A combustion chamber air straightener cowling and combustion chamber

Abstract

The application discloses a combustion chamber air flow straightener, which comprises a flow straightener outer cylinder (1) and a flow guide plate (2), the flow guide plate (2) is located on the radial inner side of the flow straightener outer cylinder (1), at least part of the flow guide plate (2) is a curved surface, a plurality of through holes are formed in the flow straightener outer cylinder (1), and the combustion chamber air flow straightener is characterized in that a plurality of partition plates (3) are further arranged, the partition plates (3) are connected to the flow straightener outer cylinder (1) and the flow guide plate (2), and a spoiler (4) is further arranged. The combustion chamber air flow straightener solves the problems that air uniformity from the flow straightener into different nozzles is poor, the flow straightener is easy to be damaged when a thin-wall structure of the flow straightener operates, and air and fuel mixing effect in the combustion chamber is general, simultaneously reduces vortex and turbulent flow of air before entering the nozzles, and makes air flow more stable, which is helpful to reducing energy loss in the combustion chamber, improving combustion efficiency, and ensuring stability and uniformity of the combustion process. The application further discloses a combustion chamber with the combustion chamber air flow straightener.

Description

Technical Field

[0001] This invention relates to the field of gas turbines, and more specifically to a combustion chamber air smother and a combustion chamber. Background Technology

[0002] During the operation of a gas turbine, air first enters the compressor. After compression, its temperature and pressure increase, and then this high-temperature, high-pressure air flows into the combustion chamber. The combustion chamber typically includes a central nozzle and multiple peripheral nozzles. To ensure that air is evenly distributed to each nozzle, a shroud needs to be designed and installed. This ensures consistent airflow into each nozzle, enabling uniform air distribution within the combustion chamber, improving combustion efficiency, reducing eddies and turbulence, protecting the nozzles, and optimizing airflow distribution within the combustion chamber.

[0003] The main function of the fairing is to rectify and guide the air, so that the air can flow into the nozzle in a more stable and uniform state, thereby ensuring the efficient and stable operation of the combustion chamber. Traditionally, the fairing adopts a thin-walled structure with several fairing outer cylinders and a guide plate. Air flows in from the fairing outer cylinders 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 shroud and nozzles for a gas turbine. The air shroud includes a front end plate, an outer wall, and N guide plates disposed on the inner side of the outer wall, where N is a positive integer greater than or equal to 1. The front end plate is connected to the outer wall and has several first rectification holes. A first region of the outer wall has several second rectification holes. The first end of at least one guide plate is connected to the inner side of the outer wall. A portion of the air enters the air shroud axially through the rectification holes of the front end plate, while another portion enters the air shroud circumferentially through the rectification holes of the outer wall. Under the action of at least one guide plate, the air entering the air shroud flows axially and exits from the other end of the air shroud. However, this invention does not solve the problems of poor uniformity of air flowing from the shroud into different nozzles, easy damage to the thin-walled structure of the shroud during operation, and poor mixing effect of air and fuel in the combustion chamber.

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

[0006] In summary, neither of the two existing patents mentioned above has solved the problems of poor uniformity of air flowing from the cowl into different nozzles, easy damage to the thin-walled structure of the cowl during operation, and mediocre mixing effect of air and fuel in the combustion chamber. Summary of the Invention

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

[0008] To achieve the above objectives, the present invention proposes a combustion chamber air shroud.

[0009] A combustion chamber air hood includes an outer cylinder and a guide plate, wherein the guide plate is located radially inside the outer cylinder and at least a portion of the guide plate is curved. The outer cylinder has multiple through holes. The hood is characterized by further including multiple partition plates connected to the outer cylinder and the guide plate.

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

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

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

[0013] Furthermore, it also includes spoilers, with a plurality of said spoilers extending along said guide plate.

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

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

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

[0017] Furthermore, the spoiler is located at the tail of the guide plate, and multiple 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 being connected to the guide plate; the spoiler end is curved and located at the tail end of the spoiler.

[0019] Furthermore, the two sides of the spoiler extending axially 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] Furthermore, the warped side bend angle θ1 of the spoiler end ranges from 8° to 20°, the straight side bend angle θ2 of the spoiler end ranges from 5° to 15°, and the blade bend angle θ of the spoiler ranges from 20° to 32°; the blade bend angle θ of the spoiler is the sum of the absolute value of the warped side bend angle θ1 of the spoiler end and the absolute value of the straight side bend angle θ2 of the spoiler end.

[0021] To achieve the above objectives, the present invention also proposes a combustion chamber having the aforementioned fairing.

