Aero-engine force-bearing casing temperature control structure

Abstract

The application provides an aero-engine load-bearing casing temperature control structure, comprising: a load-bearing casing mainly composed of an outer ring, an inner ring and load-bearing plates; a flow channel piece mainly composed of an outer flow channel, an inner flow channel and a fairing, the flow channel piece isolates the load-bearing casing from the main flow high-temperature gas; and a flow guide structure arranged in each load-bearing plate and having the same cross-sectional shape and size, wherein for the load-bearing plate with functional pipelines passing through the inside, the flow guide structure is arranged between the load-bearing plate and the functional pipelines; and for the load-bearing plate without functional pipelines passing through the inside, the flow guide structure is arranged in the load-bearing plate; by arranging the flow guide structure in each load-bearing plate, the cold gas passage with the same flow passage cross section is formed between each load-bearing plate and the flow guide structure, the cooling gas flows through the cooling passage to realize the cooling of the load-bearing casing wall surface, so that the temperature levels of the load-bearing plates are consistent, and finally the problem of circumferential deformation of the load-bearing casing is overcome.

Description

Technical Field

[0001] This application belongs to the field of aero-engine thermal protection technology, and specifically relates to a temperature control structure for aero-engine load-bearing casing. Background Technology

[0002] The load-bearing casing is a crucial load-bearing component of an aero-engine, playing a vital role in the engine's operational safety. For example... Figure 1 and Figure 2 The diagram shows a typical cooling structure 10 for an engine load-bearing casing. The load-bearing casing 11 is mainly composed of an outer ring 12, an inner ring 14, and load-bearing support plates 13. To ensure that the load-bearing casing 11 can meet the long-term allowable temperature requirements of the materials and the requirements of structural strength in a high-temperature working environment, a flow channel component 15, mainly composed of an outer flow channel 16, an inner flow channel 18, and a fairing 17, is used to isolate the load-bearing casing 11 from the mainstream high-temperature combustion gas. At the same time, cooling gas is introduced into the load-bearing casing 11 for cooling. After cooling the outer ring 12, the cooling gas flows into the interior of each load-bearing support plate 13, and further flows into the inner ring cavity to cool the inner ring 14, thereby achieving cooling of the wall surface of the load-bearing casing 11 and ensuring that the load-bearing casing 11 operates at a lower temperature level.

[0003] Existing technical solutions can reduce the temperature of the load-bearing casing 11 through cooling gas, but cannot guarantee that all load-bearing support plates 13 of the load-bearing casing 1 maintain the same temperature level. This is because, for the actual engine structure, the structural forms of all load-bearing support plates 13 are the same. However, for the overall engine layout, some load-bearing support plates 13 have functional pipes 19 passing through them, such as oil pipes and air pipes. This results in inconsistent cooling gas flow areas inside the load-bearing support plates 13. Specifically, for load-bearing support plates 13 without functional pipes 19 passing through them, their internal flow area is equal to the cross-sectional area of ​​the load-bearing support plate 13 itself. Figure 3 As shown in the shaded area; for the load-bearing support plate 13 through which the functional pipe 19 passes, its internal flow area is the difference between the cross-sectional area of ​​the load-bearing support plate 13 and the cross-sectional area of ​​the functional pipe 19, such as Figure 4 As shown in the shaded area. Therefore, for the existing load-bearing casing cooling scheme, the cooling air flow area in each load-bearing support plate 13 is different, which affects the distribution of cooling air flow in each support plate. This results in different cooling effects of the cooling air in each load-bearing support plate, and thus the temperature levels of each load-bearing support plate will vary. Temperature differences are an adverse factor affecting the strength of the load-bearing casing, and can lead to uneven stress and damage. Summary of the Invention

[0004] The purpose of this application is to provide a temperature control structure for the load-bearing casing of an aero-engine to solve or mitigate at least one of the problems in the prior art.

[0005] The technical solution of this application is: a temperature control structure for a load-bearing casing of an aero-engine, comprising:

[0006] The load-bearing casing is mainly composed of an outer ring, an inner ring, and load-bearing support plates;

[0007] The flow channel component mainly consists of an outer flow channel, an inner flow channel, and a rectifier cover, which isolates the load-bearing casing from the mainstream high-temperature combustion gas.

