Combustion chamber air fairing and combustion chamber

Abstract

The invention discloses a combustion chamber air fairing which comprises a fairing outer cylinder (1) and a guide plate (2), the guide plate (2) is located on the radial inner side of the fairing outer cylinder (1), at least part of the guide plate (2) is a curved surface, a plurality of through holes are formed in the fairing outer cylinder (1), and the combustion chamber air fairing is characterized by further comprising a plurality of partition plates (3) connected to the fairing outer cylinder (1) and the guide plate (2) and further comprising spoilers (4). The problems that uniformity of air flowing into different nozzles from a fairing is poor, a thin-wall structure of the fairing is prone to being damaged during operation, and the mixing effect of air and fuel in a combustion chamber is common are solved, meanwhile, vortex and turbulent flow of the air before the air enters the nozzles are reduced, air flowing is more stable, energy loss in the combustion chamber is reduced, combustion efficiency is improved, and the service life of the combustion chamber is prolonged. The stability and the uniformity of the combustion process are ensured; the invention further discloses a combustion chamber with the combustion chamber air fairing.

Description

Technical Field

[0001] The invention relates to the field of gas turbines, and in particular to a combustion chamber air fairing and a combustion chamber. Background Art

[0002] During the operation of a gas turbine, air first enters the compressor. After being compressed, its temperature and pressure increase, and then the high-temperature and high-pressure air flows into the combustion chamber. The structure of the combustion chamber usually includes a central nozzle and multiple peripheral nozzles. In order to ensure that the air can be evenly distributed to each nozzle, it is necessary to design and install a fairing to ensure the consistency of the air flow entering each nozzle, so that the air can be evenly distributed in the combustion chamber, improve combustion efficiency, reduce vortices and turbulence, protect the nozzles, and optimize the airflow distribution in the combustion chamber.

[0003] The main function of the fairing is to achieve air rectification and flow guidance, so that the air can flow into the nozzle in a more stable and uniform state, thereby providing a guarantee for the efficient and stable operation of the combustion chamber. Traditionally, the fairing adopts a thin-walled structure with several fairing outer tubes and a guide plate. The air flows in from the outer tube of the fairing and enters the nozzle after being guided by the guide plate. The fairing plays a key role in rectifying and guiding the air in this process to ensure the stability and uniformity of the air flow. However, the current fairing still has the following problems: (1) The uniformity of air flowing from the fairing into different nozzles is poor; (2) The fairing has a thin-walled structure and is easily damaged during operation; (3) It does not enhance the mixing of air and fuel in the nozzle.

[0004] Patent document CN113091093A discloses an air fairing and nozzle of a gas turbine, including an air fairing including a front end plate of the fairing, an outer wall of the fairing, and N guide plates arranged on the inner side of the outer wall of the fairing, wherein N is a positive integer greater than or equal to 1, the front end plate of the fairing is connected to the outer wall of the fairing, and a plurality of first fairing holes are arranged on the front end plate of the fairing; a plurality of second fairing holes are arranged on the first area of ​​the outer wall of the fairing; a first end of at least one guide plate is connected to the inner side of the outer wall of the fairing; a part of the air enters the air fairing axially through the fairing holes of the front end plate of the fairing, and another part of the air enters the air fairing circumferentially through the fairing holes of the outer wall of the fairing, and under the action of at least one guide plate, the air entering the air fairing flows axially and flows out from the other end of the air fairing, but the problems that the uniformity of air flowing from the fairing into different nozzles is poor, the thin-walled structure of the fairing is easily damaged during operation, and the mixing effect of air and fuel in the combustion chamber is general are not solved.

[0005] Patent document CN117366623A discloses a gas turbine combustion chamber guide bushing, which includes a flange part and a shell part, wherein the flange part includes a front end flange and a rear end flange, the front end flange and the rear end flange are welded on the front and rear sides of the shell part respectively, the front end of the shell part is fixed to the outer casing of the high-pressure compressor through the front end flange, and the rear end of the shell part is fixed to the rear end diffuser of the high-pressure compressor through the rear end flange, the shell part includes a shroud and a fairing, and the shroud and the fairing are alternately welded to form a cylindrical shell structure, which does not solve the problems of poor uniformity of air flowing from the fairing into different nozzles, easy damage to the thin-walled structure of the fairing during operation, and general air and fuel mixing effect in the combustion chamber.

