High-temperature heat insulation cover and aircraft nozzle assembly based on phase change heat storage

Abstract

The present application relates to a high-temperature heat insulation cover and an aircraft nozzle assembly based on phase change heat storage, and relates to the technical field of aerospace aircraft design. The high-temperature heat insulation cover includes an aerogel layer and a phase change heat storage encapsulation layer that are sequentially distributed and connected from the nozzle to the cabin section. The phase change heat storage encapsulation layer includes an encapsulation shell and a phase change energy storage material. The encapsulation shell has an accommodation cavity; the phase change energy storage material is filled in the accommodation cavity; and the thickness of the aerogel layer is adapted such that after the heat source of the nozzle passes through the heat insulation of the aerogel layer, the heat transferred to the phase change heat storage encapsulation layer reaches the phase transition temperature of the phase change energy storage material. The aircraft nozzle assembly includes a nozzle and a cabin section, and an insulation space is formed between the cabin section and the nozzle; the high-temperature heat insulation cover is provided in the insulation space. The aerogel layer isolates and blocks a large amount of heat generated by the nozzle, and the phase change energy storage material absorbs heat and stores energy, greatly reducing the heat entering the interior of the cabin section, improving the working environment of important single machines inside the cabin section, and realizing the long-term stable operation of the aircraft.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace vehicle design, and particularly relates to a high-temperature heat insulation shield and an aircraft nozzle assembly based on phase change heat storage. Background Art

[0002] When an aircraft flies at high speed in the atmosphere for a long time, the total external aerodynamic heating reaches the gigawatt level. At the same time, the temperature of the large-area outer wall of the built-in nozzle reaches above 1000°C for a long time. Under the constraint of a compact space layout, the internal space temperature and single-unit thermal management are one of the core elements restricting aircraft design. The cabin section where the nozzle is located generally integrates important single units, which is crucial for aircraft control. The design of the nozzle heat insulation shield is extremely difficult. The application of materials at high temperatures has exceeded the use limit of traditional materials, posing higher requirements for the overall mechanical properties, heat resistance, and overall processing technology of the materials, and becoming one of the important contents of the overall energy management technology.

[0003] Currently, the research on high-temperature insulation of the tail nozzle mainly uses pure passive insulation methods such as aerogel materials or sandwich combinations to delay the conduction of high-temperature heat energy at the tail nozzle to the cabin section, avoid the rapid and excessive rise of the cabin temperature, and ensure the operation of the instruments in the cabin at normal temperatures. With the extension of flight time, as well as the weight reduction and space compactification design of the aircraft, for high-speed aircraft, this method is difficult to achieve satisfactory results.

[0004] To ensure flight safety, corresponding thermal protection materials must be combined to ensure the normal operation of the aircraft. At present, the improvement of the thermal protection materials and structures used in this type of heat insulation shield has reached a bottleneck. The research on the high-temperature heat insulation method combining active and passive based on phase change heat storage can further improve the heat insulation ability in a limited space, which is of great significance for protecting the single-unit equipment in the cabin. Summary of the Invention

[0005] The embodiments of the present application provide a high-temperature heat insulation shield and an aircraft nozzle assembly based on phase change heat storage to solve the problem that the pure passive heat insulation shield structures such as aerogel materials or sandwich combinations in the related art cannot meet the long-term stable operation of the aircraft.

[0006] In a first aspect, a high-temperature heat insulation shield based on phase change heat storage is provided, which includes an aerogel layer and a phase change heat storage encapsulation layer that are distributed and connected in sequence from the nozzle to the cabin section. The phase change heat storage encapsulation layer includes:

[0007] An encapsulation shell having an accommodation cavity therein;

[0008] A phase change energy storage material filled in the accommodation cavity; and,

[0009] The thickness of the aerogel layer is adapted such that after the heat source of the nozzle passes through the heat insulation of the aerogel layer, the heat transferred to the phase change heat storage encapsulation layer reaches the phase transition temperature of the phase change energy storage material.

[0010] In some embodiments, one side of the encapsulation shell close to the aerogel layer is a corrugated structure, and the encapsulation shell is connected to the aerogel layer through the corrugated structure.