[0008] A flow guiding structure with identical cross-sectional shape and dimensions, installed within each load-bearing support plate, wherein:

[0009] For load-bearing plates with internal functional pipelines, the flow guiding structure is arranged between the load-bearing plate and the functional pipelines;

[0010] For load-bearing plates with no internal functional pipelines, the flow guiding structure is arranged inside the load-bearing plate;

[0011] By setting a flow guide structure in each load-bearing support plate, a cold air channel with the same flow cross section is formed between each load-bearing support plate and the flow guide structure. The cooling gas flows through the cooling channel to cool the wall of the load-bearing casing.

[0012] In a preferred embodiment of this application, the cooling gas flow rate entering each of the cooling gas channels is the same.

[0013] In a preferred embodiment of this application, there is a gap between the flow guiding structure and the functional pipeline.

[0014] In a preferred embodiment of this application, the flow guiding structure is longer than the length of the load-bearing support plate in the length direction.

[0015] In a preferred embodiment of this application, the flow guiding structure is a pipeline structure.

[0016] In a preferred embodiment of this application, the cross-sectional shape of the flow guiding structure includes a runway circle and an ellipse.

[0017] The temperature control structure for the aero-engine load-bearing casing provided in this application ensures a consistent cooling airflow area within each load-bearing support plate. This results in uniform cooling airflow distribution and cooling effect across all support plates, ultimately leading to a consistent temperature level and mitigating the problem of inconsistent circumferential deformation of the load-bearing casing caused by uneven temperatures. Furthermore, the flow-guiding structure isolates the functional piping from the cooling air within the load-bearing support plates, reducing the impact of the functional piping's heat dissipation on the cooling effect within the load-bearing support plates. Attached Figure Description

[0018] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0019] Figure 1 This is a cross-sectional view of a typical engine load-bearing casing cooling structure.

[0020] Figure 2 This is a side view of a typical engine load-bearing casing cooling structure.

[0021] Figure 3 This is a schematic diagram of the ventilation cross-section when a non-functional pipe passes through a typical engine load-bearing casing cooling structure.

[0022] Figure 4 This is a schematic diagram of the ventilation cross-section when a functional pipeline passes through a typical engine load-bearing casing cooling structure.

[0023] Figure 5 This is a cross-sectional view of the temperature control structure of the load-bearing casing of the aero-engine in this application.

[0024] Figure 6 This is a side view of the temperature control structure of the load-bearing casing of the aero-engine in this application.

[0025] Figure 7 This is a schematic diagram of the ventilation section when a functional pipeline passes through the temperature control structure of the load-bearing casing of the aero-engine in this application.

[0026] Figure 8 This is a schematic diagram of the ventilation section when no functional pipeline passes through the temperature control structure of the load-bearing casing of the aero-engine in this application. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0028] like Figure 5 and Figure 6As shown, in order to achieve uniform cooling of each load-bearing support plate 13 of the load-bearing casing, this application provides a temperature control structure for the load-bearing casing of an aero-engine. This temperature control structure 20 includes a typical load-bearing casing cooling structure 10 and a flow-guiding structure 21 with identical cross-sectional shape and dimensions disposed within each load-bearing support plate 13. For load-bearing support plates 13 through which functional pipes 19 pass, the flow-guiding structure 21 is arranged between the load-bearing support plate 13 and the functional pipes 19. For load-bearing support plates 13 without internal functional pipes 19, the flow-guiding structure 21 is simply arranged within the load-bearing support plate 13. By providing the flow-guiding structure 21 within each load-bearing support plate 13, a cold air channel with the same flow cross-section is formed between each load-bearing support plate 13 and the flow-guiding structure 21. Cooling gas flows through this cooling channel to cool the walls of the load-bearing casing.

[0029] In a preferred embodiment of this application, the cooling gas flow rate in the cooling gas passage between the load-bearing support plate 13 and the guide structure 21 remains unchanged, thereby reducing the cooling gas flow area within the load-bearing support plate 13. However, with the total cooling gas flow rate remaining unchanged, the cooling gas flow velocity within the load-bearing support plate 13 can be increased, the cooling gas heat exchange capacity can be enhanced, and the cooling effect of the load-bearing support plate 13 can be improved.