[0006] In summary, the above two existing patents do not solve the problems of poor uniformity of air flowing from the fairing into different nozzles, easy damage to the thin-walled structure of the fairing during operation, and general mixing effect of air and fuel in the combustion chamber. Summary of the invention

[0007] Based on the above technical problems, the present invention proposes a combustion chamber air fairing and a combustion chamber to solve the problems of poor uniformity of air flowing from the fairing into different nozzles, easy damage to the thin-walled structure of the fairing during operation, and general air and fuel mixing effect in the combustion chamber.

[0008] To achieve the above object, the present invention provides a combustion chamber air fairing.

[0009] A combustion chamber air fairing comprises a fairing outer tube and a guide plate, wherein the guide plate is located radially inward of the fairing outer tube, at least a portion of the guide plate is a curved surface, a plurality of through holes are provided on the fairing outer tube, and the invention is characterized in that the fairing outer tube further comprises a plurality of partition plates, wherein the partition plates are connected to the fairing outer tube and the guide plate.

[0010] Furthermore, the partition plate is perpendicular to the fairing outer cylinder and is arranged on the inner surface of the fairing outer cylinder along the axial direction of the fairing outer cylinder.

[0011] Furthermore, the radial inner edge of the partition plate at least extends forward to the curved surface portion of the guide plate.

[0012] Furthermore, the radially outer edge of the partition plate extends rearward to the tail end of the fairing outer cylinder.

[0013] Furthermore, it also includes a spoiler, and a plurality of the spoilers are extended along the guide plate.

[0014] Furthermore, the number of spoilers arranged between the partition plates is 2-7.

[0015] Furthermore, the spoiler is in the shape of a curved rectangular plate.

[0016] Furthermore, the spoiler and the partition plate are evenly distributed on the outer cylinder of the fairing in a rotationally symmetrical manner.

[0017] Furthermore, the spoiler is arranged at the tail of the guide plate, and a plurality of the spoilers are connected to the guide plate in the same direction.

[0018] Furthermore, the spoiler includes a mounting end and a spoiler end, the mounting end is connected to the guide plate; the spoiler end is bent and located at the rear end of the spoiler.

[0019] Furthermore, two sides of the spoiler extending in the axial direction are a straight side and a warped side, the partition plate is connected to the straight side of the spoiler, and the warped side is bent in a radially outward direction.

[0020] Further, the warped edge bending angle θ1 of the spoiler end of the spoiler is in the range of 8°-20°, the straight edge bending angle θ2 of the spoiler end of the spoiler is in the range of 5°-15°, and the blade-shaped bending angle θ of the spoiler is in the range of 20°-32°; the blade-shaped bending angle θ of the spoiler is the sum of the absolute value of the warped edge bending angle θ1 of the spoiler end of the spoiler and the absolute value of the straight edge bending angle θ2 of the spoiler end of the spoiler.

[0021] To achieve the above object, the present invention also provides a combustion chamber having the above fairing.

[0022] Furthermore, the combustion chamber includes peripheral nozzles, and the number n1 of the partition plates is an integer multiple of the number n2 of the peripheral nozzles of the combustion chamber.

[0023] Based on the above technical solution, the present invention has at least the following beneficial effects:

[0024] 1. The present invention proposes a combustion chamber air fairing and a combustion chamber. By designing a plurality of partition plates between the outer tube of the fairing and the guide plate, the air flow path can be evenly divided to ensure that the air is evenly distributed before entering each nozzle. The partition plates are evenly distributed along the circumference, and each peripheral nozzle is located between two partition plates, thereby ensuring the consistency of air flow. The design of the partition plates can reduce the vortex and turbulence of the air before entering the nozzle, making the air flow smoother, which helps to reduce energy loss in the combustion chamber, improve combustion efficiency, and ensure the stability and uniformity of the combustion process.

