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 a load-bearing plate; a flow channel piece mainly composed of an outer flow channel, an inner flow channel and a fairing; and a heat insulation plate arranged between the flow channel piece and the load-bearing casing, wherein the heat insulation plate comprises an outer ring heat insulation plate, a plate heat insulation plate and an inner ring heat insulation plate, the outer ring heat insulation plate is arranged between the outer flow channel and the outer ring, the plate heat insulation plate is arranged between the fairing and the load-bearing plate, and the inner ring heat insulation plate is arranged between the inner flow channel and the inner ring. The application can control the temperature level of the outer ring, the inner ring and the load-bearing plate of the load-bearing casing, reduce the radial temperature gradient of the load-bearing casing and reduce the adverse effect of the load-bearing casing on the strength.

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 of an aero-engine is a crucial load-bearing component, playing a vital role in the engine's operational safety. For example... Figure 1 The diagram shows a typical engine load-bearing casing structure 10. To ensure that the load-bearing casing 11, which is mainly composed of an outer ring 12, an inner ring 14, and load-bearing support plates 13, can meet the long-term allowable temperature requirements of 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 used to cool the load-bearing casing 11. 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 load-bearing casing wall and ensuring that the load-bearing casing 11 operates at a reasonable temperature level.

[0003] However, for this cooling scheme, the temperature of the load-bearing casing 11 is mainly affected by two factors: firstly, the heat radiation from the flow channel component 15 to the load-bearing casing 11; and secondly, the convective heat transfer between the cooling air and the load-bearing casing 11. The disadvantages of this technical solution are as follows:

[0004] a) The load-bearing casing has a high temperature level under high conditions.

[0005] For the existing cooling scheme, since the flow channel component 15 is exposed to the mainstream high-temperature combustion environment, its temperature level is relatively high, and its radiation capacity to the load-bearing casing 11 is relatively strong. Although the load-bearing casing 11 is cooled by cooling air, in order to ensure the overall performance of the engine, there is usually an upper limit requirement for the cooling air flow rate. Therefore, the load-bearing casing 11 cannot ensure that it operates at a low temperature level by drawing in a large amount of cooling air. In other words, the load-bearing casing 11 is in a thermal environment with strong external radiation and limited internal cooling. This performance is particularly obvious at high altitudes (thin air, small cooling air flow rate) and high heat loads (high mainstream temperature, strong radiation force of flow channel component), thus causing the load-bearing casing 11 to be at a high temperature level as a whole.

[0006] b) Large radial temperature gradient in the load-bearing casing

[0007] For existing cooling solutions, when the cooling gas temperature is low (such as using the engine bypass gas for cooling), combined with the radial temperature distribution of the main flow channel, the radial temperature distribution of the load-bearing casing 11 usually shows a distribution pattern of higher temperature in the load-bearing support plate 13 and inner ring 4, and lower temperature in the outer ring 12. The overall radial temperature distribution gradient of the load-bearing casing 11 is large, which has an adverse effect on the strength of the load-bearing casing 11. Summary of the Invention

[0008] 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.

[0009] The technical solution of this application is: a temperature control structure for a load-bearing casing of an aero-engine, comprising:

[0010] The load-bearing casing is mainly composed of an outer ring, an inner ring, and load-bearing support plates;

[0011] The flow channel component mainly consists of an outer flow channel, an inner flow channel, and a fairing; and

[0012] A heat insulation plate is disposed between the flow channel component and the load-bearing casing, wherein the heat insulation plate includes an outer ring heat insulation plate, a support plate heat insulation plate and an inner ring heat insulation plate. The outer ring heat insulation plate is disposed between the outer flow channel and the outer ring, the support plate heat insulation plate is disposed between the fairing and the load-bearing support plate, and the inner ring heat insulation plate is disposed between the inner flow channel and the inner ring.

[0013] In a preferred embodiment of this application, the wall surface of the heat insulation plate does not contact the wall surfaces of the load-bearing casing and the flow channel components.

[0014] In a preferred embodiment of this application, a low-emissivity coating is provided on the outer surface of the outer flow channel, the inner surface of the fairing, the inner surface of the inner flow channel component, the inner surface of the outer ring, the outer surface of the load-bearing support plate, the outer surface of the inner ring, and the inner and outer surfaces of the outer ring heat insulation plate, the inner and outer surfaces of the support plate heat insulation plate, and the inner and outer surfaces of the inner ring heat insulation plate.

[0015] The temperature control structure for the aero-engine load-bearing casing provided in this application can control the temperature levels of the outer ring, inner ring, and load-bearing support plate of the load-bearing casing by setting heat insulation plates, thereby reducing the radial temperature gradient of the load-bearing casing and minimizing its adverse effects on the strength of the load-bearing casing. Furthermore, by setting a low-emissivity coating at a designated location, the temperature level of the load-bearing casing can be effectively reduced, with particularly significant effects on operating conditions where the mainstream temperature is high and the cooling gas conditions are poor. Attached Figure Description

[0016] 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.

[0017] Figure 1 This is a schematic diagram of a typical aircraft engine load-bearing casing cooling structure.

[0018] Figure 2 This is a schematic diagram of the temperature control structure of the load-bearing casing of the aero-engine in this application.