[0011] In some embodiments, the phase change heat storage encapsulation layer further includes a partition plate, the partition plate is arranged in the encapsulation shell, and divides the accommodation cavity into a first sub-accommodation cavity far from the aerogel layer and a second sub-accommodation cavity close to the aerogel layer, and the phase change energy storage material is filled in the first sub-accommodation cavity.

[0012] In some embodiments, the high-temperature heat insulation cover further includes a first reflective layer, the first reflective layer is located in the second sub-accommodation cavity and is arranged on the partition plate.

[0013] In some embodiments, the phase change heat storage encapsulation layer further includes a lattice structure, the lattice structure is a plurality of protruding parts protruding from the inner wall of the encapsulation shell, and the protruding parts are connected to the side of the first reflective layer far from the partition plate.

[0014] In some embodiments, the high-temperature heat insulation cover further includes a second reflective layer, and the second reflective layer is arranged on the side of the aerogel layer far from the phase change heat storage encapsulation layer.

[0015] In some embodiments, the reflectivity of the material used for the second reflective layer is not less than 0.85.

[0016] In some embodiments, the accommodation cavity is a vacuum cavity.

[0017] In a second aspect, a nozzle assembly of an aircraft is provided, which includes:

[0018] A nozzle;

[0019] A cabin section, an insulation space is formed between it and the nozzle; and,

[0020] The above-mentioned high-temperature heat insulation cover based on phase change heat storage, and the high-temperature heat insulation cover based on phase change heat storage is arranged in the insulation space.

[0021] In some embodiments, one side of the high-temperature heat insulation cover based on phase change heat storage is connected to the inner surface of the cabin section, and there is a gap between the other side and the outer surface of the nozzle.

[0022] The beneficial effects brought by the technical solutions provided in this application include:

[0023] (1) The present application adopts a technical solution that combines aerogel and phase change energy storage materials. The aerogel layer isolates and blocks as much heat generated by the nozzle as possible. By designing the thickness of the aerogel layer, the heat source of the nozzle, after being insulated by the aerogel layer, transfers heat to the phase change heat storage encapsulation layer to reach the phase transition temperature of the phase change energy storage material, so that the phase change energy storage material absorbs heat and stores energy, greatly reducing the heat entering the interior of the cabin section, improving the working environment of important single machines inside the cabin section, and realizing the long-term stable operation of the aircraft.

[0024] (2) The aerogel layer and the phase change heat storage encapsulation layer in the present application are connected through a corrugated structure, reducing the contact area between the two, increasing the thermal resistance, and minimizing the heat conduction between the aerogel layer and the phase change heat storage encapsulation layer as much as possible.

[0025] (3) The high-temperature heat insulation cover of the present application further includes a first reflective layer, which is located in the second sub-accommodation cavity and is provided on the partition board. By designing the first reflective layer, part of the heat is further reflected and blocked. And after setting the first reflective layer on the partition board, the phase change energy storage material reaches a certain applicable range. Using the limited space, an encapsulated phase change energy storage material can be designed to further control the cold surface temperature facing the interior of the cabin section.

[0026] (4) The present application connects the first reflective layer and the encapsulation shell through a lattice structure, reducing the contact area between the two, increasing the thermal resistance, and minimizing the heat conduction between the aerogel layer and the first reflective layer 5 as much as possible.

[0027] (5) The present application further attaches a high-temperature resistant and high-reflectivity flexible ceramic coating or other high-reflectivity materials to the aerogel layer to block the radiant heat generated by the nozzle and form a first heat insulation barrier.

[0028] (6) The present application adopts a vacuum pumping method inside the accommodation cavity, making the heat conduction inside the accommodation cavity mainly radiation.