[0025] 2. The present invention proposes a combustion chamber air fairing and a combustion chamber. Since the traditional fairing adopts a thin-walled structure and is easily damaged under high temperature and high pressure operating conditions, the present invention can significantly improve the structural strength of the fairing by designing a partition plate between the outer tube of the fairing and the guide plate. The addition of the partition plate can disperse stress and reduce local stress concentration, thereby improving the fairing's anti-deformation ability. While enhancing the structural strength, it can also reduce the damage of the fairing during operation and reduce maintenance costs.

[0026] 3. The present invention proposes a combustion chamber air fairing and a combustion chamber, wherein a spoiler is added to the tail end of the guide plate, and the spoiler is bent at a certain angle. The spoiler disturbs the incoming air, thereby enhancing the mixing effect of air and downstream fuel. The design of the spoiler can also enhance the turbulence of the air, improve the mixing efficiency of fuel and air, and reduce the situation of incomplete combustion. The maintenance and replacement frequency is reduced, the operating cost is reduced, the economy and reliability of the equipment are improved, and the long-term stable operation of the gas turbine is ensured. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0028] Figure 1 A schematic diagram of the three-dimensional structure of a combustion chamber air fairing according to an embodiment is shown;

[0029] Figure 2 A front view of a three-dimensional structure of a combustion chamber air fairing according to one embodiment is shown;

[0030] Figure 3 A three-dimensional structural side view of a combustion chamber air cowling according to one embodiment is shown;

[0031] Figure 4 A schematic diagram of the three-dimensional structure of a spoiler according to an embodiment is shown;

[0032] Figure 5 A schematic diagram of the three-dimensional structure of a spoiler end of a spoiler according to an embodiment is shown.

[0033] The above-mentioned drawings include the following reference numerals:

[0034] 1. Fairing outer tube; 2. Guide plate; 3. Separator; 4. Spoiler;

[0035] 41. Mounting end; 42. Spoiler end; 43. Straight edge; 44. Warped edge. DETAILED DESCRIPTION

[0036] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0037] The present invention is further described in detail below in conjunction with specific embodiments, and these embodiments cannot be understood as limiting the scope of protection claimed by the present invention. The term "including" when used indicates the existence of a feature, but does not exclude the existence or addition of one or more other features; the orientation or position relationship indicated by the terms "lateral", "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inside", "outside", etc. is based on the orientation or position relationship shown in the drawings, which is only for the convenience of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention; in addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance.

[0038] In the description, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. In addition, in the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0039] Example

[0040] The present invention proposes a combustion chamber air fairing, such as Figure 1 As shown in the figure, it includes a fairing outer tube 1 and a guide plate 2, wherein the guide plate 2 is located on the radial inner side of the fairing outer tube 1, at least a portion of the guide plate 2 is a curved surface, and a plurality of through holes are provided on the fairing outer tube 1. It is characterized in that it also includes a plurality of partition plates 3, and the partition plates 3 are connected to the fairing outer tube 1 and the guide plate 2.

[0041] Furthermore, combined with Figure 2 and Figure 3 As shown in the figure, part of the guide plate 2 is connected to part of the fairing outer tube 1, and the guide plate 2 includes a curved portion and a parallel portion. The curved portion of the guide plate 2 is connected to the fairing outer tube 1, and the parallel portion of the guide plate 2 is parallel to the fairing outer tube 1 along the axial direction of the fairing outer tube 1.

[0042] Furthermore, the partition plate 3 is arranged between the fairing outer tube 1 and the guide plate 2, and the radial inner edge of the partition plate 3 extends at least forward to the curved portion of the guide plate 2; the radial outer edge of the partition plate 3 extends rearward to the tail end of the fairing outer tube 1.

[0043] Furthermore, the spoiler 4 is arranged at the rear of the guide plate 2 and is extended along the parallel part of the guide plate 2, and the spoiler 4 and the partition plate 3 are evenly distributed on the outer cylinder of the fairing in a rotationally symmetrical manner.

