Combustion chamber and combustion chamber interstage section

Abstract

The application aims to provide a combustion chamber and a combustion chamber interstage section, the combustion chamber interstage section comprising an inner wall body and an outer disc body, the inner wall body being arranged upstream of the outer disc body along a flow direction, the inner wall body and the outer disc body being annular, the inner wall body being connected with the outer disc body through a connecting ring part, the combustion chamber interstage section being provided with outer ring cooling holes, inner ring cooling holes and intermediate cooling holes, the outer ring cooling holes being arranged at the outer edge of the inner wall body along the circumferential direction of the inner wall body, the inner ring cooling holes being arranged through the inner edge of the inner wall body, the connecting ring part and the inner edge of the outer disc body, and the intermediate cooling holes being arranged in the inner wall body between the outer ring cooling holes and the inner ring cooling holes and towards the outer disc body. The angle between the arrangement direction of the outer ring cooling holes and the central axis of the combustion chamber interstage section is an acute angle. The combustion chamber and the combustion chamber interstage section can avoid ablation of the interstage section.

Description

Technical Field

[0001] This invention relates to the field of gas turbine engines, and more particularly to a combustion chamber and an interstage section of the combustion chamber. Background Technology

[0002] With the development of aero-engine technology, the turbine inlet temperature of engines is constantly increasing. Modern aero-engine combustors generally adopt staged combustion technology. The interstage section is located between the main combustion stage and the pre-combustion stage in the combustor. The heat load of its working environment is constantly increasing. How to prevent the interstage section from burning out and ensure its long-term safe service is one of the main challenges in aero-engine combustor design.

[0003] like Figure 1 A schematic diagram of an existing combustor head structure is shown. This combustor head adopts a staged combustion scheme. The head 926 includes a main combustion stage and a pre-combustion stage. The main combustion stage includes a nozzle 915, a swirler assembly, and a main combustion stage channel. The swirler assembly is located within the main combustion stage channel and includes swirlers 921 and 922. The nozzle 915, swirler 921, and second swirler 922 form premixed combustion within the main combustion stage channel. The pre-combustion stage includes a nozzle 914, a swirler assembly, a venturi tube 918, and a pre-combustion stage channel. The swirler assembly is located within the pre-combustion stage channel and includes swirlers 916 and 917. The nozzle 914, swirler 916, and swirler 917 form diffusion combustion within the pre-combustion stage channel. The interstage section 919 is surrounded by both the premixed combustion flame formed by the main combustion stage and the diffusion combustion flame formed by the pre-combustion stage. The interstage section 919 suffers from high heat load and is prone to ablation, making its thermal protection design quite difficult.

[0004] How to provide a configuration that can effectively avoid interstage ablation is a problem that urgently needs to be solved. Summary of the Invention

[0005] The purpose of this invention is to provide an interstage section of a combustion chamber that can prevent interstage section erosion.

[0006] The combustion chamber interstage section for achieving the aforementioned purpose includes: an inner wall body and an outer disc body. The inner wall body is disposed upstream of the outer disc body along the incoming flow direction. The inner wall body and the outer disc body are annular. The inner edge of the inner wall body is connected to the inner edge of the outer disc body through a connecting ring.

[0007] The combustion chamber interstage section is provided with an outer ring cooling hole, an inner ring cooling hole, and a middle cooling hole. The outer ring cooling hole is opened along the circumference of the inner wall body at the outer edge of the inner wall body. The inner ring cooling hole is provided through the inner edge of the inner wall body, the connecting ring portion, and the inner edge of the outer disc body. The middle cooling hole is opened in the inner wall body between the outer ring cooling hole and the inner ring cooling hole, and faces the outer disc body.

[0008] The outer ring cooling holes are arranged at an acute angle to the central axis of the combustion chamber interstage section.

[0009] In one or more embodiments, an annular groove is defined between the inner wall body, the outer disc body, and the connecting ring portion in the combustion chamber interstage section, and the intermediate cooling hole communicates with the annular groove to allow airflow to be ejected from the annular groove toward the outer disc body.

[0010] In one or more embodiments, the acute angle allows the airflow ejected from the outer ring cooling holes to cover the outer edge of the outer disk.

