Heat insulation structure of high-temperature air entraining pipe of airplane

Abstract

The utility model relates to the technical field of heat insulation of air entraining pipes, and discloses a heat insulation structure of an airplane high-temperature air entraining pipe, which comprises a pipeline main body, a plurality of groups of positioning rings are arranged on the outer side of the pipeline main body, each group comprises two positioning rings, a support ring is arranged between the two positioning rings, and the support ring is sleeved on the outer side of the pipeline main body. A plurality of open holes are formed in one side of the supporting ring. Welding and conventional mechanical connection are adopted as a whole, an adhesive connection mode is not adopted, connection is more reliable, the problem that adhesive is prone to aging is solved, meanwhile, the positioning ring is adopted for fixing the supporting ring, contact between the positioning ring and the pipe wall contact face is small, heat conduction is reduced, meanwhile, the supporting ring is perforated, and the service life of the supporting ring is prolonged. According to the utility model, air circulation in the wrapping layer can be ensured, thermal deformation of the supporting structure can be compensated, and the problems that in the prior art, plastic and adhesive tape are easy to age, and the thermal insulation effect of a thermal sleeve and an air interlayer is poor are solved.

Description

Technical Field

[0001] The utility model relates to the technical field of heat insulation of air intake pipes, in particular to a heat insulation structure for a high-temperature air intake pipe of an aircraft. Background Art

[0002] The high-pressure gas in the aircraft air supply system is mainly used for systems such as engine starting and wing anti-icing. The gas from the engine bleed air system is high-temperature and high-pressure gas. During the gas transmission process, in order to prevent the surrounding components from overheating and reduce the fire risk, it is necessary to insulate the high-temperature air intake pipeline. The existing heat insulation methods mainly include winding glass wool felt, reinforced plastic film, pressure-sensitive tape with a winding tape reinforcement, or an insulating sleeve with an air interlayer.

[0003] For high-temperature pipelines around 500 °C, the pressure-sensitive tape with a winding tape reinforcement has problems such as insufficient heat resistance of the heat insulation material itself and easy aging of plastics and tapes. For the heat sleeve with an air interlayer, there is a disadvantage of poor heat insulation effect. Summary of the Utility Model

[0004] The purpose of the utility model is to solve the problems existing in the prior art, and to propose a heat insulation structure for a high-temperature air intake pipe of an aircraft.

[0005] In order to achieve the above purpose, the utility model adopts the following technical scheme:

[0006] A heat insulation structure for a high-temperature air intake pipe of an aircraft, including a pipeline main body. A plurality of groups of positioning rings are arranged on the outer side of the pipeline main body. Each group of positioning rings is provided with two, and a support ring is arranged between the two positioning rings. The support ring is sleeved on the outer side of the pipeline main body. A plurality of openings are formed on one side of the support ring, and the plurality of openings extend to the other side of the support ring. A first heat insulation layer sleeved on the outer side of the pipeline main body is arranged between the plurality of support rings. A fixing ring is arranged on the outer side of the plurality of support rings. A second heat insulation layer sleeved on the outer side of the pipeline main body is arranged on the other side of the positioning ring, and an embossed plate is arranged on the outer side of the second heat insulation layer.

[0007] Preferably, the positioning ring is fixedly connected to the outer side of the pipeline main body by spot welding.

[0008] Preferably, the production materials of the first heat insulation layer and the second heat insulation layer are both microporous heat insulation materials, and non-alkali fiberglass cloth is wrapped on the outer sides thereof.

[0009] Preferably, the production material of the support ring is zirconia ceramic or gypsum.

[0010] Preferably, the fixing ring includes two semi-fixing rings, and the two semi-fixing rings are connected by welding or a flange structure.

[0011] Preferably, a positioning groove is formed in the inner wall of the fixing ring, and the fixing ring is axially positioned with the side surface of the support ring through the positioning groove.