[0044] Furthermore, if Figure 4 The spoiler 4 shown in the figure is a curved rectangular plate, including a mounting end 41 and a spoiler end 42. The mounting end 41 is connected to the guide plate 2, and the two opposite sides connecting the end surface of the mounting end 41 and the end surface of the spoiler end 42 are a straight edge 43 and a warped edge 44 respectively.

[0045] Furthermore, if Figure 5 As shown in the figure, the bending angle θ1 of the warped edge 44 of the spoiler end 42 of the spoiler 4 ranges from 8° to 20°, the bending angle θ2 of the straight edge 43 of the spoiler end 42 of the spoiler 4 ranges from 5° to 15°, and the blade bending angle θ of the spoiler end 42 of the spoiler 4 ranges from 20° to 32°.

[0046] The bending angle θ1 of the warped edge 44 of the spoiler end 42 and the bending angle θ2 of the straight edge 43 of the spoiler end 42 are respectively the angles formed by the tangent lines of the middle arc line of the end face of the spoiler end 42 at both ends and the chord line of the end face of the spoiler end 42. The line formed by connecting the midpoints of the edges at both ends of the end face of the spoiler end 42 is called the chord line of the end face of the spoiler end 42; the line connecting the centers of the inscribed circles of the end faces of the spoiler end 42 is the middle arc line.

[0047] Preferably, the bending angle θ1 of the warped edge 44 is 16°, the bending angle θ2 of the straight edge 43 is 12°, and the leaf-shaped bending angle θ is 28°.

[0048] Furthermore, the number of spoilers 4 between the partition plates 3 may be 2, 3, 4, 5, 6 or 7. In the combustion chamber of a gas turbine, the calculation formula for the mixing unevenness is as follows:

[0049]

[0050] Among them, U is the fuel and air mixing unevenness, is the standard deviation of fuel component distribution, which is calculated based on the collected standard deviation of fuel component distribution. The relationship between the obtained fuel and air mixing unevenness and the number of spoilers 4 is shown in Table 1.

[0051] Table 1 Corresponding relationship between fuel and air mixing unevenness and spoiler 4

[0052] Number of spoilers / pcs Fuel and air mixing unevenness / % 2 15％ 3 11％ 4 6％ 5 3％ 6 7％ 7 8％

[0053] As shown in Table 1, there is a corresponding relationship between the number of spoilers 4 and the unevenness of fuel and air mixing. During the combustion process in the gas turbine, a higher unevenness of fuel and air mixing will lead to unstable combustion and affect the performance and life of the gas turbine. Therefore, preferably, the number of spoilers 4 between the partition plates 3 is 5.

[0054] To achieve the above object, the present invention further provides a combustion chamber having the above fairing, comprising:

[0055] The combustion chamber includes a peripheral nozzle and a central nozzle. The peripheral nozzles are arranged in a rotationally symmetrical manner around the central nozzle. The number n1 of the partition plates 3 can be equal to the number n2 of the peripheral nozzles of the combustion chamber, or can be an integer multiple of the number n2 of the peripheral nozzles of the combustion chamber.

[0056] In summary, it can be seen from the above description that the above embodiments of the present invention achieve the following technical effects:

[0057] 1. The present invention proposes a combustion chamber air fairing and a combustion chamber. By designing a plurality of partition plates between the outer tube of the fairing and the guide plate, the air flow path can be evenly divided to ensure that the air is evenly distributed before entering each nozzle. The partition plates are evenly distributed along the circumference, and each peripheral nozzle is located between two partition plates, thereby ensuring the consistency of air flow. The design of the partition plates can reduce the vortex and turbulence of the air before entering the nozzle, making the air flow smoother, which helps to reduce energy loss in the combustion chamber, improve combustion efficiency, and ensure the stability and uniformity of the combustion process.

[0058] 2. The present invention proposes a combustion chamber air fairing and a combustion chamber. Since the traditional fairing adopts a thin-walled structure and is easily damaged under high temperature and high pressure operating conditions, the present invention can significantly improve the structural strength of the fairing by designing a partition plate between the outer tube of the fairing and the guide plate. The addition of the partition plate can disperse stress and reduce local stress concentration, thereby improving the fairing's anti-deformation ability. While enhancing the structural strength, it can also reduce the damage of the fairing during operation and reduce maintenance costs.