[0011] In one or more embodiments, the intermediate cooling hole comprises multiple rings, which are radially spaced between the outer ring cooling hole and the inner ring cooling hole along the inner wall.

[0012] In one or more embodiments, adjacent rings of the intermediate cooling holes are staggered along the circumference of the inner wall.

[0013] In one or more embodiments, the inner ring cooling hole has a section with a gradually narrowing inner diameter along the incoming flow direction.

[0014] In one or more embodiments, along the flow direction, the inner ring cooling hole has a first section, a second section and a third section in sequence, the inner diameter of the second section is larger than the inner diameter of the first section, and the inner diameter of the third section gradually decreases from the second section outward along the flow direction.

[0015] In one or more embodiments, along the incoming flow direction, the inner ring cooling hole has a section that is inclined inward toward the central axis of the combustion chamber interstage section.

[0016] In one or more embodiments, along the incoming flow direction, the inner ring cooling holes are inclined inward toward the central axis of the combustion chamber interstage section, and the inner ring cooling holes have a section with a gradually narrowing inner diameter.

[0017] On the other hand, according to some embodiments of this application, a combustion chamber is also provided, which includes a main combustion stage swirler, a pre-combustion stage swirler, and the aforementioned interstage section;

[0018] Along the incoming flow direction, the upstream outer side of the interstage section corresponds to the main combustion stage cyclone, and the upstream inner side of the interstage section corresponds to the pre-combustion stage cyclone.

[0019] The beneficial effects of this invention are as follows:

[0020] The interstage section of the combustion chamber with this configuration employs a thermal protection structure composed of outer ring cooling holes, inner ring cooling holes, and intermediate cooling holes. Thermal protection is achieved by forming cooling air walls near both the outer and inner rings of the interstage section. Furthermore, combined with purging and cooling of the outer disc, this comprehensive thermal protection structure, working from the outside in, provides excellent thermal protection, reducing the thermal load on the interstage section and preventing fuel entrainment near the outer and inner rings, which could cause ablation. Simultaneously, the impact cooling system lowers the overall wall temperature of the interstage section, extending its service life.

[0021] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0022] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0023] Figure 1 A schematic diagram of the existing combustion chamber head structure is shown;

[0024] Figure 2 A schematic diagram of a combustion chamber according to some embodiments of this application is shown;

[0025] Figure 3 A front view diagram according to the first embodiment of the combustion chamber interstage section is shown;

[0026] Figure 4 It shows Figure 3 A cross-sectional view obtained by cutting along the AA direction;

[0027] Figure 5 It shows Figure 4 A magnified view of part B;

[0028] Figure 6 A side view diagram according to the first embodiment of the interstage section of this combustion chamber is shown;

[0029] Figure 7 It shows Figure 6 A cross-sectional view obtained by cutting along the CC direction;

[0030] Figure 8 A cross-sectional schematic diagram according to the second embodiment of the combustion chamber interstage section is shown;

[0031] Figure 9 It shows Figure 8 A magnified schematic diagram of part D. Detailed Implementation

[0032] The embodiments of the technical solution of this application will now be described in detail with reference to the accompanying drawings. These embodiments are only used to more clearly illustrate the technical solution of this application and are therefore merely examples, and should not be used to limit the scope of protection of this application.

[0033] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.

[0034] To avoid the problem of interstage erosion in the combustion chamber, on the one hand, according to some embodiments of this application, a combustion chamber is provided, such as... Figure 2 A schematic diagram of a combustion chamber according to some embodiments of this application is shown. The combustion chamber includes a main combustion stage swirler 101, a pre-combustion stage swirler 102, and an interstage section 100. Along the incoming flow direction a, the upstream outer side of the interstage section 100 corresponds to the main combustion stage swirler 101, and the upstream inner side of the interstage section 100 corresponds to the pre-combustion stage swirler 102. It is understood that the incoming flow direction a refers to the flow direction of the airflow in the combustion chamber when the engine is in operation. As shown in the figure, the outlet airflow 51 of the main combustion stage cyclone separator 101, after premixing with the fuel injected by the nozzle, forms an outer high-temperature low-speed recirculation zone 52 downstream of the interstage section. The outlet airflow 61 of the pre-combustion stage cyclone separator 102, after mixing with the fuel injected by the nozzle, forms an inner high-temperature low-speed recirculation zone 62 downstream of the interstage section. When the equivalence ratio between the main combustion stage cyclone separator 101 and the pre-combustion stage cyclone separator 102 is large, some fuel may not be completely burned in some areas. The presence of the outer high-temperature low-speed recirculation zone 52 and the inner high-temperature low-speed recirculation zone 51 will entrain some unburned fuel into the low-speed recirculation zone, exacerbating the risk of ablation near the interstage section.

