Combustion chamber and interstage section of combustion chamber

Abstract

The invention aims at providing a combustion chamber and a combustion chamber interstage section, the combustion chamber interstage section comprises an inner wall body and an outer disc body, the inner wall body is arranged on the upstream of the outer disc body in the incoming flow direction, the inner wall body and the outer disc body are annular, the inner wall body is connected with the outer disc body through a connecting ring part, and the outer disc body is connected with the inner wall body. An outer ring cooling hole, an inner ring cooling hole and a middle cooling hole are formed in the combustion chamber interstage section, the outer ring cooling hole is formed in the outer edge of the inner wall body in the circumferential direction of the inner wall body, and the inner ring cooling hole penetrates through the inner edge of the inner wall body, the connecting ring part and the inner edge of the outer disc body. The middle cooling holes are formed in the inner wall body between the outer ring cooling holes and the inner ring cooling holes and face the outer disc body. An acute included angle is formed between the forming direction of the outer ring cooling holes and the central axis of the combustion chamber interstage section. According to the combustion chamber and the combustion chamber interstage section, interstage section ablation can be avoided.

Description

Technical Field

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

[0002] With the development of aircraft engine technology, the temperature before the engine turbine continues to increase. The staged combustion technology is generally used in the combustion chamber head of modern aircraft engines. The interstage section is located between the main combustion stage and the pre-combustion stage of the combustion chamber. The heat load of its working environment continues to increase. How to prevent the ablation problem of the interstage section and ensure its long-term safe service is one of the main challenges in the design of aircraft engine combustion chambers.

[0003] like Figure 1 A schematic diagram of the existing combustion chamber head structure is shown. The combustion chamber 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 group and a main combustion stage channel. The swirler group is arranged in the main combustion stage channel. The swirler group includes a swirler 921 and a swirler 922. The nozzle 915, the swirler 921 and the second swirler 922 form premixed combustion in the main combustion stage channel; the pre-combustion stage includes a nozzle 914, a swirler group, a venturi 918 and a pre-combustion stage channel. The swirler group is arranged in the pre-combustion stage channel. The swirler group includes a swirler 916 and a swirler 917. The nozzle 914, the swirler 916 and the swirler 917 form diffusion combustion in the pre-combustion stage channel; the interstage 919 is surrounded by two flames, the premixed combustion formed by the main combustion stage and the diffusion combustion formed by the pre-combustion stage. The interstage 919 has problems such as high heat load and easy ablation, and its thermal protection design is relatively difficult.

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

[0005] The object of the present invention is to provide a combustion chamber interstage section which can avoid interstage section ablation.

[0006] To achieve the above-mentioned purpose, a combustion chamber interstage section comprises: an inner wall body and an outer disc body, wherein the inner wall body is arranged upstream of the outer disc body along the incoming flow direction, the inner wall body and the outer disc body are annular, and the inner edge of the inner wall body is connected to the inner edge of the outer disc body through a connecting ring portion;

[0007] The combustion chamber interstage section is provided with an outer ring cooling hole, an inner ring cooling hole and an intermediate cooling hole, the outer ring cooling hole is provided at the outer edge of the inner wall body along the circumferential direction 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 disk body, and the intermediate cooling hole is provided in the inner wall body between the outer ring cooling hole and the inner ring cooling hole, and is provided toward the outer disk body;

[0008] Wherein, the opening direction of the outer ring cooling holes forms an acute angle with the central axis of the combustion chamber interstage section.

[0009] In one or more embodiments, an annular groove in the combustion chamber interstage section is defined between the inner wall body, the outer disk body and the connecting ring portion, and the intermediate cooling hole is connected to the annular groove to allow airflow to be ejected in the annular groove toward the outer disk 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 holes include a plurality of circles, and the plurality of circles of intermediate cooling holes are opened between the outer ring cooling holes and the inner ring cooling holes at intervals along the radial direction of the inner wall body.

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

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

[0014] In one or more embodiments, along the incoming 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 to the outside along the incoming flow direction.

[0015] In one or more embodiments, along the incoming flow direction, the inner ring cooling hole has a section which is opened in an inwardly inclined manner 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 opened in an inwardly inclined manner toward the central axis of the combustion chamber interstage section, and the inner ring cooling holes have a section with a gradually inwardly contracting inner diameter.

[0017] On the other hand, according to some embodiments of the present application, there is also provided a combustion chamber, 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 swirler, and the upstream inner side of the interstage section corresponds to the pre-combustion stage swirler.

