Flame tube, combustion chamber and gas turbine engine

Abstract

The present invention belongs to the field of gas turbine engines, and specifically relates to a flame tube, a combustion chamber, and a gas turbine engine. A flame tube of a gas turbine engine includes an inner annular wall and an outer annular wall, wherein the inner annular wall is disposed within the outer annular wall, and a combustion chamber is formed between the inner annular wall and the outer annular wall; the outer surface of the inner annular wall and / or the outer surface of the outer annular wall are provided with a boss structure, and the boss structure is used to increase the heat dissipation area of the outer surface of the inner annular wall and / or the outer surface of the outer annular wall. The present invention increases the outer surface area of the flame tube (increases the heat dissipation area) by designing a boss on the outer surface of the flame tube, thereby improving the heat dissipation and combustion effects of the flame tube, and has the advantage of increasing the service life of the flame tube and the engine.

Description

Technical Field

[0001] The present invention belongs to the field of gas turbine engines, and in particular relates to a flame tube and a combustion chamber of a gas turbine engine and the gas turbine engine. Background Art

[0002] A gas turbine engine, also known as a gas turbine, is a type of heat engine. The term "gas turbine" is used broadly to refer to a wide range of engines, including gas turbine jet engines, which share similar principles.

[0003] A gas turbine engine consists of three core components: a compressor, a combustion chamber, and a turbine. The combustion chamber includes a flame tube where the gas burns, so the flame tube needs to have a good heat dissipation effect. The heat dissipation effect of the flame tube seriously affects its combustion efficiency and service life, which in turn affects the service life of the engine.

[0004] In order to increase the service life of the flame tube and the engine, the present invention is proposed. Summary of the Invention

[0005] In order to solve the technical problems existing in the prior art, the present invention provides a flame tube, a combustion chamber and a gas turbine engine of a gas turbine engine. The present invention increases the outer surface area of the flame tube (increases the heat dissipation area) by designing a boss on the outer surface of the flame tube, thereby improving the heat dissipation effect and combustion effect of the flame tube, and has the advantage of increasing the service life of the flame tube and the engine.

[0006] The present invention includes the following technical solutions:

[0007] A first aspect of the present invention provides a flame tube of a gas turbine engine, comprising an inner annular wall and an outer annular wall, wherein the inner annular wall is arranged inside the outer annular wall, and a combustion chamber is formed between the inner annular wall and the outer annular wall; the outer surface of the inner annular wall and / or the outer surface of the outer annular wall is provided with a boss structure, and the boss structure is used to increase the heat dissipation area of the outer surface of the inner annular wall and / or the outer surface of the outer annular wall.

[0008] Furthermore, the boss structure includes a first boss and a second boss of different shapes, and the first boss and the second boss are spaced apart.

[0009] Furthermore, the first boss is circumferentially arranged on the outer surface of the inner ring wall and / or the outer surface of the outer ring wall; the second boss is serrated, and the second boss is circumferentially arranged on the outer surface of the inner ring wall and / or the outer surface of the outer ring wall; in the axial direction of the flame tube, the second boss is connected between two adjacent first bosses, and the first boss is connected between two adjacent second bosses.

[0010] Furthermore, when the outer surface of the inner ring wall is provided with a boss structure, a heat dissipation hole is opened on the inner ring wall between two adjacent first bosses.

[0011] Furthermore, when the outer surface of the outer ring wall is provided with a boss structure, a heat dissipation hole is opened on the outer ring wall between two adjacent first bosses; and / or when the outer surface of the inner ring wall is provided with a boss structure, a heat dissipation hole is opened on the inner ring wall between two adjacent first bosses.

[0012] Further, the first boss is provided with a first inner cavity, and the first boss is also provided with a first air inlet hole for allowing gas to enter the first inner cavity; the gas entering the first inner cavity can enter the combustion chamber through the first diverging hole; and / or the second boss is provided with a second inner cavity, and the second boss is also provided with a second air inlet hole for allowing gas to enter the second inner cavity; the gas entering the second inner cavity can enter the combustion chamber through the second diverging hole.

[0013] Further, when the first boss is provided with a first air inlet hole, the first air inlet hole includes a first impact hole and a first small hole, the first impact hole is provided on the top wall of the first boss, and the first small hole is provided on the side wall of the first boss.

[0014] Further, when the second boss is provided with a second air inlet hole, the second air inlet hole includes a second impact hole and a second small hole, the second impact hole is provided on the top wall of the second boss, and the second small hole is provided on the side wall of the second boss.

[0015] A second aspect of the present invention provides a combustion chamber of a gas turbine engine, comprising the flame tube described above.

[0016] A third aspect of the present invention provides a gas turbine engine comprising an air inlet, a compressor, the combustion chamber and the tail nozzle connected in sequence.

