodiment)

[0070] Figure 5 This is a cross-sectional view showing an enlarged view of the main part of the pilot burner of the second embodiment of the present invention. Figure 4 .exist Figure 5 In the present invention, the same reference numerals as those in the first embodiment are given to the same or corresponding elements as those in the first embodiment, and the description thereof will be appropriately omitted.

[0071] This embodiment differs from the first embodiment in that it includes a sealing member 39 that seals the gap G2 between the outer circumferential surface of the partition member 37e and the inner circumferential surface of the outer cylinder 36. The sealing member is an annular member corresponding to the shape of the gap G2, and is preferably made of an elastic material to accommodate changes in the relative radial extension difference between the bellows 37d and the outer cylinder 36. Providing the sealing member 39 allows the gap G2 to be set larger than in the first embodiment. In other respects, this embodiment is the same as the first embodiment.

[0072] According to this embodiment, in addition to the same effects as the first embodiment, the fuel manifold 33 and the bellows chamber 38 are separated by the sealing member 39, thereby sealing the flow of fuel supplied to the fuel manifold 33 into the bellows chamber 38. This effectively prevents foreign matter accompanying the fuel supplied to the fuel manifold 33 from interfering with the bellows 37d. Furthermore, the ingress of fuel into the bellows chamber 38 is suppressed, thereby preventing fuel from stagnating within the bellows chamber 38.

Claims

1. A burner having a double tube structure including an outer tube and an inner tube. The burner is characterized in that The inner cylinder is constructed to include: a top side support portion fixed to the outer cylinder; a base side support portion fixed to the outer cylinder; a main body portion supported by the top side support portion; a bellows located between the main body and the base-side support portion; as well as a partition member installed at a position between the top side support portion and the base side support portion, Between the outer peripheral surface of the partition member and the inner peripheral surface of the outer cylinder, there is a second gap smaller than the first gap between the outermost peripheral surface of the bellows and the inner peripheral surface of the outer cylinder. The burner has: a fuel header formed between the outer cylinder and the inner cylinder; a plurality of main fuel nozzles connected to the fuel manifold; a pilot fuel nozzle extending through the interior of the inner barrel; and a fuel flow path connected to the fuel header, The partition wall member is present between an outlet of the fuel flow path that opens to the fuel header and the bellows.

2. The burner according to claim 1, characterized in that The burner includes a sealing member that seals the second gap between the outer peripheral surface of the partition wall member and the inner peripheral surface of the outer cylinder.

3. A burner, wherein: The burner includes the burner according to claim 1 or 2.

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