[0029] (7) The high-temperature heat insulation cover based on phase change heat storage of the present application has a certain gap with the nozzle to block, making the heat exchange method between the nozzle and the heat insulation cover mainly radiant heat and convective heat transfer. When the flight altitude reaches a certain level, the air density is small. On the premise of ensuring the heat insulation and sealing between the end face of the heat insulation cover and the interior of the cabin section, the convective heat transfer between the nozzle and the heat insulation cover is extremely weak, and radiant heat becomes the main heat exchange form. Description of the Drawings

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0031] Figure 1 A cross-sectional view of the high-temperature heat insulation cover based on phase change heat storage provided by the embodiment of the present application;

[0032] Figure 2 A cross-sectional view of the nozzle assembly of the aircraft provided by the embodiment of the present application;

[0033] Figure 3 The improvement effect of the nozzle heat insulation in the medium and low temperature section of 1000 °C provided by the embodiment of the present application.

[0034] In the figure: 1, nozzle; 2, cabin section; 3, aerogel layer; 4, phase change heat storage encapsulation layer; 40, encapsulation shell; 400, first sub-accommodation cavity; 401, second sub-accommodation cavity; 41, phase change energy storage material; 42, corrugated structure; 43, partition; 44, lattice structure; 5, first reflection layer; 6, second reflection layer. Detailed implementation manners

[0035] To make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Apparently, the described embodiments are some, but not all, of the embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts shall fall within the protection scope of the present application.

[0036] Embodiment 1:

[0037] Refer to Figure 1 As shown, Embodiment 1 of the present application provides a high-temperature heat insulation cover based on phase change heat storage, which includes an aerogel layer 3 and a phase change heat storage encapsulation layer 4 that are sequentially distributed and connected along the nozzle 1 to the cabin section 2. The phase change heat storage encapsulation layer 4 includes an encapsulation shell 40 and a phase change energy storage material 41. The encapsulation shell 40 has an accommodation cavity; the phase change energy storage material 41 is filled in the accommodation cavity; and, the thickness of the aerogel layer 3 is adapted such that: after the heat source of the nozzle 1 is insulated by the aerogel layer 3, the heat transferred to the phase change heat storage encapsulation layer 4 reaches the phase transition temperature of the phase change energy storage material 41.

[0038] The large-area radiation temperature of a certain aircraft nozzle 1 reaches above 1000 °C. After only using a certain thickness of aerogel for heat insulation, the cold surface temperature can only be reduced to 600 - 800 °C within 1500 s.

[0039] The present application adopts a technical solution that combines aerogel and phase change energy storage materials. The aerogel layer 3 isolates and blocks the large amount of heat generated by the nozzle 1 as much as possible, and by designing the thickness of the aerogel layer 3, the heat source of the nozzle 1 is insulated by the aerogel layer 3, and the heat transferred to the phase change heat storage packaging layer 4 reaches the phase transition temperature of the phase change energy storage material 41, so that the phase change energy storage material 41 absorbs heat and stores energy, greatly reducing the amount of heat entering the interior of the cabin 2, improving the working environment of important single machines inside the cabin 2, and realizing long-term stable operation of the aircraft.

[0040] Furthermore, a side of the packaging shell 40 close to the aerogel layer 3 is a corrugated structure 42 , and the packaging shell 40 is connected to the aerogel layer 3 via the corrugated structure 42 .

[0041] The aerogel layer 3 and the phase change heat storage packaging layer 4 are connected by a corrugated structure 42, which reduces the contact area between the two, increases the thermal resistance, and minimizes the heat conduction between the aerogel layer 3 and the phase change heat storage packaging layer 4.

[0042] Preferably, the phase change heat storage packaging layer 4 also includes a partition 43, which is arranged in the packaging shell 40 and divides the accommodating cavity into a first sub-accommodating cavity 400 away from the aerogel layer 3, and a second sub-accommodating cavity 401 close to the aerogel layer 3, and the phase change energy storage material 41 is filled in the first sub-accommodating cavity 400.

[0043] A titanium alloy layer is provided on the outer wall of the packaging shell 40 away from the aerogel layer 3 and on the side of the partition 43 close to the aerogel layer 3 to further reduce the heat conduction between the aerogel layer 3 and the phase change heat storage packaging layer 4.

[0044] Furthermore, the high temperature heat insulation cover further comprises a first reflective layer 5 , which is located in the second sub-accommodation 401 cavity and is disposed on the partition 43 .