[0017] By adopting the above technical solution, the present invention has the following advantages:

[0018] 1. The present invention increases the outer surface area of the flame tube (increases the heat dissipation area) by designing a boss on the outer surface of the flame tube, thereby improving the heat dissipation effect and combustion effect of the flame tube, and has the advantage of increasing the service life of the flame tube and the engine.

[0019] 2. Based on the conventional divergent cooling flame tube, the present invention designs a boss structure, which not only enhances the rigidity of the flame tube, but also increases the surface area of the flame tube, thereby enhancing the surface area heat exchange, so that the flame tube wall (inner ring wall and / or outer ring wall) can be quickly cooled, which has the advantage of increasing the service life of the flame tube and the engine.

[0020] 3. Due to the provision of a boss structure, the present invention can make the flame tube wall (inner ring wall and / or outer ring wall) thinner compared with the conventional divergent cooling flame tube, which not only reduces the weight of the flame tube and has the advantage of improving the power-to-weight ratio of the engine; but also reduces the use of materials and reduces costs.

[0021] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or will be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0023] Figure 1 Schematic diagram of the structure of a flame tube of a gas turbine engine according to an embodiment of the present invention;

[0024] Figure 2 A schematic diagram of the partial structure of the outer ring wall in an embodiment of the present invention;

[0025] Figure 3 Schematic diagram of the local structure of the inner ring wall in an embodiment of the present invention;

[0026] Figure 4 is a cross-sectional view of the first boss in an embodiment of the present invention;

[0027] Figure 5 for Figure 4 AA section view;

[0028] Figure 6 is a cross-sectional view of the second boss in an embodiment of the present invention;

[0029] Figure 7 for Figure 6 BB cross-sectional view;

[0030] In the figure, 10-inner annular wall, 20-outer annular wall, 30-boss structure, 31-first boss, 311-first inner cavity, 312-first air inlet, 3121-first impact hole, 3122-first small hole, 313-first diverging hole, 32-second boss, 321-second inner cavity, 322-second air inlet, 3221-second impact hole, 3222-second small hole, 323-second diverging hole, 40-heat dissipation hole, 50-vortex finder. DETAILED DESCRIPTION

[0031] The following description provides many different embodiments or examples for implementing different features of the present invention. The components and arrangements described in the following specific examples are only used to simplify the present invention and are only used as examples, not to limit the present invention.

[0032] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0033] A first aspect of this embodiment provides a flame tube of a gas turbine engine, such as Figure 1 As shown, it includes an inner annular wall 10 and an outer annular wall 20, wherein the inner annular wall 10 is arranged inside the outer annular wall 20, and a combustion chamber is formed between the inner annular wall 10 and the outer annular wall 20; the outer surface of the inner annular wall 10 and / or the outer surface of the outer annular wall 20 is provided with a boss structure 30, and the boss structure 30 is used to increase the heat dissipation area of the outer surface of the inner annular wall 10 and / or the outer surface of the outer annular wall 20.

[0034] It should be noted that the present invention increases the heat dissipation area by providing a boss structure 30, thereby improving the heat dissipation effect; and for the flame tube, it includes an inner ring wall 10 and an outer ring wall 20, so the boss structure 30 can be provided only on the inner ring wall 10 or the outer ring wall 20; and when the boss structure 30 is provided on both the inner ring wall 10 and the outer ring wall 20, the heat dissipation area is further increased compared to the case where the boss structure 30 is provided only on the inner ring wall 10 or the outer ring wall 20, which has the advantage of further improving the heat dissipation effect.

[0035] Furthermore, if Figure 1 As shown, a swirler 50 is further provided at the inlet end of the flame tube.

[0036] In some embodiments, as Figure 2 、 Figure 3 As shown, the boss structure 30 includes a first boss 31 and a second boss 32 of different shapes, and the first boss 31 and the second boss 32 are spaced apart. Figure 3 As shown, a second boss 32 is provided between any two adjacent first bosses 31 , and a first boss 31 is provided between any two adjacent second bosses 32 .

[0037] In order to further increase the heat dissipation area and improve the strength of the flame tube wall, in some embodiments, such as Figure 3 As shown, the first boss 31 is circumferentially arranged on the outer surface of the inner annular wall 10 and / or the outer surface of the outer annular wall 20; the second boss 32 is zigzag-shaped, and the second boss 32 is circumferentially arranged on the outer surface of the inner annular wall 10 and / or the outer surface of the outer annular wall 20; in the axial direction of the flame tube, the second boss 32 is connected between two adjacent first bosses 31, and the first boss 31 is connected between two adjacent second bosses 32. By designing the position and shape of the first boss 31 and the second boss 32, on the one hand, due to their good symmetry, they are easier to manufacture (such as they can be manufactured by 3D printing), thereby reducing manufacturing costs; another invention is that such a reasonable layout of the first boss 31 and the second boss 32 can make greater use of the wall surface of the flame tube, thereby improving the heat dissipation effect of the flame tube, which has the advantage of increasing the service life of the flame tube and the service life of the engine.