[0035] In order to solve the aforementioned problems, on the other hand, according to some embodiments of this application, a combustion chamber stage section is also provided. Figure 3 A front schematic diagram according to the first embodiment of the combustion chamber interstage section is shown. Figure 4 It shows Figure 3 A schematic cross-sectional view obtained by cutting along the AA direction. Figure 5 It shows Figure 4 A magnified view of part B. Figure 6 A side view diagram according to the first embodiment of the interstage section of this combustion chamber is shown. Figure 7 It shows Figure 6 A cross-sectional view obtained by cutting along the CC direction.

[0036] Please refer to the above. Figures 2 to 6 According to some embodiments of this combustion chamber interstage section 100, the combustion chamber interstage section 100 includes: an inner wall body 1 and an outer disc body 2. The inner wall body 1 is disposed upstream of the outer disc body 2 along the incoming flow direction a. Both the inner wall body 1 and the outer disc body 2 are annular. The inner edge of the inner wall body 1 is connected to the inner edge of the outer disc body 2 through a connecting ring 3. It can be understood that the inner edge of the inner wall body 1 refers to the disc rim area around the inner ring of the inner wall body 1, and the outer edge of the inner wall body 1 refers to the disc rim area around the outer ring of the inner wall body 1. Similarly, the inner edge of the outer disc body 2 refers to the disc rim area around the inner ring of the outer disc body 2, and the outer edge of the outer disc body 2 refers to the disc rim area around the outer ring of the outer disc body 2.

[0037] The combustion chamber stage section 100 is provided with an outer ring cooling hole 11, an inner ring cooling hole 12, and an intermediate cooling hole 13. The outer ring cooling hole 11 is formed along the circumference of the inner wall 1 at the outer edge of the inner wall 1. The inner ring cooling hole 12 passes through the inner edge of the inner wall 1, the connecting ring 3, and the inner edge of the outer disc 2. The intermediate cooling hole 13 is formed in the inner wall 1 between the outer ring cooling hole 11 and the inner ring cooling hole 12, and faces the outer disc 2, so that the gas blown out from the intermediate cooling hole 13 can impact the outer disc 2.

[0038] Among them, such as Figure 5 As shown, the opening direction of the outer ring cooling hole 11 forms an acute angle x with the central axis of the combustion chamber interstage section 100.

[0039] like Figure 2 As shown, when the airflow is blown out from the angled outer ring cooling hole 11, a cooling air film can be formed near the outer ring of the interstage section, blocking the high-temperature backflow combustion gas from the main combustion stage and reducing the wall temperature of the outer ring of the interstage section. At the same time, the outer ring swirling airflow 7 blown out from the outer ring cooling hole 11 can effectively blow away unburned fuel near the outer ring of the interstage section, preventing the fuel in the high-temperature, low-speed backflow zone 52 of the outer ring from being entrained to the outer ring of the interstage section for combustion and thus preventing the outer ring of the interstage section from burning.

[0040] When the airflow blows out from the central cooling hole 13, the impact airflow 8 can impact and cool the outer plate 2, thereby reducing the wall temperature of the outer plate 2.

[0041] The inner ring purge airflow 9 blown out from the inner ring cooling hole 12 can form an inner ring cooling air wall, which blocks the high-temperature backflow of pre-combustion stage gas and reduces the inner ring wall temperature of the interstage section. The high-speed airflow at the outlet formed by the inner ring purge airflow 9 can prevent fuel in the high-temperature low-speed backflow zone 62 of the inner ring from being entrained into the inner ring of the interstage section, thus preventing the inner ring of the interstage section from being burned.