[0019] The beneficial effects of the present invention are:

[0020] The interstage section of the combustion chamber with this configuration adopts a thermal protection structure composed of outer ring cooling holes, inner ring cooling holes and intermediate cooling holes. The cooling air walls are formed near the outer ring and the inner ring of the interstage section respectively, and the thermal protection is realized together. On this basis, the purging and cooling of the outer disk are combined from the outside to the inside to realize a full range of thermal protection structure with good thermal protection effect, thereby reducing the thermal load of the interstage section and preventing the fuel from being sucked into the outer ring and the inner ring of the interstage section to cause ablation. At the same time, the impact cooling can reduce the wall temperature of the interstage section as a whole and increase the service life of the interstage section.

[0021] The above description is only an overview of the technical solution of the present application. In order to more clearly understand the technical means of the present application, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Moreover, the same reference numerals are used throughout the drawings to represent the same components. In the drawings:

[0023] Figure 1 A schematic diagram showing a conventional combustion chamber head structure is shown;

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

[0025] Figure 3 A front schematic diagram of a first embodiment of the interstage section of the combustion chamber is shown;

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

[0027] Figure 5 Shows Figure 4 A partial enlarged schematic diagram of part B;

[0028] Figure 6 A side schematic diagram of a first embodiment of the interstage section of the combustion chamber is shown;

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

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

[0031] Fig. 9 Shows Figure 8 A partial enlarged schematic diagram of part D of FIG. DETAILED DESCRIPTION

[0032] The following embodiments of the technical solution of the present application are described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present application, and are therefore only used as examples, and cannot be used to limit the scope of protection of the present application.

[0033] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0034] In order to avoid the problem of ablation of the intermediate stage of the combustion chamber, on the one hand, according to some embodiments of the present application, a combustion chamber is provided, such as Figure 2 A schematic diagram of a combustion chamber according to some embodiments of the present 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 can be understood that the incoming flow direction a refers to the flow direction of the airflow in the combustion chamber when the engine is in working condition. As shown in the figure, the outlet airflow 51 of the main combustion stage swirler 101 is premixed with the fuel injected from the nozzle to form an outer circle high temperature and low speed recirculation zone 52 downstream of the interstage section. The outlet airflow 61 of the pre-combustion stage swirler 102 is mixed with the fuel injected from the nozzle to form an inner circle high temperature and low speed recirculation zone 62 downstream of the interstage section. When the equivalence ratio of the main combustion stage swirler 101 and the pre-combustion stage swirler 102 is large, some fuel will not be completely burned locally. The existence of the outer circle high temperature and low speed recirculation zone 52 and the inner circle high temperature and low speed recirculation zone 51 will draw some unburned fuel into the low speed recirculation zone, aggravating the risk of ablation near the interstage section.

[0035] In order to solve the aforementioned problems, on the other hand, a combustion chamber interstage section is further provided according to some embodiments of the present application. Figure 3 FIG. 2 shows a front schematic diagram of a first embodiment of the interstage section of the combustion chamber, Figure 4 Shows Figure 3 The cross-sectional view obtained by cutting along the AA direction, Figure 5 Shows Figure 4 A partial enlarged schematic diagram of part B, Figure 6 FIG. 1 shows a side schematic diagram of a first embodiment of the interstage section of the combustion chamber, Figure 7 Shows Figure 6 Schematic cross-sectional view obtained by cutting along the CC direction.

[0036] Please refer to Figures 2 to 6 According to some embodiments of the combustor interstage, the combustor interstage 100 includes: an inner wall body 1 and an outer disk body 2, the inner wall body 1 is arranged upstream of the outer disk body 2 along the incoming flow direction a, the inner wall body 1 and the outer disk body 2 are both annular, the inner edge of the inner wall body 1 is connected to the inner edge of the outer disk body 2 through the connecting ring portion 3, it can be understood that the inner edge of the inner wall body 1 refers to the disk edge area of ​​the inner ring outer periphery of the inner wall body 1, and the outer edge of the inner wall body 1 refers to the disk edge area of ​​the outer periphery of the inner wall body 1. Similarly, the inner edge of the outer disk body 2 refers to the disk edge area of ​​the inner ring outer periphery of the outer disk body 2, and the outer edge of the outer disk body 2 refers to the disk edge area of ​​the outer periphery of the outer disk body 2.

[0037] The combustion chamber interstage section 100 is provided with outer ring cooling holes 11, inner ring cooling holes 12 and intermediate cooling holes 13. The outer ring cooling holes 11 are provided at the outer edge of the inner wall body 1 along the circumference of the inner wall body 1, and the inner ring cooling holes 12 are provided through the inner edge of the inner wall body 1, the connecting ring portion 3 and the inner edge of the outer disk body 2. The intermediate cooling holes 13 are provided in the inner wall body 1 between the outer ring cooling holes 11 and the inner ring cooling holes 12, and are provided toward the outer disk body 2, so that the gas blown out from the intermediate cooling holes 13 can impact the outer disk body 2.