[0045] The first reflective layer 5 is made of high-temperature, high-reflective flexible ceramic coating or other materials with a high reflectivity of more than 0.85. By designing the first reflective layer 5, part of the heat is further reflected and blocked. After the first reflective layer 5 is set on the partition 43, the phase change energy storage material 41 reaches a certain application range. By utilizing limited space and designing a packaged phase change energy storage material, the temperature of the cold surface facing the interior of the cabin 2 can be further controlled.

[0046] Preferably, the phase-change heat storage packaging layer 4 further includes a lattice structure 44 , which includes a plurality of protrusions protruding from the inner wall of the packaging shell 40 , and the protrusions are connected to a side of the first reflective layer 5 away from the partition 43 .

[0047] The first reflective layer 5 and the packaging shell 40 are connected via a lattice structure 44 to reduce the contact area between the two, increase thermal resistance, and minimize heat conduction between the aerogel layer 3 and the first reflective layer 5.

[0048] Further, the high-temperature heat insulation cover further includes a second reflective layer 6, and the second reflective layer 6 is disposed on a side of the aerogel layer 3 away from the phase change heat storage encapsulation layer 4.

[0049] In an embodiment of the present application, a high-temperature and high-reflectivity flexible ceramic coating or other high-reflectivity materials are further attached to the aerogel layer 2 to block the radiant heat generated by the nozzle 1 and form a first heat insulation barrier.

[0050] Furthermore, the reflectivity of the material used for the second reflective layer 6 is not less than 0.85.

[0051] The second reflective layer 6 in the embodiment of the present application is made of a high-temperature and high-reflective flexible ceramic coating or other materials with a reflectivity above 0.85.

[0052] Optionally, the accommodating cavity is a vacuum cavity.

[0053] Inside the accommodating cavity, a vacuum pumping method is adopted to make the heat conduction inside the accommodating cavity mainly radiation-based.

[0054] Embodiment 2:

[0055] See Figure 2 As shown, an embodiment of the present application provides an aircraft nozzle assembly, which includes a nozzle 1, a cabin section 2, and a high-temperature heat insulation cover based on phase change heat storage. An insulation space is formed between the cabin section 2 and the nozzle 1, and the high-temperature heat insulation cover based on phase change heat storage is disposed in the insulation space.

[0056] In the aircraft nozzle assembly of Embodiment 2 of the present application, heat insulation is carried out between the nozzle 1 and the cabin section 2 through the high-temperature heat insulation cover based on phase change heat storage. The high-temperature heat insulation cover based on phase change heat storage adopts a technical solution combining aerogel and phase change energy storage materials. The aerogel layer 3 isolates and blocks as much heat generated by the nozzle 1 as possible, and by designing the thickness of the aerogel layer 3, the heat source of the nozzle 1 passes through the heat insulation of the aerogel layer 3, and the heat transferred to the phase change heat storage encapsulation layer 4 reaches the phase transition temperature of the phase change energy storage material 41, so that the phase change energy storage material 41 absorbs heat and stores energy, greatly reducing the heat entering the interior of the cabin section 2, improving the working environment of important single machines inside the cabin section 2, and realizing the long-term stable operation of the aircraft.

[0057] Further, one side of the high-temperature heat insulation cover based on phase change heat storage is connected to the inner surface of the cabin section 2, and a gap is left between the other side and the outer surface of the nozzle 1.

[0058] The high-temperature heat insulation cover based on phase change heat storage and the nozzle 1 are blocked with a certain gap, so that the heat transfer mode between the nozzle 1 and the heat insulation cover is mainly radiative heat and convective heat transfer. When the flight altitude reaches a certain level, the air density is small. On the premise of ensuring the heat insulation and sealing of the end face of the heat insulation cover and the interior of the cabin section 2, the convective heat transfer between the nozzle 1 and the heat insulation cover is extremely weak, and radiative heat becomes the main heat transfer form. Using the high-temperature heat insulation cover based on phase change heat storage of the present application to insulate the nozzle 1 and the cabin section 2 of the aircraft, there is no need to change the nozzle profile and the internal structure size of the aircraft. In a limited space, during the whole flight process of the aircraft in the atmosphere, the internal thermal environment of the cabin section can be improved to a large extent. The specific improvement effects are as follows:

