A combustion chamber nozzle flow straightener

Abstract

The application provides a combustion chamber nozzle rectifying device, which comprises a base, a cover, a rectifying cover and two or more connecting pieces, the base and the cover are located at different axial positions of the rectifying device, and the two or more connecting pieces are fixed between the base and the cover along the circumferential direction of the cover; in the projection along the axial direction of the cover, the projections of the connecting pieces are all located inside the projection of the cover, and the rectifying cover is fixed to the side of the connecting pieces away from the axial line of the cover along the circumferential direction of the cover. The application can not only reduce the diameter of the whole nozzle rectifying device, the diameter of the head of the combustion chamber and the volume and weight of the whole gas turbine, and reduce the cost of the gas turbine, but also can further reduce the diameter of the whole nozzle rectifying device by using the single-layer structure of the rectifying cover, so that the structure is simple and the installation is convenient.

Description

Technical Field

[0001] This invention relates to the field of gas turbine structural design, and more specifically, to a combustion chamber nozzle rectification device. Background Technology

[0002] A gas turbine mainly consists of three major components: the compressor, the combustion chamber, and the turbine. The combustion chamber is the core hot-end component that mixes compressed air with fuel and combusts it to generate high-temperature, high-pressure gas to drive the turbine. A typical combustion chamber structure, along the airflow direction, includes the combustion chamber head, flame tube, and transition section. The combustion chamber head further integrates sub-components such as end caps, shrouds, and nozzles. The combustion chamber shroud is a critical component of the combustion chamber, and its functions include: guiding and distributing airflow: uniformly distributing the high-speed compressed air output from the compressor to each nozzle in the combustion chamber, ensuring uniform mixing of air and fuel output from the nozzles, and avoiding combustion instability or efficiency reduction caused by uneven mixing in certain areas; stabilizing the combustion environment: by adjusting the airflow speed and direction, reducing turbulence and flow separation, maintaining a stable pressure distribution within the combustion chamber, preventing flame flickering or extinguishing, thereby improving combustion efficiency and reducing emissions; reducing flow losses: optimizing the airflow path design, reducing pressure loss, and improving the overall efficiency of the gas turbine; and suppressing vibration and noise: by stabilizing airflow and reducing pressure pulsation, the shroud indirectly reduces vibration and noise during combustion, improving operational stability.

[0003] In the prior art, CN113669758 discloses a combustion chamber cap and a gas turbine having it. The support structure of this cap mainly includes an annular flange and a group of A-shaped supports. The annular flange is fitted onto the outer wall of the cap, and the outer cylinder of the cap is connected by a group of A-shaped supports evenly distributed around the circumference. It is then connected to external equipment via bolts and pins. Another example is CN113739203B, which discloses a cap assembly for a burner. The support structure of this cap mainly includes a connecting flange and a group of straight or spiral connecting parts. This cap places the connecting flange on the burner's end cover, and the connecting flange has connecting parts extending away from the end cover. The cap connects to the end of the connecting parts away from the end cover, increasing the distance between the connecting flange and the cap. This allows for a larger temperature difference between the connecting flange and the cap without generating excessive thermal stress, eliminating the need to reduce the thickness of the connecting parts, ensuring the rigidity of the connecting parts, preventing resonance cracking, and ensuring stable support of the cap by the connecting parts.

[0004] With the development of gas turbine technology, some advanced gas turbines require reduced manufacturing costs and smaller combustion chamber space and weight. However, the existing technologies mentioned above all require a large annular space outside the outer casing to accommodate annular flanges, A-frame supports, or various connecting components. Therefore, none of the existing technologies can meet these requirements. Summary of the Invention

[0005] The purpose of this invention is to solve the above-mentioned technical problems.

[0006] To achieve the above objectives, the first aspect of the present invention provides a combustion chamber nozzle straightening device, comprising a base, a cap, a shunting cover, and two or more connecting members. The base and the cap are respectively located at different axial positions of the straightening device, and the two or more connecting members are fixed between the base and the cap along the circumference of the cap. In the projection along the axial direction of the cap, the projection of the connecting members is located inside the projection of the cap, and the shunting cover is fixed along the circumference of the cap to the side of the connecting members away from the axis of the cap.