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

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

[0024] 1. This invention proposes a combustion chamber air shroud and combustion chamber. By designing multiple partition plates between the outer cylinder of the shroud and the guide plate, the airflow channel can be evenly divided, ensuring that the air is evenly distributed before entering each nozzle. The partition plates are evenly distributed circumferentially, and each peripheral nozzle is located between two partition plates, thereby ensuring the consistency of airflow. The design of the partition plates can reduce the eddies and turbulence of air before entering the nozzle, making the airflow more stable, 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. This invention proposes a combustion chamber air shunting cowl and a combustion chamber. Traditional cowlings, with their thin-walled structure, are prone to damage under high-temperature and high-pressure operating conditions. This invention significantly improves the structural strength of the cowling by designing a partition plate between the outer cylinder and the guide plate. The partition plate disperses stress, reduces localized stress concentration, and thus improves the cowling's resistance to deformation. This enhanced structural strength also reduces damage to the cowling during operation, lowering maintenance costs.

[0026] 3. This invention proposes a combustion chamber air shroud and combustion chamber, in which a spoiler is added to the tail end of the guide vane. The spoiler is bent at a certain angle, and by disturbing the incoming airflow, the mixing effect between air and downstream fuel is enhanced. The design of the spoiler can also enhance air turbulence, improve fuel-air mixing efficiency, and reduce incomplete combustion. This reduces maintenance and replacement frequency, lowers operating costs, improves the economy and reliability of the equipment, and ensures the long-term stable operation of the gas turbine. Attached Figure Description

[0027] The accompanying drawings, which form part of this specification, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0028] Figure 1 A three-dimensional structural schematic diagram of a combustion chamber air shroud according to one embodiment is shown;

[0029] Figure 2 A three-dimensional front view of the combustion chamber air shroud of one embodiment is shown;

[0030] Figure 3 A three-dimensional side view of the combustion chamber air shroud of one embodiment is shown;

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

[0032] Figure 5 A three-dimensional structural schematic diagram of the spoiler end of one embodiment is shown.

[0033] The above figures include the following reference numerals:

[0034] 1. Fairing outer cylinder; 2. Guide vane; 3. Separator; 4. Spoiler;

[0035] 41. Mounting end; 42. Turbulence end; 43. Straight edge; 44. Warped edge. Detailed Implementation

[0036] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0037] The present invention will be further described in detail below with reference to specific embodiments. These embodiments should not be construed as limiting the scope of protection claimed by the present invention. The term "comprising" indicates the presence of a feature, but does not exclude the presence or addition of one or more other features. The terms "lateral," "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the purpose of description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0038] In this description, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances. Furthermore, in the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0039] Example

[0040] This invention proposes a combustion chamber air shroud, such as... Figure 1 The diagram shows a fairing outer cylinder 1 and a guide plate 2. The guide plate 2 is located radially inside the fairing outer cylinder 1. At least a portion of the guide plate 2 is curved. The fairing outer cylinder 1 has multiple through holes. The diagram is characterized by further including multiple partition plates 3, which are connected to the fairing outer cylinder 1 and the guide plate 2.

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

[0042] Furthermore, the partition plate 3 is disposed between the outer cylinder of the fairing 1 and the guide plate 2, and the radial inner edge of the partition plate 3 extends at least forward to the curved part of the guide plate 2; the radial outer edge of the partition plate 3 extends towards the tail end to the tail end of the outer cylinder of the fairing 1.

[0043] Furthermore, the spoiler 4 is disposed at the tail of the guide plate 2 and extends along the parallel portion 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, such as Figure 4 The spoiler 4 shown 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. The two opposite sides of the end face connecting the mounting end 41 and the end face of the spoiler end 42 are a straight side 43 and a warped side 44, respectively.

[0045] Furthermore, such as Figure 5 As shown, the bend angle θ1 of the warped edge 44 of the spoiler end 42 of the spoiler 4 ranges from 8° to 20°, the bend angle θ2 of the straight edge 43 of the spoiler end 42 of the spoiler 4 ranges from 5° to 15°, and the bend angle θ of the leaf shape of the spoiler end 42 of the spoiler 4 ranges from 20° to 32°.

[0046] The bend angle θ1 of the warped side 44 and the bend angle θ2 of the straight side 43 of the spoiler end 42 are the angles formed by the intersections of the tangents to the arc line at both ends of the end face of the spoiler end 42 and the chord line of the end face of the spoiler end 42. The line connecting the midpoints of the sides 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 face of the spoiler end 42 is called the arc line.

[0047] Preferably, the bend angle θ1 of the warped side 44 is 16°, the bend angle θ2 of the straight side 43 is 12°, and the bend angle θ of the leaf shape is 28°.