[0038] Among them, 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 in the figure, when the airflow is blown out from the outer ring cooling hole 11 with an inclination angle, a cooling air film can be formed near the outer ring of the interstage section, blocking the high-temperature reflux gas of the main combustion stage and reducing the wall temperature of the outer ring of the interstage section. At the same time, the outer ring rotary cutting airflow 7 blown out from the outer ring cooling hole 11 can effectively blow away the unburned fuel near the outer ring of the interstage section, avoiding the fuel in the outer ring high-temperature and low-speed reflux zone 52 from being sucked into the outer ring of the interstage section for combustion and causing the outer ring of the interstage section to burn, thereby preventing the outer ring of the interstage section from burning.

[0040] When the airflow is blown out from the intermediate cooling holes 13 , the impinging airflow 8 can impinge and cool the outer disk 2 , thereby reducing the wall temperature of the outer disk 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 to block the high-temperature reflux combustion gas of the pre-combustion stage and reduce the inner ring wall temperature of the interstage section. The outlet high-speed airflow formed by the inner ring purge airflow 9 can prevent the fuel in the inner ring high-temperature and low-speed reflux zone 62 from being sucked into the inner ring of the interstage section, thereby preventing the inner ring of the interstage section from being burned.

[0042] The interstage section of the combustion chamber with the above-mentioned configuration adopts a thermal protection structure composed of outer ring cooling holes 11, inner ring cooling holes 12 and intermediate cooling holes 13, and thermal protection is achieved by forming cooling air walls near the outer ring and the inner ring of the interstage section. On this basis, combined with the purging and cooling of the outer disk 2, it is combined from the outside to the inside to achieve a full range of thermal protection structure with good thermal protection effect, thereby reducing the heat load of the interstage section and preventing the fuel from being sucked into the outer ring and the inner ring of the interstage section to cause ablation. At the same time, the impact cooling can reduce the wall temperature of the interstage section as a whole and increase the service life of the interstage section.

[0043] In the description of the embodiments of the present application, “plurality” means more than two, unless otherwise clearly and specifically defined.

[0044] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0045] In some embodiments of the combustor interstage section, Figure 5 As shown, the inner wall body 1, the outer disk body 2 and the connecting ring portion 3 define an annular groove 4 in the combustion chamber interstage section 100, and the intermediate cooling hole 13 is connected to the annular groove 4 to allow the airflow to be ejected toward the outer disk body in the annular groove 4.

[0046] In some embodiments of the interstage section of the combustion chamber, the size of the acute angle x allows the airflow ejected from the outer ring cooling hole 11 to cover the outer edge of the outer disk 2, thereby ensuring that a cooling air film can be formed on the outer ring of the interstage section, blocking the high-temperature reflux combustion gas of the main combustion stage, and reducing the wall temperature of the outer ring of the interstage section. At the same time, it can effectively prevent unburned fuel from being sucked into the outer ring of the interstage section for combustion, thereby preventing the outer ring of the interstage section from being burned.

[0047] In some embodiments of the combustor interstage section, Figure 7 As shown, the intermediate cooling holes 13 include multiple circles, and the multiple circles of intermediate cooling holes 13 are opened between the outer ring cooling holes 11 and the inner ring cooling holes 12 along the radial direction of the inner wall body at intervals, so that the impact cooling effect on the outer disk body 2 can be improved through the multiple circles of intermediate cooling holes 13.

[0048] In some embodiments of the combustor interstage section, Figure 7 As shown, two adjacent circles of intermediate cooling holes 13 are staggered along the circumferential direction of the inner wall body 1. Such arrangement enables the impingement cooling airflow blown out from the intermediate cooling holes 13 to spread over the entire outer disk body 2, thereby further improving the impingement cooling effect on the outer disk body 2.

[0049] In some embodiments of the combustor interstage section, Figure 5 As shown, along the incoming flow direction, the inner ring cooling hole 12 has a section with an inner diameter that gradually contracts inward, that is, the inner ring cooling hole 12 is in a closing shape, so as to increase the flow rate of the cooling air flow ejected from the inner ring cooling hole 12, thereby being able to more effectively and quickly form an inner ring cooling air wall to block the high-temperature reflux combustion gas of the pre-combustion stage. At the same time, a faster flow rate can more effectively prevent the fuel in the high-temperature and low-speed reflux zone 62 from being sucked into the inner ring of the interstage section, thereby improving the protection effect against ablation of the inner ring of the interstage section.

[0050] Furthermore, if 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, and 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 form a larger airflow velocity at the outlet of the inner ring cooling hole 12.