[0007] Furthermore, from one end fixed to the base to one end fixed to the cap, the distance between the connector and the axis of the cap on a cross section perpendicular to the axis of the cap continuously increases.

[0008] Furthermore, the base includes two or more first fixing parts, and in the projection along the axial direction of the cap, the projection of the first fixing part is located inside the projection of the cap, and one end of the connector is fixed to the first fixing part.

[0009] Furthermore, the base has a ring-shaped structure, with two or more first fixing parts disposed on the inner circumferential surface of the base along the circumference of the base, and the first fixing parts extending toward the center of the base.

[0010] Furthermore, the cap includes a cap body and a cap front plate, the cap front plate is fixed to one end of the cap body near the base, and the other end of the connector is fixed to the cap front plate.

[0011] Furthermore, the fairing is a single-layer structure, and the thickness of the fairing is 0.5mm-15mm.

[0012] Furthermore, the fairing includes two or more through holes, and the total area of ​​the through holes accounts for 20%-80% of the outer peripheral surface area of ​​the fairing.

[0013] Furthermore, it also includes two or more deflectors, which are arranged circumferentially on the inner radial side of the fairing.

[0014] Furthermore, the deflector includes a first deflector portion and a second deflector portion, both of which are annular. The first deflector portion extends axially along the fairing, and the second deflector portion extends radially along the fairing. The second deflector portion is directly or indirectly fixed to the first deflector portion, and the second deflector portion is located on the side of the first deflector portion near the combustion chamber nozzle.

[0015] Furthermore, the radius of curvature of the first deflector is less than or equal to the radius of curvature of the fairing.

[0016] Furthermore, the deflector also includes an arc surface, and the second deflector is fixed to the first deflector via the arc surface. The radius of curvature of the arc surface is less than or equal to the length of the second deflector along the radial direction of the fairing.

[0017] Furthermore, the deflector also includes a support portion, which extends at least partially along the axial direction of the fairing, and both the first deflector portion and the second deflector portion are fixed to the nozzle flange of the combustion chamber via the support portion.

[0018] Furthermore, the base also includes two or more bolt holes and two or more pin holes, wherein the bolt holes and the pin holes are through holes extending along the axial direction of the base, and the two or more bolt holes and the two or more pin holes are arranged along the circumference of the base.

[0019] By applying the above-described technical solution of the present invention, at least the following technical effects are achieved: 1. The combustion chamber nozzle rectification device proposed in this invention has a connecting piece fixed between the base and the cover, which can reduce the diameter of the entire nozzle rectification device, thereby reducing the diameter of the combustion chamber head, and ultimately reducing the volume and weight of the entire gas turbine, thus reducing the cost of the gas turbine.

[0020] 2. The combustion chamber nozzle rectifier proposed in this invention has a single-layer shroud and a deflector arranged circumferentially within the radial direction of the shroud. This not only reduces the diameter of the entire nozzle rectifier but also has a simple structure and is easy to install.

[0021] 3. The combustion chamber nozzle straightening device proposed in this invention has one end of the connector fixed to the cap and the other end fixed to the base, so that there is a certain distance between the cap and the nozzle flange, thereby allowing a large temperature difference between the nozzle flange without generating excessive thermal stress.

[0022] 4. The combustion chamber nozzle rectification device proposed in this invention can make the rectified air flow evenly to the center and peripheral areas of the hood, so that the air distribution ratio entering the peripheral nozzle premixing pipe and the central nozzle premixing pipe meets the design requirements.

[0023] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0024] 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: Figure 1 A schematic diagram of the combustion chamber nozzle rectifier device described in one embodiment is shown; Figure 2 A simplified structural diagram of the combustion chamber nozzle rectifier device described in one embodiment is shown; Figure 3 A cross-sectional view of the combustion chamber nozzle rectifying device described in one embodiment is shown; Figure 4 An installation diagram of the baffle element described in one embodiment is shown; Figure 5 A structural schematic diagram of the base described in one embodiment is shown; Figure 6 An installation diagram of the connector described in one embodiment is shown; Figure 7 A structural schematic diagram of the fairing described in one embodiment is shown; Figure 8 A schematic diagram of the baffle element described in one embodiment is shown.