[0012] Preferably, a support structure is arranged on the outer side of the fixing ring. The support structure includes a plurality of mounting seats, the mounting seats are L-shaped, and mounting holes are formed in the mounting seats.

[0013] Preferably, a plurality of protrusions are arranged on the inner wall of the support ring, and the support ring is connected to the outer side of the pipeline main body through the plurality of protrusions.

[0014] Preferably, the inner wall of the embossed plate covers a part of the fixing ring, and the embossed plate is connected to the fixing ring by spot welding.

[0015] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0016] In the present utility model, welding and conventional mechanical connections are adopted as a whole, and the adhesive connection method is not adopted, so the connection is more reliable, and the problem of easy aging of the adhesive is solved. At the same time, a positioning ring is used to fix the support ring. The contact surface between the positioning ring and the pipe wall is small, reducing heat conduction. At the same time, the support ring is perforated, which can not only ensure the gas circulation inside the wrapping layer, but also play a compensating role in the thermal deformation of the support structure, solving the problems of easy aging of plastics and tapes in the prior art and the poor heat insulation effect of the hot sleeve with an air interlayer. Description of the Drawings

[0017] Figure 1 is a front sectional view of a heat insulation structure of a high-temperature air intake pipe of an aircraft proposed by the present utility model;

[0018] Figure 2 is a three-dimensional schematic diagram of a heat insulation structure of a high-temperature air intake pipe of an aircraft proposed by the present utility model;

[0019] Figure 3 is a three-dimensional schematic diagram of a support ring of a heat insulation structure of a high-temperature air intake pipe of an aircraft proposed by the present utility model;

[0020] Figure 4 is a three-dimensional schematic diagram of a fixing ring of a heat insulation structure of a high-temperature air intake pipe of an aircraft proposed by the present utility model;

[0021] Figure 5 is a three-dimensional schematic diagram of a side view angle of a heat insulation structure of a high-temperature air intake pipe of an aircraft proposed by the present utility model;

[0022] Figure 6 is a schematic diagram of a support structure of Embodiment 2 of a heat insulation structure of a high-temperature air intake pipe of an aircraft proposed by the present utility model.

[0023] In the figure: 1, pipeline main body; 2, positioning ring; 3, support ring; 4, opening; 5, first heat insulation layer; 6, fixing ring; 7, second heat insulation layer; 8, embossed plate; 9, positioning groove; 10, support structure. Specific implementation mode

[0024] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0025] Embodiment 1

[0026] Refer to Figures 1 - 5 , a heat insulation structure for an aircraft high-temperature air intake pipe, including a pipeline main body 1. Two groups of positioning rings 2 are arranged on the outer side of the pipeline main body 1. Each group of the positioning rings 2 is provided with two. A support ring 3 is arranged between the two positioning rings 2, and the support ring 3 is sleeved on the outer side of the pipeline main body 1. A plurality of openings 4 are opened on one side of the support ring 3, and the plurality of openings 4 extend to the other side of the support ring 3. A first heat insulation layer 5 sleeved on the outer side of the pipeline main body 1 is arranged between the two support rings 3. A fixing ring 6 is arranged on the outer side of the support ring 3. A second heat insulation layer 7 sleeved on the outer side of the pipeline main body 1 is arranged on the other side of the positioning ring 2, and an embossed plate 8 is arranged on the outer side of the second heat insulation layer 7;

[0027] The positioning ring 2 is fixedly connected to the outer side of the pipeline main body 1 by spot welding;

[0028] The inner wall of the embossed plate 8 covers a part of the fixing ring 6, and the embossed plate 8 is connected to the fixing ring 6 by spot welding.

