Inlet duct inner skin radiator

Abstract

The present application provides an air inlet inner skin radiator, the radiator comprising: an outer skin; an inner barrel wall, a gap between the inner barrel wall and the outer skin; a heat and mass channel, the heat and mass channel is fixed on the inner barrel wall, and the heat and mass channel extends in a spiral shape along the axis of the inner barrel wall, one side of the heat and mass channel is connected to the heat and mass channel inlet, and the other side is connected to the heat and mass channel outlet, so that the hot side working medium in the heat and mass channel flows forward in a spiral in the heat and mass channel; fins, the fins are fixedly connected to the heat and mass channel and the outer skin, and are used to provide support force to the outer skin so that the outer skin has the ability to maintain the shape and can exchange heat with the heat and mass channel. The air inlet inner skin heat exchanger provided by the present application can not only maintain the air inlet shape, but also use the cold air in the air inlet to perform two heat exchanges to provide heat exchange efficiency.

Description

Technical Field

[0001] The present application relates to the technical field of radiators, and in particular to an air inlet inner skin radiator. Background Art

[0002] With the continuous advancement of aircraft, the demand for heat exchange in aircraft systems is also increasing. Therefore, a large number of heat exchangers are needed in the aircraft to exchange heat for the heat medium in the aircraft system (such as the lubricating oil system) to ensure the normal operation of the aircraft system.

[0003] At the same time, due to the aircraft's requirements on flight speed and fuel economy, the aircraft surface needs to be relatively smooth to reduce the aircraft's resistance. Therefore, ram air inlets are almost no longer set on the fuselage surface, which makes it difficult to dissipate the cooling air source in the engine compartment and the heat of various systems.

[0004] Therefore, a heat exchanger is needed which can be arranged in the engine compartment and can dissipate heat. Summary of the invention

[0005] The purpose of the present application is to provide an air inlet inner skin radiator to solve or alleviate at least one problem in the background technology.

[0006] The technical solution of the present application is: an air inlet inner skin radiator, the radiator comprising:

[0007] Outer skin;

[0008] An inner cylinder wall, wherein a gap is formed between the inner cylinder wall and the outer skin;

[0009] A heat and mass channel, wherein the heat and mass channel is fixed on the inner barrel wall and extends in a spiral shape along the axis of the inner barrel wall, one side of the heat and mass channel is connected to the heat and mass channel inlet and the other side is connected to the heat and mass channel outlet, so that the hot side working medium in the heat and mass channel flows forward in a spiral shape in the heat and mass channel;

[0010] The fins are fixedly connected to the heat and mass channel and the outer skin, and are used to provide a supporting force to the outer skin so that the outer skin has the ability to maintain a profile and can exchange heat with the heat and mass channel.

[0011] Furthermore, the profile of the outer skin is consistent with the profile of the original aircraft air inlet.

[0012] Furthermore, the inner diameter of the inner tube wall is determined according to the requirements of the aircraft air inlet surface.

[0013] Furthermore, the cross-section of the heat and mass channel is rectangular or square.

[0014] Furthermore, the inlet of the heat and mass channel is located on a side close to the rear air inlet, and the outlet of the heat and mass channel is located on a side close to the front air inlet.

[0015] Furthermore, the fins are also arranged in a spiral between the inner tube wall and the outer skin, and the spiral direction is consistent with the heat and mass channel.

[0016] Furthermore, the width of the fin is greater than the cross-sectional width of the heat and mass channel.

[0017] Furthermore, the width of the fin is 5 to 6 times the cross-sectional width of the heat and mass channel.

[0018] The inlet inner skin heat exchanger provided in the present application can not only maintain the inlet surface, but also utilize the cold air in the inlet for heat exchange, thereby providing an additional heat exchange channel for the heat source or heat components in the aircraft, realizing a fusion design of maintaining the aircraft inlet surface and heat dissipation. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0020] Figure 1 This is a schematic diagram of the appearance of the air intake inner skin radiator of this application.

[0021] Figure 2 This is a cross-sectional view of the air inlet inner skin radiator of the present application.

[0022] Figure 3 This is a partial enlarged view of the inner skin radiator of the air inlet duct of this application.

[0023] Reference numerals

[0024] 11-Front air intake

[0025] 12-Rear air intake

[0026] 20-Radiator

[0027] 21-Heat and mass channel entrance

[0028] 22-Heat and mass channel outlet

[0029] 23-Heat and Mass Channel

[0030] 24-Fin

[0031] 25-Outer skin

[0032] 26-Inner cylinder wall

[0033] 27-Ring-shaped ram air inlet

[0034] 28-Annular stamping outlet DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0036] like Figures 1 to 3 As shown, the present application provides an air inlet inner skin heat exchanger, and the air inlet inner skin radiator (hereinafter referred to as radiator) includes: an inner cylinder wall 26, an outer skin 25, a heat and mass channel 23 and fins 24.

[0037] The outer skin 25 is used to form the outer profile of the radiator 20, which is basically consistent with the outer profile of the original air inlet. The front and rear sides of the outer skin 25 are respectively connected to the front air inlet 11 and the rear air inlet 12. The connection between the outer skin 25 and the front air inlet 11 and the rear air inlet 12 is smooth and does not form a boss or step.