[0025] Reference numerals: 1. Base; 11. First fixing part; 12. Bolt hole; 13. Pin hole; 2. Connector; 3. End cap; 4. Cover; 41. Front plate of cover; 42. Cover body; 5. Radiator; 6. Bolt; 7. Positioning pin; 8. Flow deflector; 81. First flow deflector; 82. Second flow deflector; 83. Support part; 84. Arc surface; 9. Nozzle flange. Detailed Implementation

[0026] 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.

[0027] The present invention will be further described in detail below with reference to specific embodiments, which should not be construed as limiting the scope of protection claimed by the present invention.

[0028] Example

[0029] According to one aspect of the present invention, a combustion chamber nozzle straightening device is provided, such as... Figure 1-8As shown, the device includes a base 1, a cap 4, a shunting cover 5, and two or more connecting members 2. The base 1 and the cap 4 are located at different axial positions of the rectifier. The two or more connecting members 2 are fixed between the base 1 and the cap 4 along the circumference of the cap 4. In the projection along the axial direction of the cap 4, the projections of the connecting members 2 are all located inside the projection of the cap 4. The shunting cover 5 is fixed along the circumference of the cap 4 to the side of the connecting members 2 away from the axis of the cap 4. Specifically, the combustion chamber nozzle rectifier body is mounted on the end cover 3 via the base 1 and is used to rectify the compressed air entering the combustion chamber from the compressor.

[0030] like Figure 5 As shown, the base 1 includes two or more bolt holes 12 and two or more pin holes 13. Both the bolt holes 12 and the pin holes 13 are through holes extending axially along the base 1, and both are arranged circumferentially along the base 1. Specifically, the pin hole 13 is located between two bolt holes 12, and a bolt 6 and a locating pin 7 are respectively installed in the bolt hole 12 and the pin hole 13. The base 1 is fixed to the end cover 3 by the bolt 6, and the locating pin 7 and the pin hole 13 are used for alignment between the base 1 and the end cover 3.

[0031] like Figure 3 As shown, from one end fixed to the base 1 to the other end fixed to the cap 4, the distance between the connecting member 2 and the axis of the cap 4 on a section perpendicular to the axis of the cap 4 continuously increases. This design allows sufficient space to be reserved for bolt holes 12 and pin holes 13 on the base 1, facilitating the installation and removal of bolts 6 and locating pins 7. Furthermore, this design reduces the diameter of the base 1, thereby reducing the diameter of the entire rectifier.

[0032] Specifically, the connector 2 is prismatic in shape, extending axially along the cap 4. One end is fixed to the cap 4, and the other end is fixed to the base 1, creating a certain distance between the cap 4 and the nozzle flange 9. This allows for a larger temperature difference between the nozzle flange 9 without generating excessive thermal stress. In other embodiments, the connector 2 may also be helical, extending axially along the cap 4.

[0033] like Figure 5As shown, the base 1 includes two or more first fixing parts 11. In the projection along the axial direction of the cap 4, the projections of the first fixing parts 11 are all located inside the projection of the cap 4. One end of the connector 2 is fixed to the first fixing part 11. The base 1 has an annular structure, and two or more first fixing parts 11 are arranged circumferentially on the inner circumferential surface of the base 1, with the first fixing parts 11 extending towards the center of the base 1. Specifically, the first fixing part 11 is a protruding structure higher than the inner circumferential surface of the base 1, and the connector 2 is fixed to the first fixing part 11 by welding.

[0034] In other embodiments, the connector 2 and the first fixing part 11 can also be fixed by bolts. The base 1 can also be a ring structure without the first fixing part 11.

[0035] like Figure 2-3 The cap 4 includes a cap body 42 and a cap front plate 41. The cap front plate 41 is fixed to one end of the cap body 42 near the base 1, and the other end of the connector 2 is fixed to the cap front plate 41. Specifically, the cap front plate 41 is perpendicular to the axial direction of the cap 4, and the outer peripheral surface of the cap front plate 41 is flush with the outer peripheral surface of the cap 4. The other end of the connector 2 is fixed to the cap front plate 41 by welding.