[0042] The interstage section of the combustion chamber with the aforementioned configuration employs a thermal protection structure composed of outer ring cooling holes 11, inner ring cooling holes 12, and intermediate cooling holes 13. Thermal protection is achieved by forming cooling air walls near both the outer and inner rings of the interstage section. Furthermore, combined with purging and cooling of the outer disc 2, this comprehensive thermal protection structure, working from the outside in, provides excellent thermal protection, reducing the thermal load on the interstage section and preventing fuel entrainment near the outer and inner rings, which could cause ablation. Simultaneously, the impact cooling system reduces the overall wall temperature of the interstage section, extending its service life.

[0043] In the description of the embodiments of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0044] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0045] In some embodiments of this combustion chamber interstage section, such as Figure 5 As shown, an annular groove 4 is defined in the combustion chamber stage section 100 between the inner wall body 1, the outer disc body 2, and the connecting ring 3. The intermediate cooling hole 13 communicates with the annular groove 4 to allow airflow to be ejected towards the outer disc body in the annular groove 4.

[0046] In some embodiments of this combustion chamber interstage section, the size of the acute angle x allows the airflow ejected from the outer ring cooling holes 11 to cover the outer edge of the outer disc 2, thereby ensuring that a cooling gas film is formed on the outer ring of the interstage section, blocking the high-temperature backflow combustion gas of the main combustion stage, reducing the wall temperature of the outer ring of the interstage section, and effectively preventing unburned fuel from being entrained to the outer ring of the interstage section for combustion, thus preventing the outer ring of the interstage section from being burned.

[0047] In some embodiments of this combustion chamber interstage section, such as Figure 7 As shown, the intermediate cooling hole 13 includes multiple rings, and the multiple rings of intermediate cooling holes 13 are radially spaced between the outer ring cooling hole 11 and the inner ring cooling hole 12, thereby improving the impact cooling effect on the outer plate 2 through the multiple rings of intermediate cooling holes 13.

[0048] In some embodiments of this combustion chamber interstage section, such as Figure 7 As shown, the intermediate cooling holes 13 of two adjacent rings are staggered along the circumference of the inner wall 1. This arrangement allows the impact cooling airflow blown out from the intermediate cooling holes 13 to cover the entire outer plate 2, thereby further improving the impact cooling effect on the outer plate 2.

[0049] In some embodiments of this combustion chamber interstage section, such as Figure 5 As shown, along the incoming flow direction, the inner ring cooling hole 12 has a section with a gradually narrowing inner diameter, that is, the inner ring cooling hole 12 is in a constricted shape, which can increase the flow rate of the cooling airflow ejected from the inner ring cooling hole 12, thereby forming an inner ring cooling air wall more effectively and quickly, blocking the high-temperature backflow combustion gas of the pre-combustion stage. At the same time, the faster flow rate can more effectively prevent the fuel in the high-temperature low-speed backflow zone 62 from being entrained into the inner ring of the interstage section, thus improving the protection effect against the ablation of the inner ring of the interstage section.

[0050] Furthermore, such as Figure 5 As shown, along the incoming flow direction a, the inner ring cooling hole 12 has a first section 121, a second section 122 and a third section 123 in sequence. The inner diameter of the second section 122 is larger than the inner diameter of the first section 121. The inner diameter of the third section 123 gradually decreases from the second section 122 outward along the incoming flow direction a, thereby forming a nozzle structure that is easy to generate a large airflow velocity at the outlet of the inner ring cooling hole 12.

[0051] Figure 8 A cross-sectional schematic diagram according to the second embodiment of the combustion chamber interstage section is shown. Figure 9 It shows Figure 8 A magnified schematic diagram of part D.

[0052] like Figure 9 In the second embodiment shown, the configurations of the inner wall 1', outer disk 2', and connecting ring 3' are the same as in the first embodiment. Similarly, the configurations of the outer cooling hole 11' and the intermediate cooling hole 13' are also the same as in the first embodiment. The difference between the second and first embodiments is that, along the flow direction a, the inner cooling hole 12' has a section 121' that is inclined inward toward the central axis of the interstage section of the combustion chamber. This inwardly inclined section 121' allows the airflow ejected from the inner cooling hole 12' to counteract and isolate the high-temperature, low-speed backflow zone 62 of the inner ring, keeping it away from the wall of the outer disk 2' and preventing ablation of the inner ring of the interstage section.