[0038] like Figure 3 As shown, the two opposite sides of the sawtooth-shaped second boss 32 have raised tooth-like structures, and the second boss 32 is connected to the first bosses 31 on both sides through the tooth-like structures; such a structure of the second boss 32 can not only further increase the heat dissipation area, but also further increase the strength of the flame tube wall.

[0039] Since the airflow enters the flame tube through the wall surface of the flame tube (the inner ring wall 10 and the outer ring wall 20), the airflow can not only dissipate heat for the flame tube, but also participate in combustion; in the case where the boss structure 30 is provided, the airflow can enter the flame tube through the heat dissipation holes 40 provided on the inner ring wall 10 and the outer ring wall 20. Specifically, in some embodiments, such as Figure 3 As shown, when the outer surface of the inner ring wall 10 is provided with a boss structure 30, a heat dissipation hole 40 is opened on the inner ring wall 10 between two adjacent first bosses 31; and / or when the outer surface of the outer ring wall 20 is provided with a boss structure 30, a heat dissipation hole 40 is opened on the outer ring wall 20 between two adjacent first bosses 31.

[0040] On the flame tube provided with the boss structure 30, since the boss has a reverse effect on the airflow, the airflow will form a angular vortex at the boss structure 30 (such as Figure 5 、 Figure 7 As shown), it will affect the forward flow of the airflow. On the one hand, it will reduce the airflow entering through the heat dissipation hole 40, which is not conducive to the cooling of the flame tube; on the other hand, it will also affect the continuous entry of the front airflow, affecting the combustion of the flame tube. Therefore, in some embodiments, as shown Figure 4As shown, the first boss 31 is provided with a first inner cavity 311, and the first boss 31 is also provided with a first air inlet 312 for gas to enter the first inner cavity 311; the gas entering the first inner cavity 311 can enter the combustion chamber through the first diffusion hole 313. And / or Figure 6 As shown, the second boss 32 is provided with a second inner cavity 321 and a second air inlet hole 322 for allowing gas to enter the second inner cavity 321. The gas entering the second inner cavity 321 can enter the combustion chamber through the second diverging holes 323. In some embodiments, this arrangement not only improves the airflow entering through the outer annular wall 20 and the inner annular wall 10 of the flame tube, but also reduces the formation of corner vortices.

[0041] By designing the first boss 31 and the second boss 32 to allow the airflow to enter the flame tube, the flow rate of the incoming airflow can be increased and the formation of the corner vortex can be reduced, but there is still a large corner vortex effect. Figure 5 As shown, the first air inlet 312 includes a first impact hole 3121 and a first small hole 3122, the first impact hole 3121 is provided on the top wall of the first boss 31, and the first small hole 3122 is provided on the side wall of the first boss 31. And / or as Figure 7 As shown, the second air inlet 322 includes a second impact hole 3221 and a second small hole 3222. The second impact hole 3221 is provided on the top wall of the second boss 32, and the second small hole 3222 is provided on the side wall of the second boss 32. By providing the first small hole 3122 on the side wall of the first boss 31 and the second small hole 3222 on the side wall of the second boss 32, the formation of corner vortices can be further prevented, the airflow rate entering the flame tube can be further increased, and the heat dissipation effect of the flame tube can be further improved.

[0042] In some embodiments, the first inner cavity 311 and the second inner cavity 321 are connected; the connection of the cavities can increase the flow of air inside the cavity, thereby enhancing the heat exchange between the airflow and the cavity wall.

[0043] In some embodiments, the first impact holes 3121 and the first diverging holes 313 are arranged in a staggered arrangement; it can be understood that, Figure 4 As shown, the gas entering the first inner cavity 311 from the first impact holes 3121 is distributed between the inlets of adjacent first diffusion holes 313 .

[0044] In some embodiments, the first impact holes 3121 and the first diverging holes 313 are arranged in a staggered arrangement; it can be understood that, Figure 4As shown, the gas entering the first inner cavity 311 from the first impact hole 3121 is distributed between the inlets of adjacent first diffusion holes 313. Figure 4 As shown, the first impact hole 3121 is vertically arranged, and the first diverging hole 313 is inclined.

[0045] In some embodiments, the second impact holes 3221 and the second diverging holes 323 are arranged in a staggered arrangement; it can be understood that, Figure 4 As shown, the gas entering the second inner cavity 321 from the second impact hole 3221 is distributed between the inlets of adjacent second diffusion holes 323. Figure 6 As shown, the second impact hole 3221 is vertically arranged, and the second diverging hole 323 is inclinedly arranged.