[0048] Furthermore, the number of baffles 4 between the partition plates 3 can be 2, 3, 4, 5, 6, or 7. In the gas turbine combustion chamber, the formula for calculating the mixing non-uniformity is as follows:

[0049]

[0050] Where U represents the non-uniformity of fuel and air mixing. The standard deviation of fuel component distribution is calculated based on the collected standard deviation of fuel component distribution. The relationship between the fuel and air mixing non-uniformity and the number of baffles 4 is shown in Table 1.

[0051] Table 1. Correspondence between fuel and air mixing non-uniformity and spoiler 4

[0052] Number of spoilers / piece Fuel and air mixing non-uniformity / % 2 15％ 3 11％ 4 6％ 5 3％ 6 7％ 7 8％

[0053] Table 1 shows the relationship between the number of baffles 4 and the non-uniformity of fuel and air mixing. During combustion in a gas turbine, a high degree of non-uniformity of fuel and air mixing can lead to unstable combustion, affecting the performance and lifespan of the gas turbine. Therefore, preferably, the number of baffles 4 between the partition plates 3 is 5.

[0054] To achieve the above objectives, the present invention also provides a combustion chamber having the aforementioned fairing, comprising:

[0055] The combustion chamber includes peripheral nozzles 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 it can be an integer multiple of the number n2 of the peripheral nozzles of the combustion chamber.

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

[0057] 1. This invention proposes a combustion chamber air shroud and combustion chamber. By designing multiple partition plates between the outer cylinder of the shroud and the guide plate, the airflow channel can be evenly divided, ensuring that the air is evenly distributed before entering each nozzle. The partition plates are evenly distributed circumferentially, and each peripheral nozzle is located between two partition plates, thereby ensuring the consistency of airflow. The design of the partition plates can reduce the eddies and turbulence of air before entering the nozzle, making the airflow more stable, 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. This invention proposes a combustion chamber air shunting cowl and a combustion chamber. Traditional cowlings, with their thin-walled structure, are prone to damage under high-temperature and high-pressure operating conditions. This invention significantly improves the structural strength of the cowling by designing a partition plate between the outer cylinder and the guide plate. The partition plate disperses stress, reduces localized stress concentration, and thus improves the cowling's resistance to deformation. This enhanced structural strength also reduces damage to the cowling during operation, lowering maintenance costs.

[0059] 3. This invention proposes a combustion chamber air shroud and combustion chamber, in which a spoiler is added to the tail end of the guide vane. The spoiler is bent at a certain angle, and by disturbing the incoming airflow, the mixing effect between air and downstream fuel is enhanced. The design of the spoiler can also enhance air turbulence, improve fuel-air mixing efficiency, and reduce incomplete combustion. This reduces maintenance and replacement frequency, lowers operating costs, improves the economy and reliability of the equipment, and ensures the long-term stable operation of the gas turbine.

[0060] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

[0061] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0062] It should be noted that, in the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

Claims

1. A combustion chamber air shroud, comprising a shroud outer cylinder (1) and a guide plate (2), wherein the guide plate (2) is located radially inside the shroud outer cylinder (1), at least a portion of the guide plate (2) is curved, and a plurality of through holes are formed on the shroud outer cylinder (1), characterized in that, It also includes multiple partition plates (3), which are connected to the outer cylinder of the fairing (1) and the guide plate (2); It also includes spoilers (4), a plurality of said spoilers (4) extending along said guide plate (2); The spoiler (4) includes 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 curved and located at the tail end of the spoiler (4). The spoiler (4) has two straight sides (43) and warped sides (44) extending axially. The partition plate (3) is connected to the straight side (43) of the spoiler (4), and the warped side (44) bends in a radially outward direction. The bend angle θ1 of the warped side (44) of the spoiler end (42) of the spoiler (4) is in the range of 8°-20°, the bend angle θ2 of the straight side (43) of the spoiler end (42) of the spoiler (4) is in the range of 5°-15°, and the bend angle θ of the blade of the spoiler (4) is in the range of 20°-32°; the bend angle θ of the blade of the spoiler (4) is the sum of the absolute value of the bend angle θ1 of the warped side (44) of the spoiler end (42) of the spoiler (4) and the absolute value of the bend angle θ2 of the straight side (43) of the spoiler end (42) of the spoiler (4); The number of baffles (4) provided between the partition plates (3) is 2-7; The spoiler (4) is a curved rectangular plate.

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

3. The fairing according to claim 1, characterized in that, The radial inner edge of the partition plate (3) extends at least forward to the curved 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 towards the tail end to the tail end of the fairing outer cylinder (1).

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

6. The fairing according to claim 1, characterized in that, The spoiler (4) is located at the tail of the guide plate (2), and multiple spoilers (4) are connected to the guide plate (2) in the same direction.

7. A combustion chamber having a cowling as described in claim 1, the combustion chamber comprising peripheral nozzles, 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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