[0030] In this application, the flow guiding structure 21 is a pipe structure passing through the load-bearing support plate 13. It does not contact the load-bearing support plate or the functional pipes, and there is a certain gap between the flow guiding structure 21 and the functional pipes 19. In a preferred embodiment of this application, the flow guiding structure 21 is longer than the load-bearing support plate 13 in the length direction, so that the entire height of the load-bearing support plate 13 can be cooled during the airflow process.

[0031] In some embodiments of this application, the cross-section of the flow guiding structure 21 can be a runway circle, an ellipse, or other shapes. For example, in the illustrated embodiment of this application, the cross-section of the flow guiding structure 21 is a runway circle (semicircles at both ends and a rectangle in the middle).

[0032] like Figure 7 and Figure 8 The diagram shows the internal cooling airflow area of ​​the load-bearing support plate with and without the flow guide structure 21. The cooling airflow area in both types of load-bearing support plates is the space between the load-bearing support plate 13 and the flow guide structure 21 (i.e., the shaded area), and the flow area is the difference between the cross-sectional area of ​​the load-bearing support plate 13 and the cross-sectional area of ​​the flow guide structure 21. Because of the flow guide structure 21, the cooling airflow area is the same in each load-bearing support plate 13 through which the functional pipe 19 passes, resulting in the same amount of cooling air flowing in each support plate and ultimately maintaining a consistent temperature level across all support plates.

[0033] The load-bearing casing temperature control structure provided in this application can achieve uniform cooling of each load-bearing support plate of the load-bearing casing without changing the original load-bearing casing frame structure and cooling airflow path layout, so that the temperature level of each load-bearing support plate remains consistent, thus saving modification costs.

[0034] The aircraft engine load-bearing casing temperature control structure 20 provided in this application can ensure that the cooling air flow area in each load-bearing support plate 13 is consistent, thereby ensuring that the cooling air flow distribution in each load-bearing support plate 13 is the same, the cooling effect in each load-bearing support plate 13 is the same, and ultimately the temperature level of each load-bearing support plate 13 is consistent, thus avoiding the problem of inconsistent circumferential deformation of the load-bearing casing caused by uneven temperature in each load-bearing support plate 13. In addition, the flow guiding structure 21 isolates the functional pipe 19 from the cooling air in the load-bearing support plate 13, reducing the impact of the heat dissipation of the functional pipe 19 on the cooling effect in the load-bearing support plate 13.

[0035] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A temperature control structure for a load-bearing casing of an aero-engine, characterized in that, include: The load-bearing casing (11) is mainly composed of an outer ring (12), an inner ring (14) and a load-bearing support plate (13). The load-bearing support plate (13) includes a load-bearing support plate through which functional pipelines (19) pass and a load-bearing support plate through which no functional pipelines (19) pass. The flow channel component (15) is mainly composed of an outer flow channel (16), an inner flow channel (18) and a fairing (17), which isolates the load-bearing casing (11) from the mainstream high-temperature gas. A flow guiding structure (21) with identical cross-sectional shape and size is installed within each load-bearing support plate (13), wherein: For a load-bearing support plate (13) through which a functional pipeline (19) passes, the flow guiding structure (21) is arranged between the load-bearing support plate (13) and the functional pipeline (19); For load-bearing support plates (13) through which no internal functional pipelines (19) pass, the flow guiding structure (21) is arranged inside the load-bearing support plate (13); By setting a flow guide structure (21) in each load-bearing support plate (13), a cooling channel with the same flow cross section is formed between each load-bearing support plate (13) and the flow guide structure (21). Cooling gas flows through the cooling channel to cool the load-bearing casing wall.

2. The temperature control structure for the load-bearing casing of an aero-engine as described in claim 1, characterized in that, The cooling gas flow rate is the same for each of the aforementioned cooling channels.

3. The temperature control structure for the load-bearing casing of an aero-engine as described in claim 1, characterized in that, There is a gap between the flow guiding structure (21) and the functional pipeline (19).

4. The temperature control structure for the load-bearing casing of an aero-engine as described in claim 3, characterized in that, The flow guiding structure (21) is longer than the load-bearing support plate (13) in the length direction.

5. The temperature control structure for the load-bearing casing of an aero-engine as described in any one of claims 1 to 4, characterized in that, The flow guiding structure (21) is a pipeline structure.

6. The temperature control structure for the load-bearing casing of an aero-engine as described in claim 5, characterized in that, The cross-sectional shape of the flow guiding structure (21) includes a runway circle and an ellipse.

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