[0036] like Figure 7 As shown, the fairing 5 has a single-layer structure and includes two or more through holes. In this embodiment, the thickness of the fairing 5 is 2 mm, and the total area of ​​the through holes accounts for 50% of the outer peripheral surface area of ​​the fairing 5. In other embodiments, the thickness of the fairing 5 can also be 0.5 mm, 1 mm, 5 mm, 9 mm, 12 mm, and 15 mm, etc., and the total area of ​​the through holes can also account for 20%, 40%, 60%, and 80% of the outer peripheral surface area of ​​the fairing 5, etc.

[0037] The combustion chamber nozzle straightening device further includes two or more deflectors 8, which are arranged radially inside the shroud 5 along its circumference. Further, as... Figure 8 As shown, the deflector 8 includes a first deflector portion 81 and a second deflector portion 82. Both the first deflector portion 81 and the second deflector portion 82 are annular. The first deflector portion 81 extends axially along the shroud 5, and the second deflector portion 82 extends radially along the shroud 5. The second deflector portion 82 is indirectly fixed to the first deflector portion 81 and is located on the side of the first deflector portion 81 near the combustion chamber nozzle.

[0038] Specifically, such as Figure 8As shown, the deflector 8 further includes an arc surface 84, through which the second deflector 82 is fixed to the first deflector 81. The radius of curvature of the arc surface is smaller than the radial length of the second deflector 82 along the fairing 5, and the arc surface 84 protrudes towards the base 1. In other embodiments, the radius of curvature of the arc surface may also be equal to the radial length of the second deflector 82 along the fairing 5. In still some embodiments, the second deflector 82 may be directly fixed to the first deflector 81.

[0039] The radius of curvature of the first deflector 81 is smaller than the radius of curvature of the fairing 5. In other embodiments, the radius of curvature of the first deflector 81 may also be equal to the radius of curvature of the fairing 5.

[0040] Preferably, the distance between the edge of the first deflector 81 extending circumferentially along the fairing 5 and the front plate 41 of the hood is less than 10 mm; the area of ​​the second deflector 82 should cover the gap between the first deflector 81 and the fairing 5 without affecting installation and disassembly.

[0041] The baffle 8 further includes a support 83, which extends at least partially along the axial direction of the shroud 5. Both the first baffle 81 and the second baffle 82 are fixed to the nozzle flange 9 of the combustion chamber via the support 83. Specifically, the nozzle flange 9 is the flange of the peripheral nozzle, and both the first baffle 81 and the second baffle 82 are fixed to the flange of the peripheral nozzle via the support 83. Multiple peripheral nozzles and their premixing pipes are arranged circumferentially around the central nozzle. The premixing pipes of the peripheral nozzles are located radially inside the shroud 4. Compressed air enters the combustion chamber from the compressor, first passing through the shroud 5, where the compressed air flow is rectified through the through-holes of the shroud 5 to ensure uniform and stable airflow. Then, the airflow is deflected by the baffle 8, allowing the air to be more evenly distributed to the center and peripheral areas of the shroud 4 after passing through the shroud 5, thereby ensuring that the air distribution ratio entering the premixing pipes of the peripheral nozzles and the central nozzle meets the design requirements.

[0042] By applying the above-described technical solution of the present invention, at least the following technical effects are achieved: 1. The combustion chamber nozzle rectification device proposed in this invention has a connecting piece fixed between the base and the cover, which can reduce the diameter of the entire nozzle rectification device, thereby reducing the diameter of the combustion chamber head, and ultimately reducing the volume and weight of the entire gas turbine, thus reducing the cost of the gas turbine.

[0043] 2. The combustion chamber nozzle rectifier proposed in this invention has a single-layer shroud and a deflector arranged circumferentially within the radial direction of the shroud. This not only reduces the diameter of the entire nozzle rectifier but also has a simple structure and is easy to install.

[0044] 3. The combustion chamber nozzle straightening device proposed in this invention has one end of the connector fixed to the cap and the other end fixed to the base, so that there is a certain distance between the cap and the nozzle flange, thereby allowing a large temperature difference between the nozzle flange without generating excessive thermal stress.