[0051] Figure 8 FIG. 2 shows a cross-sectional schematic diagram of a second embodiment of the combustion chamber interstage section. Fig. 9 Shows Figure 8 A partial enlarged schematic diagram of part D of FIG.

[0052] like Fig. 9 In the second embodiment shown, the configurations of the inner wall body 1', the outer disk body 2' and the connecting ring 3' are the same as those of the first embodiment. At the same time, the configurations of the outer ring cooling holes 11' and the intermediate cooling holes 13' are also the same as those of the first embodiment. The difference between the second embodiment and the first embodiment is that, along the incoming flow direction a, the inner ring cooling hole 12' has a section 121' that is opened inwardly and tilted toward the central axis of the interstage section of the combustion chamber. Through the section 121' that is opened inwardly and tilted, the airflow ejected from the inner ring cooling hole 12' can offset and isolate the inner ring high-temperature and low-speed recirculation zone 62, keeping it away from the wall surface of the outer disk body 2', and preventing the inner ring of the interstage section from being ablated.

[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 inclined inwardly toward the central axis of the interstage section of the combustion chamber. At the same time, the inner ring cooling hole has a section with a gradually narrowing inner diameter, thereby further enhancing the effect of preventing ablation of the inner ring of the interstage section.

[0054] In the description of the embodiments of the present application, technical terms such as "first" and "second" are only used to distinguish different objects and cannot be understood 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 the present application, unless otherwise clearly specified and limited, technical terms such as "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0056] It should be understood that "along" a certain direction mentioned in the text means that there is at least a component in the direction, preferably, the angle with the direction is within 10°, and 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 the present application, rather than to limit them; although the present application 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 replace some or all of the technical features therein by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application, and they should all be included in the scope of the claims and specification of the present application. In particular, as long as there is no structural conflict, the various technical features mentioned in the various embodiments can be combined in any way. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions that fall within the scope of the claims.

Claims

1. A combustion chamber interstage section, characterized in that: include: An inner wall body and an outer disc body, wherein the inner wall body is arranged upstream of the outer disc body along the incoming flow direction, the inner wall body and the outer disc body are annular, and the inner edge of the inner wall body is connected to the inner edge of the outer disc body through a connecting ring portion; The combustion chamber interstage section is provided with an outer ring cooling hole, an inner ring cooling hole and an intermediate cooling hole, the outer ring cooling hole is provided at the outer edge of the inner wall body along the circumferential direction 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 disk body, and the intermediate cooling hole is provided in the inner wall body between the outer ring cooling hole and the inner ring cooling hole, and is provided toward the outer disk body; Wherein, the opening direction of the outer ring cooling holes forms an acute angle with the central axis of the combustion chamber interstage section.

2. The combustor interstage section according to claim 1, characterized in that: An annular groove in the combustion chamber interstage section is defined between the inner wall body, the outer disk body and the connecting ring portion, and the intermediate cooling hole is connected to the annular groove to allow airflow to be ejected toward the outer disk body in the annular groove.

3. The combustor interstage section according to claim 1, characterized in that: The acute angle allows the airflow ejected from the outer ring cooling holes to cover the outer edge of the outer disk.

4. The combustor interstage section according to claim 1, characterized in that: The intermediate cooling holes include a plurality of circles, and the plurality of circles of intermediate cooling holes are arranged between the outer ring cooling holes and the inner ring cooling holes at intervals along the radial direction of the inner wall body.

5. The combustor interstage section according to claim 1, characterized in that: Two adjacent circles of the intermediate cooling holes are staggeredly arranged along the circumferential direction of the inner wall body.

6. The combustor interstage section according to claim 1, characterized in that: Along the incoming flow direction, the inner ring cooling hole has a section with an inner diameter gradually contracting inwards.

7. The combustor interstage section according to claim 1, characterized in that: Along the incoming 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 to the outside along the incoming flow direction.

8. The combustor interstage section according to claim 1, characterized in that: Along the incoming flow direction, the inner ring cooling hole has a section which is opened in an inwardly inclined manner toward the central axis of the combustion chamber interstage section.

9. The combustor interstage section according to claim 1, characterized in that: Along the incoming flow direction, the inner ring cooling hole is opened in an inwardly inclined manner toward the central axis of the combustion chamber interstage section, and the inner ring cooling hole has a section with a gradually inwardly contracted inner diameter.

10. A combustion chamber, characterized in that: It comprises a main combustion stage swirler, a pre-combustion stage swirler and an interstage section as claimed in any one of claims 1 to 9; Along the incoming flow direction, the upstream outer side of the interstage section corresponds to the main combustion stage swirler, and the upstream inner side of the interstage section corresponds to the pre-combustion stage swirler.

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