[0059] 3. The present invention proposes a combustion chamber air fairing and a combustion chamber, wherein a spoiler is added to the tail end of the guide plate, and the spoiler is bent at a certain angle. The spoiler disturbs the incoming air, thereby enhancing the mixing effect of air and downstream fuel. The design of the spoiler can also enhance the turbulence of the air, improve the mixing efficiency of fuel and air, and reduce the situation of incomplete combustion. The maintenance and replacement frequency is reduced, the operating cost is reduced, the economy and reliability of the equipment are improved, and the long-term stable operation of the gas turbine is ensured.

[0060] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

[0061] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0062] It should be noted that, in the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, unless they are contradictory.

Claims

1. A combustion chamber air fairing, comprising a fairing outer cylinder (1) and a guide plate (2), wherein the guide plate (2) is located radially inward of the fairing outer cylinder (1), at least a portion of the guide plate (2) is a curved surface, and a plurality of through holes are provided on the fairing outer cylinder (1), characterized in that: It also comprises a plurality of partition plates (3), wherein the partition plates (3) are connected to the fairing outer cylinder (1) and the guide plate (2).

2. The fairing according to claim 1, characterized in that: The partition plate (3) is perpendicular to the fairing outer cylinder (1) and is arranged on the inner surface of the fairing outer cylinder (1) along the axial direction of the fairing outer cylinder (1).

3. The fairing according to claim 1, characterized in that: The radial inner edge of the partition plate (3) at least extends forward to the curved surface portion of the guide plate (2).

4. The fairing according to claim 3, characterized in that: The radially outer edge of the partition plate (3) extends toward the rear to the rear end of the fairing outer cylinder (1).

5. The fairing according to claim 1, characterized in that: Also includes a spoiler (4), A plurality of spoilers (4) are arranged extending along the guide plate (2).

6. The fairing according to claim 5, characterized in that: The number of spoilers (4) arranged between the partition plates (3) is 2-7.

7. The fairing according to claim 5, characterized in that: The spoiler (4) is in the shape of a curved rectangular plate.

8. The fairing according to claim 5, characterized in that: The spoiler (4) and the partition plate (3) are evenly distributed on the fairing outer cylinder (1) in a rotationally symmetrical manner.

9. The fairing according to claim 5, characterized in that: The spoiler (4) is arranged at the rear of the guide plate (2), and a plurality of the spoilers (4) are connected to the guide plate (2) in the same direction.

10. The fairing according to claim 5, characterized in that: The spoiler (4) comprises a mounting end (41) and a spoiler end (42). The mounting end (41) is connected to the guide plate (2); The spoiler end (42) is bent and located at the rear end of the spoiler plate (4).

11. The fairing according to claim 10, characterized in that: The two sides of the spoiler (4) extending in the axial direction are a straight side (43) and a warped side (44); the partition plate (3) is connected to the straight side (43) of the spoiler (4); and the warped side (44) is bent in a radially outward direction.

12. The fairing according to claim 11, characterized in that: The bending angle θ1 of the warped edge (44) of the spoiler end (42) of the spoiler (4) is in the range of 8°-20°, the bending angle θ2 of the straight edge (43) of the spoiler end (42) of the spoiler (4) is in the range of 5°-15°, and the blade bending angle θ of the spoiler (4) is in the range of 20°-32°; The blade bending angle θ of the spoiler (4) is the sum of the absolute value of the bending angle θ1 of the warped edge (44) of the spoiler end (42) of the spoiler (4) and the absolute value of the bending angle θ2 of the straight edge (43) of the spoiler end (42) of the spoiler (4).

13. A combustion chamber having a fairing as claimed in claim 1, said combustion chamber comprising a peripheral nozzle, characterized in that: The number n1 of the partition plates (3) is an integer multiple of the number n2 of the peripheral nozzles of the combustion chamber.

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