[0045] 4. The combustion chamber nozzle rectification device proposed in this invention can make the rectified air flow evenly to the center and peripheral areas of the hood, so that the air distribution ratio entering the peripheral nozzle premixing pipe and the central nozzle premixing pipe meets the design requirements.

[0046] The above are merely several specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

[0047] 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.

[0048] 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 nozzle straightening device, comprising a base (1), a cap (4), a straightening shroud (5), and two or more connecting parts (2), characterized in that, The base (1) and the cap (4) are located at different axial positions of the rectifier, and two or more of the connecting pieces (2) are fixed between the base (1) and the cap (4) along the circumference of the cap (4). In the projection along the axial direction of the cap (4), the projection of the connector (2) is located inside the projection of the cap (4), and the fairing (5) is fixed along the circumference of the cap (4) to the side of the connector (2) away from the axis of the cap (4).

2. The combustion chamber nozzle rectifying device according to claim 1, characterized in that, From one end fixed to the base (1) to the other end fixed to the cap (4), the distance between the connector (2) and the axis of the cap (4) on the cross section perpendicular to the axis of the cap (4) continuously increases.

3. The combustion chamber nozzle rectifying device according to claim 1, characterized in that, The base (1) includes two or more first fixing parts (11). In the projection along the axial direction of the cap (4), the projection of the first fixing part (11) is located inside the projection of the cap (4). One end of the connector (2) is fixed to the first fixing part (11).

4. The combustion chamber nozzle rectifying device according to claim 3, characterized in that, The base (1) is a ring structure, and two or more first fixing parts (11) are arranged on the inner circumferential surface of the base (1) along the circumference of the base (1), and the first fixing parts (11) extend toward the center of the base (1).

5. The combustion chamber nozzle rectifying device according to claim 3, characterized in that, The cap (4) includes a cap body (42) and a cap front plate (41). The cap front plate (41) is fixed to one end of the cap body (42) near the base (1), and the other end of the connector (2) is fixed to the cap front plate (41).

6. The combustion chamber nozzle rectifying device according to claim 1, characterized in that, The fairing (5) is a single-layer structure, and the thickness of the fairing (5) is 0.5mm-15mm.

7. The combustion chamber nozzle rectifying device according to claim 6, characterized in that, The fairing (5) includes two or more through holes, and the total area of ​​the through holes accounts for 20%-80% of the outer peripheral surface area of ​​the fairing (5).

8. The combustion chamber nozzle rectifying device according to claim 6, characterized in that, It also includes two or more deflectors (8), which are arranged radially inside the fairing (5) along the circumference of the fairing (5).

9. The combustion chamber nozzle rectifying device according to claim 8, characterized in that, The deflector (8) includes a first deflector (81) and a second deflector (82). Both the first deflector (81) and the second deflector (82) are annular. The first deflector (81) extends axially along the shroud (5), and the second deflector (82) extends radially along the shroud (5). The second deflector (82) is directly or indirectly fixed to the first deflector (81). The second deflector (82) is located on the side of the first deflector (81) near the combustion chamber nozzle.

10. The combustion chamber nozzle rectifying device according to claim 9, characterized in that, The radius of curvature of the first deflector (81) is less than or equal to the radius of curvature of the fairing (5).

11. The combustion chamber nozzle rectifying device according to claim 9, characterized in that, The deflector (8) further includes an arc surface (84), and the second deflector (82) is fixed to the first deflector (81) by the arc surface. The radius of curvature of the arc surface is less than or equal to the length of the second deflector (82) along the radial direction of the fairing (5).

12. The combustion chamber nozzle rectifying device according to claim 9, characterized in that, The deflector (8) further includes a support (83) which extends at least partially along the axial direction of the fairing (5). The first deflector (81) and the second deflector (82) are both fixed to the nozzle flange (9) of the combustion chamber by the support (83).

13. The combustion chamber nozzle rectifying device according to claim 4, characterized in that, The base (1) also includes two or more bolt holes (12) and two or more pin holes (13). The bolt holes (12) and the pin holes (13) are both through holes extending along the axial direction of the base (1). The two or more bolt holes (12) and the two or more pin holes (13) are all arranged along the circumference of the base (1).

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