[0029] The assembly steps of this device are as follows:

[0030] Step 1: Considering the fixing requirements of fireproof seals, fire alarm detection lines, pressure guiding pipes, etc., arrange the positioning rings 2 on the high-temperature pipeline. The positioning rings 2 are mainly used for the positioning of the support rings 3. Spot weld the positioning rings 2 to the air intake pipeline (i.e., the pipeline main body 1) for fixation. Only the width required for support is reserved on the contact surface between the positioning ring 2 and the pipeline main body 1, so as to reduce the heat transfer of the positioning ring 2. After the installation of the positioning ring 2 is completed, fit the support ring 3 with the positioning ring 2, then place the second positioning ring 2, and perform spot welding to ensure the fixation of the support ring 3 and complete the setting of the first support point; at the same time, in order to minimize the heat conduction of the high-temperature air intake pipeline as much as possible, remove materials from the inner wall of the support ring 3, and only the ceramic inner wall surface is left in contact with the high-temperature air intake pipeline. That is, a plurality of protrusions are arranged on the inner wall of the support ring 3, and the support ring 3 is connected to the outer side of the pipeline main body 1 through the plurality of protrusions. At the same time, in order to ensure the internal gas flow of the pipeline heat insulation layer and compensate for the thermal deformation of the pipeline and the support ring 3, openings 4 are evenly opened on the side of the support ring 3;

[0031] Step 2: According to the designed spacing, repeat the steps to set the second support point, and then wrap the first heat insulation layer 5 between the support rings 3;

[0032] Step 3: Wrap and cover the support ring 3 and the first heat insulation layer 5 with the fixing ring 6;

[0033] Step 4: Tie the second heat insulation layer 7 on both sides of the set fixed support structure 10. The material of the second heat insulation layer 7 is the same as that of the first heat insulation layer 5. Wrap the embossed plate 8 on the outer layer of the second heat insulation layer 7. After the embossed plate 8 wraps the second heat insulation layer 7, it wraps a part of the fixing ring 6, and then spot-weld the embossed plate 8 and the fixing ring 6 for fixation;

[0034] Compared with the prior art, the whole structure adopts welding and conventional mechanical connections, without using adhesive connection methods, and the connection is more reliable, solving the problem of easy aging of adhesives. At the same time, the positioning ring 2 is used to fix the support ring 3. The contact surface between the positioning ring 2 and the pipe wall is small, reducing heat conduction. At the same time, the support ring 3 is provided with openings 4, which can not only ensure the gas circulation inside the wrapping layer, but also play a compensating role in the thermal deformation of the support structure 10, solving the problems of easy aging of plastics and tapes in the prior art, and the problem of poor heat insulation effect of the thermal sleeve with an air interlayer.

[0035] In this embodiment, the production materials of the first heat insulation layer 5 and the second heat insulation layer 7 are both microporous heat insulation materials, and non-alkali fiberglass cloth is wrapped on the outside of them. The whole set of heat insulation layers has a good heat insulation effect.

[0036] In this embodiment, the production material of the support ring 3 is zirconia ceramics or gypsum, and the thermal conductivity is relatively low.

[0037] In this embodiment, the fixing ring 6 includes two semi-fixing rings 6, and the two semi-fixing rings 6 are connected by welding or by a flange structure. The inner wall of the fixing ring 6 is provided with a positioning groove 9, and the support ring 3 is axially positioned through the positioning groove 9. The positioning groove 9 forms the positioning surface on the inner side of the fixing ring 6. The inner positioning surface of the fixing ring 6 axially positions and cooperates with the side surface of the ceramic support ring 3 for axial positioning. Then, buckle the semi-fixing ring 6 on the outer layer of the other half of the support ring 3, adjust the semi-fixing ring 6 and the semi-fixing ring 6 to the appropriate position, and perform spot welding or fixation by flange at the butt joint surface between the two to complete the installation. It should be noted here that the fixation of the semi-fixing ring 6 is only for illustration. Other fixed supports can be set on the semi-fixing ring 6 according to actual fixation requirements, and the outer shape of the semi-fixing ring 6 can also be modified according to other fixation requirements. The connection method can also adopt connection forms such as 3-petal or 4-petal.