[0019] 10 - Typical cooling structure of aero-engine load-bearing casing

[0020] 11-Load-bearing casing

[0021] 12-Outer Ring

[0022] 13-Bearing support plate

[0023] 14-Inner Ring

[0024] 15-Flow channel components

[0025] 16-Outer Flow Channel

[0026] 17-Fairing

[0027] 18-Inner flow channel

[0028] 20-Aircraft engine load-bearing casing temperature control structure

[0029] 21-Load-bearing casing

[0030] 211-Outer Ring

[0031] 212-Bearing Support Plate

[0032] 213-Inner Ring

[0033] 22-Flow channel component

[0034] 221-Outer Flow Channel

[0035] 222-Fairing

[0036] 223-Inner flow channel

[0037] 23-Insulation Board

[0038] 231-Outer Ring Insulation Board

[0039] 232-Supported Insulation Board

[0040] 233-Inner Ring Insulation Board Detailed Implementation

[0041] 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.

[0042] In order to reduce the temperature level and radial temperature gradient of the load-bearing casing without changing the frame structure and cooling airflow path layout, this application provides a temperature control structure for an aero-engine.

[0043] like Figure 2 As shown, the aircraft engine temperature control structure 20 provided in this application includes: a load-bearing casing 21 mainly composed of an outer ring 211, an inner ring 213 and a load-bearing support plate 212; a flow channel component 22 mainly composed of an outer flow channel 221, an inner flow channel 223 and a fairing 222; and a heat insulation plate 23 disposed between the flow channel component 22 and the load-bearing casing 21. The heat insulation plate 23 includes an outer ring heat insulation plate 231, a support plate heat insulation plate 232 and an inner ring heat insulation plate 233. The outer ring heat insulation plate 231 is disposed between the outer flow channel 221 and the outer ring 211, the support plate heat insulation plate 232 is disposed between the fairing 222 and the load-bearing support plate 212, and the inner ring heat insulation plate 233 is disposed between the inner flow channel 223 and the inner ring 213.

[0044] In this application, the wall surface of the heat insulation plate 23 does not contact the wall surface of the load-bearing casing 21 or the wall surface of the flow channel component 22. That is, the outer ring heat insulation plate 231 does not contact the outer flow channel 221 and the outer ring 211, the support plate heat insulation plate 232 does not contact the fairing 222 and the load-bearing support plate 212, and the inner ring heat insulation plate 233 does not contact the inner flow channel 223 and the inner ring 213. Thus, the heat insulation plate 23 blocks the direct radiation of the flow channel component 22 to the load-bearing casing 21.

[0045] The temperature control structure for the load-bearing casing of the aero-engine provided in this application converts the direct radiation from the flow channel component 15 to the load-bearing casing 11 in the original scheme into radiation from the flow channel component 22 to the heat insulation plate 23 in this application scheme—heat conduction of the heat insulation plate 23 itself—radiation from the heat insulation plate 23 to the load-bearing casing 21, thereby significantly reducing the radiant heat flow received by the load-bearing casing 21, thus keeping the load-bearing casing 21 at a lower temperature level.

[0046] Based on this, the temperature control structure 20 of the aero-engine load-bearing casing of this application can be coated with a low-emissivity coating at designated locations to further reduce radiative heat flow and lower the temperature of the load-bearing casing. These designated locations include: the outer surface of the outer flow channel 221, the inner surface of the inner flow channel component 223, the inner surface of the fairing 222, the inner surface of the outer ring 211, the outer surface of the inner ring 213, the outer surface of the load-bearing support plate 212, the inner and outer surfaces of the outer ring heat insulation plate 231, the inner and outer surfaces of the inner ring heat insulation plate 233, and the inner and outer surfaces of the support plate heat insulation plate 232. Through the proper matching of the heat insulation plate 23 and the low-emissivity coating, the temperature levels of various parts of the load-bearing casing 21 can be further controlled.

[0047] The temperature control structure for the aero-engine load-bearing casing provided in this application can control the temperature levels of the outer ring, inner ring, and load-bearing support plate of the load-bearing casing by setting heat insulation plates, thereby reducing the radial temperature gradient of the load-bearing casing and minimizing its adverse effects on the strength of the load-bearing casing. Furthermore, by setting a low-emissivity coating at a designated location, the temperature level of the load-bearing casing can be effectively reduced, with particularly significant effects on operating conditions where the mainstream temperature is high and the cooling gas conditions are poor.

[0048] 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 (21) is mainly composed of an outer ring (211), an inner ring (213) and a load-bearing support plate (212). The flow channel component (22) mainly consists of an outer flow channel (221), an inner flow channel (223), and a fairing (222); and A heat insulation plate (23) is disposed between the flow channel component (22) and the load-bearing casing (21). The wall surface of the heat insulation plate (23) does not contact the wall surface of the load-bearing casing (21) and the flow channel component (22). The heat insulation plate (23) includes an outer ring heat insulation plate (231), a support plate heat insulation plate (232), and an inner ring heat insulation plate (233). The outer ring heat insulation plate (231) is disposed between the outer flow channel (221) and the outer ring (211). The support plate heat insulation plate (232) is disposed between the fairing (222) and the load-bearing support plate (212). The inner ring heat insulation plate (233) is disposed between the inner flow channel (223) and the inner ring (213).

2. The temperature control structure for the load-bearing casing of an aero-engine as described in claim 1, characterized in that, Low-emissivity coatings are provided on the outer surface of the outer flow channel (221), the inner surface of the fairing (222), the inner surface of the inner flow channel component (223), the inner surface of the outer ring (211), the outer surface of the load-bearing support plate (212), the outer surface of the inner ring (213), the inner and outer surfaces of the outer ring heat insulation plate (231), the inner and outer surfaces of the support plate heat insulation plate (232), and the inner and outer surfaces of the inner ring heat insulation plate (233).

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