[0038] The inner barrel wall 26 is arranged on the inner side of the outer skin 25, and there is a gap or cavity between the inner barrel wall 26 and the outer skin 25, and the gap or cavity can be used to install the heat and mass channel 23 and the fin 24. The diameter of the inner barrel wall 26 is determined according to the requirements of the aircraft air inlet surface, and the inner barrel wall 26 is a cylindrical surface structure.

[0039] The heat and mass channel 23 is fixed on the inner barrel wall 26 and is located between the inner barrel wall 26 and the outer skin 25. The heat and mass channel 23 forms a spiral hot side channel along the inner barrel wall 26, in which the hot side working medium (such as aircraft lubricating oil or other hot side medium of the aircraft) flows in a spiral manner, and one side of the heat and mass channel 23 is connected to the heat and mass channel inlet 21, and the other side is connected to the heat and mass channel outlet 22. In some embodiments of the present application, the cross-section of the heat and mass channel 23 is rectangular or square, which is convenient for arrangement. Furthermore, the inlet of the heat and mass channel 23 is located on one side of the rear air inlet 12, and the outlet of the heat and mass channel 23 is located on one side of the front air inlet 11, thereby forming a flow mode of rear-side entry and front-side exit to improve the heat exchange efficiency.

[0040] The fins 24 are fixedly connected to the heat and mass channel 23 and the outer skin 25. On the one hand, the fins 24 can provide support to the outer skin 25 so that the outer skin 25 has the ability to maintain the profile. On the other hand, the fins 24 can exchange heat with the heat and mass channel 23. Furthermore, the fins 24 are also arranged in a spiral between the inner cylinder wall 26 and the outer skin 25, and the spiral direction is consistent with the direction of the heat and mass channel 23. Among them, the width of the fins 24 is greater than the cross-sectional width of the heat and mass channel 23. For example, in the present application, Figure 3 In the illustrated embodiment, the width of the fin 24 is approximately equal to 5 to 6 times the cross-sectional width of the heat and mass channel 23 .

[0041] The front end between the inner cylinder wall 26 and the outer skin 25 forms an annular ramming air inlet 27, and the rear end between the inner cylinder wall 26 and the outer skin 25 forms an annular ramming air outlet 28. Most of the cold gas flowing in from the front air inlet 11 flows through the inner cylinder wall 26, and this part of the cold gas exchanges heat with the hot mass fluid in the hot mass channel 23 through the inner cylinder wall 26. Another part of the cold gas flows in from the annular ramming air inlet, flows through the fins 24, takes away the heat in the hot mass channel 23, and then flows out from the annular ramming air outlet and returns to the air inlet, thereby exchanging heat twice.

[0042] The inlet inner skin heat exchanger provided in the present application can not only maintain the inlet surface, but also utilize the cold air in the inlet for heat exchange, thereby providing an additional heat exchange channel for the heat source or heat components in the aircraft, realizing a fusion design of maintaining the aircraft inlet surface and heat dissipation.

[0043] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An air inlet inner skin radiator, characterized in that: The radiator comprises: Outer skin (25); an inner cylinder wall (26), wherein a gap is provided between the inner cylinder wall (26) and the outer skin (25), a front end between the inner cylinder wall (26) and the outer skin (25) forms an annular ram air inlet (27), and a rear end between the inner cylinder wall (26) and the outer skin (25) forms an annular ram air outlet (28); and A heat and mass channel (23), wherein the heat and mass channel (23) is fixed on the inner barrel wall (26), and the heat and mass channel (23) extends in a spiral shape along the axis of the inner barrel wall, and one side of the heat and mass channel (23) is connected to a heat and mass channel inlet (21), and the other side is connected to a heat and mass channel outlet (22), so that the hot side working medium in the heat and mass channel (23) flows forward in a spiral shape in the heat and mass channel; The fins (24) are fixedly connected to the heat and mass channel (23) and the outer skin (25) and are used to provide a supporting force to the outer skin (25) so that the outer skin (25) has the ability to maintain a profile and can exchange heat with the heat and mass channel (23).

2. The air inlet inner skin radiator according to claim 1, characterized in that: The profile of the outer skin (25) is consistent with the profile of the original aircraft air inlet.

3. The air inlet inner skin radiator according to claim 1, characterized in that: The inner diameter of the inner cylinder wall (26) is determined according to the requirements of the aircraft air inlet surface.

4. The air inlet inner skin radiator according to claim 1, characterized in that: The cross section of the heat and mass channel (23) is rectangular or square.

5. The air inlet inner skin radiator according to claim 4, characterized in that: The inlet of the heat and mass channel (23) is located on a side close to the rear air inlet (12), and the outlet of the heat and mass channel (23) is located on a side close to the front air inlet (11).

6. The air inlet inner skin radiator according to claim 4, characterized in that: The fins (24) are also arranged in a spiral shape between the inner tube wall (26) and the outer skin (25), and the spiral direction is consistent with the heat and mass channel (23).

7. The air inlet inner skin radiator according to claim 6, characterized in that: The width of the fin (24) is greater than the cross-sectional width of the heat and mass channel (23).

8. The air inlet inner skin radiator according to claim 7, characterized in that: The width of the fin (24) is 5 to 6 times the cross-sectional width of the heat and mass channel (23).

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