[0053] In another embodiment different from that shown in the figure, the first embodiment and the second embodiment can be combined. For example, the inner ring cooling hole can be opened inwardly towards the central axis of the interstage section of the combustion chamber, and the inner ring cooling hole has a section with a gradually narrowing inner diameter, thereby further improving the effect of preventing the ablation of the inner ring of the interstage section.

[0054] In the description of the embodiments of this application, technical terms such as "first" and "second" are used only to distinguish different objects and should not be construed as indicating or implying relative importance or implicitly indicating the number, specific order, or primary and secondary relationship of the indicated technical features.

[0055] In the description of the embodiments of this application, unless otherwise expressly specified and limited, technical terms such as "installation," "connection," "joining," and "fixing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in the embodiments of this application can be understood according to the specific circumstances.

[0056] It should be understood that the use of "along" in the text means that there is at least a component in that direction, preferably, the angle with that direction is within 10°, more preferably, the angle is within 5°.

[0057] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and not to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application, and they should all be covered within the scope of the claims and specification of this application. In particular, as long as there is no structural conflict, the various technical features mentioned in the embodiments can be combined in any way. This application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A combustion chamber interstage section, characterized in that, include: The inner wall body and the outer disc body are arranged upstream of the outer disc body along the incoming flow direction. The inner wall body and the outer disc body are annular. The inner edge of the inner wall body is connected to the inner edge of the outer disc body through a connecting ring. The combustion chamber interstage section is provided with an outer ring cooling hole, an inner ring cooling hole, and a middle cooling hole. The outer ring cooling hole is opened along the circumference of the inner wall body at the outer edge of the inner wall body, and blows out an outer ring swirling airflow. The inner ring cooling hole is disposed through the inner edge of the inner wall body, the connecting ring portion, and the inner edge of the outer disc body. The middle cooling hole is opened in the inner wall body between the outer ring cooling hole and the inner ring cooling hole, and faces the outer disc body. The outer ring cooling holes are arranged at an acute angle to the central axis of the combustion chamber interstage section, and the acute angle allows the airflow ejected from the outer ring cooling holes to cover the outer edge of the outer disc. The inner ring cooling hole has a first section, a second section and a third section in sequence. The inner diameter of the second section is larger than the inner diameter of the first section, and the inner diameter of the third section gradually decreases from the second section outward along the flow direction.

2. The combustion chamber interstage section as described in claim 1, characterized in that, The inner wall, the outer disc, and the connecting ring define an annular groove in the combustion chamber stage section, and the intermediate cooling hole communicates with the annular groove to allow airflow to be ejected from the annular groove toward the outer disc.

3. The combustion chamber interstage section as described in claim 1, characterized in that, The intermediate cooling hole comprises multiple rings, which are radially spaced between the outer ring cooling hole and the inner ring cooling hole along the inner wall.

4. The combustion chamber interstage section as described in claim 1, characterized in that, The intermediate cooling holes in two adjacent rings are staggered along the circumference of the inner wall.

5. The interstage section of the combustion chamber as described in claim 1, characterized in that, Along the flow direction, the inner ring cooling hole has a section with a gradually narrowing inner diameter.

6. The interstage section of the combustion chamber as described in claim 1, characterized in that, Along the flow direction, the inner ring cooling hole has a section that is inclined inward toward the central axis of the combustion chamber interstage section.

7. The combustion chamber interstage section as described in claim 1, characterized in that, Along the flow direction, the inner ring cooling holes are inclined inward toward the central axis of the combustion chamber interstage section, and the inner ring cooling holes have a section with a gradually narrowing inner diameter.

8. A combustion chamber, characterized in that, Includes a main combustion stage cyclone separator, a pre-combustion stage cyclone separator, and an interstage section as described in any one of claims 1 to 7; Along the incoming flow direction, the upstream outer side of the interstage section corresponds to the main combustion stage cyclone, and the upstream inner side of the interstage section corresponds to the pre-combustion stage cyclone.

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