[0038] In this embodiment, a support structure 10 is provided on the outer side of the fixing ring 6. The support structure 10 includes a number of mounting seats, and the mounting seats are L-shaped. Mounting holes are provided in the mounting seats, and structures such as detection wires can be fixed through the mounting seats and the mounting holes, enabling this structure to have a support function and being more reliable. This avoids the problems of a small adhesive contact point, high requirements for the performance of the adhesive, poor reliability, and poor maintainability when using an adhesive connection form.

[0039] Embodiment 2

[0040] As Figure 6 shown, the difference between this embodiment and Embodiment 1 is that:

[0041] In this embodiment, a support structure 10 is provided on the outer side of the fixing ring 6. The support structure 10 is in the shape of a circular ring bulge. During actual implementation, the outer shape of the semi-fixing ring 6 can be modified according to actual fixing requirements. For example, in this embodiment, if a fireproof seal needs to be fixed, it can be installed on the outer side of the circular ring bulge support structure 10.

[0042] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution of the present invention and its inventive concept, makes equivalent substitutions or changes, and all should be covered within the protection scope of the present invention.

Claims

1. A heat insulation structure for a high-temperature bleed air duct of an aircraft, comprising a duct body, characterized in that: Several groups of positioning rings are arranged on the outside of the pipeline body, each group of positioning rings is provided with two, and a support ring is arranged between the two positioning rings, and the support ring is sleeved on the outside of the pipeline body, one side of the support ring is provided with several openings, and the several openings extend to the other side of the support ring, a first thermal insulation layer sleeved on the outside of the pipeline body is arranged between the several support rings, a fixing ring is arranged on the outside of the several support rings, a second thermal insulation layer sleeved on the outside of the pipeline body is arranged on the other side of the positioning ring, and an embossed plate is arranged on the outside of the second thermal insulation layer.

2. The heat insulation structure of an aircraft high temperature air bleed duct according to claim 1, characterized in that: The positioning ring is fixedly connected to the outer side of the pipeline body by spot welding.

3. The heat insulation structure of a high-temperature air bleed duct of an aircraft according to claim 1, characterized in that: The first heat insulation layer and the second heat insulation layer are both made of microporous insulation materials, and the outer sides thereof are wrapped with alkali-free glass fiber cloth.

4. The heat insulation structure of a high-temperature bleed air duct of an aircraft according to claim 1, characterized in that: The support ring is made of zirconia ceramic or gypsum.

5. The heat insulation structure of a high-temperature air bleed duct of an aircraft according to claim 1, characterized in that: The fixing ring comprises two half fixing rings, and the two half fixing rings are connected by welding or flange structure.

6. The heat insulation structure of a high-temperature bleed air duct of an aircraft according to claim 1, characterized in that: The inner wall of the fixing ring is provided with a positioning groove, and the fixing ring is axially positioned with the side surface of the supporting ring through the positioning groove.

7. The heat insulation structure of a high-temperature bleed air duct of an aircraft according to claim 1, characterized in that: A supporting structure is arranged on the outer side of the fixing ring, and the supporting structure is in the shape of a circular protrusion.

8. The heat insulation structure of a high-temperature air bleed duct of an aircraft according to claim 1, characterized in that: A supporting structure is arranged on the outer side of the fixing ring. The supporting structure comprises a plurality of mounting seats, and the mounting seats are L-shaped. The mounting seats are provided with mounting holes.

9. The heat insulation structure of a high-temperature bleed air duct of an aircraft according to claim 1, characterized in that: The inner wall of the support ring is provided with a plurality of protrusions, and the support ring is connected to the outer side of the pipeline body through the plurality of protrusions.

10. The heat insulation structure of a high-temperature bleed air duct of an aircraft according to claim 5, characterized in that: The inner wall of the embossed plate covers a portion of the fixing ring, and the embossed plate is connected to the fixing ring by spot welding.

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