[0059] See Figure 3 As shown, for the improvement effect of the nozzle heat insulation in the medium and low temperature section of 1000°C: when the gap between the heat insulation cover and the nozzle 1 is kept at 3 mm and the same second reflective layer 6 is used, if the scheme of simply using an 18-mm aerogel layer 3 is adopted, the cold surface temperature of the cabin section 2 after 1000 s of heat insulation reaches 480°C, and the cold surface temperature of the cabin section 2 after 1500 s of heat insulation reaches 630°C; while using the scheme of combining a 12-mm aerogel layer 3 with a 6-mm phase change heat storage encapsulation layer 4 for heat insulation, the cold surface temperature of the cabin section 2 at the 1000 s moment is only 70°C, and the cold surface temperature of the cabin section 2 at the 1500 s moment is only 120°C.

[0060] In the description of the present application, it should be noted that the orientation or positional relationship indicated by terms such as "upper" and "lower" is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, so it cannot be understood as a limitation to the present application. Unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" 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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0061] It should be noted that in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "comprising an..." does not exclude the presence of additional identical elements in the process, method, article or device comprising the said element.

[0062] The above are only specific embodiments of this application, enabling those skilled in the art to understand or implement this application. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application will not be limited to these embodiments shown herein, but rather will conform to the broadest scope consistent with the principles and novel features claimed herein.

Claims

1. A high-temperature heat insulation cover based on phase change heat storage, characterized in that, It includes an aerogel layer (3) and a phase change heat storage encapsulation layer (4) which are distributed and connected in sequence from the nozzle (1) to the cabin section (2), and the phase change heat storage encapsulation layer (4) includes: An encapsulation shell (40) which has an accommodation cavity therein; A phase change energy storage material (41) which is filled in the accommodation cavity; and, The thickness of the aerogel layer (3) is adapted such that after the heat source of the nozzle (1) is insulated by the aerogel layer (3), the heat transferred to the phase change heat storage encapsulation layer (4) reaches the phase transition temperature of the phase change energy storage material (41); One side of the encapsulation shell (40) close to the aerogel layer (3) is a corrugated structure (42), and the encapsulation shell (40) is connected to the aerogel layer (3) through the corrugated structure (42); The phase change heat storage encapsulation layer (4) further includes a partition plate (43), the partition plate (43) is arranged in the encapsulation shell (40), and divides the accommodation cavity into a first sub-accommodation cavity (400) far from the aerogel layer (3) and a second sub-accommodation cavity (401) close to the aerogel layer (3), and the phase change energy storage material (41) is filled in the first sub-accommodation cavity (400); This high-temperature heat insulation cover further includes a first reflective layer (5), the first reflective layer (5) is located in the second sub-accommodation cavity (401) and is arranged on the partition plate (43); The phase change heat storage encapsulation layer (4) further includes a lattice structure (44), the lattice structure (44) includes a plurality of protrusions protruding from the inner wall of the encapsulation shell (40), and the protrusions are connected to the side of the first reflective layer (5) far from the partition plate (43).

2. The high-temperature heat insulation cover based on phase change heat storage according to claim 1, wherein This high-temperature heat insulation cover further includes a second reflective layer (6), the second reflective layer (6) is arranged on the side of the aerogel layer (3) far from the phase change heat storage encapsulation layer (4).

3. The high-temperature heat insulation cover based on phase change heat storage according to claim 2, wherein The reflectivity of the material used for the second reflective layer (6) is not less than 0.

85.

4. The high-temperature heat insulation cover based on phase change heat storage according to claim 1, characterized in that The accommodation cavity is a vacuum cavity.

5. An aircraft nozzle assembly, characterized in that, It includes: A nozzle (1); A cabin section (2) which forms a heat insulation space with the nozzle (1); And, The high-temperature heat insulation cover based on phase change heat storage as described in claim 1, and the high-temperature heat insulation cover based on phase change heat storage is arranged in the heat insulation space.

6. The aircraft nozzle assembly according to claim 5, wherein, One side of the high-temperature heat insulation cover based on phase change heat storage is connected to the inner surface of the cabin section (2), and there is a gap between the other side and the outer surface of the nozzle (1).

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