[0046] It should be noted that the first diverging holes 313 and the second diverging holes 323 are preferably directly opened on the inner ring wall 10 and / or the outer ring wall 20 of the flame tube, which can reduce the height of the first boss 31 and the second boss 32, reduce the use of materials, and reduce manufacturing costs.

[0047] In some embodiments, when the outer surface of the inner annular wall 10 is provided with a boss structure 30, the inner annular wall 10 and the boss structure 30 are integrally formed; and / or when the outer surface of the outer annular wall 20 is provided with a boss structure 30, the outer annular wall 20 and the boss structure 30 are integrally formed. This has the advantages of further improving the wall strength of the flame tube and reducing the manufacturing difficulty.

[0048] A second aspect of this embodiment provides a combustion chamber of a gas turbine engine, comprising the flame tube described above.

[0049] A third aspect of this embodiment provides a gas turbine engine, comprising an air inlet, a compressor, the combustion chamber and the tail nozzle as described above, which are connected in sequence.

[0050] In the description of the present invention, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features indicated. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of the specified features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0051] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they may refer to fixed, detachable, or integral connections; mechanical, electrical, or intercommunication connections; direct or indirect connections through an intermediary; and may encompass internal connectivity between multiple components or interactions between multiple components. Those skilled in the art will understand the specific meanings of these terms in the present invention based on specific circumstances.

[0052] In the description of the present invention, it should be understood that all terms used to indicate orientation or positional relationships are based on the orientation or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and cannot be understood as a limitation on the present invention.

[0053] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A flame tube of a gas turbine engine, characterized in that: The invention comprises an inner annular wall (10) and an outer annular wall (20), wherein the inner annular wall (10) is arranged inside the outer annular wall (20), and a combustion chamber is formed between the inner annular wall (10) and the outer annular wall (20); a first boss (31) and a second boss (32) of different shapes are provided on the outer surface of the inner annular wall (10) and / or the outer surface of the outer annular wall (20); The first boss (31) and the second boss (32) are spaced apart, and the tooth structures on opposite sides of the sawtooth-shaped second boss (32) are respectively connected to the first bosses (31) on both sides; the first boss (31) is circumferentially arranged on the outer surface of the outer annular wall (20) and / or the inner annular wall (10); The second boss (32) is circumferentially arranged on the outer surface of the outer annular wall (20) and / or the inner annular wall (10); The first boss (31) is provided with a first inner cavity (311), and the first boss (31) is further provided with a first impact hole (3121) and a first small hole (3122) for allowing gas to enter the first inner cavity (311). The gas entering the first inner cavity (311) can enter the combustion chamber through the first diverging hole (313); the first impact hole (3121) is provided on the top wall of the first boss (31), and the first small hole (3122) is provided on the side wall of the first boss (31).

2. The flame tube of a gas turbine engine according to claim 1, characterized in that: The first boss (31) is circumferentially arranged on the outer surface of the inner ring wall (10); and the second boss (32) is circumferentially arranged on the outer surface of the inner ring wall (10).

3. The flame tube of a gas turbine engine according to claim 2, characterized in that: When the outer surface of the inner ring wall (10) is provided with a boss structure (30), a heat dissipation hole (40) is opened on the inner ring wall (10) between two adjacent first bosses (31).

4. The flame tube of a gas turbine engine according to claim 2, characterized in that: When the outer surface of the outer ring wall (20) is provided with a boss structure (30), a heat dissipation hole (40) is opened on the outer ring wall (20) between two adjacent first bosses (31); and / or when the outer surface of the inner ring wall (10) is provided with a boss structure (30), a heat dissipation hole (40) is opened on the inner ring wall (10) between two adjacent first bosses (31).

5. A flame tube of a gas turbine engine according to any one of claims 1 to 4, characterized in that: The second boss (32) is provided with a second inner cavity (321), and the second boss (32) is further provided with a second air inlet (322) for allowing gas to enter the second inner cavity (321); the gas entering the second inner cavity (321) can enter the combustion chamber through the second diffusion hole (323).

6. The flame tube of a gas turbine engine according to claim 5, characterized in that: When the second boss (32) is provided with a second air inlet hole (322), the second air inlet hole (322) comprises a second impact hole (3221) and a second small hole (3222), the second impact hole (3221) being provided on the top wall of the second boss (32), and the second small hole (3222) being provided on the side wall of the second boss (32).

7. A combustion chamber of a gas turbine engine, characterized in that: The flame tube comprises the flame tube according to any one of claims 1 to 6.

8. A gas turbine engine, characterized in that: It comprises an air inlet, a compressor, a combustion chamber as claimed in claim 7 and a tail nozzle which are connected in sequence.

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