Ceramic-coated high-silica phenolic aldehyde composite material heat insulation structure

Abstract

The utility model discloses a ceramic-coated high-silica phenolic aldehyde composite material heat insulation structure, which belongs to the technical field of heat insulation equipment, and is technically characterized by comprising a shell and a heat insulation layer, the heat insulation layer is arranged on the inner wall of the shell, and the shell is attached to the heat insulation layer; and the coating layer is arranged in the heat insulation layer, the coating layer is attached to the heat insulation layer, and the solid rocket engine rear-section spray pipe has the advantages that the working time of the solid rocket engine rear-section spray pipe in the high-temperature state is prolonged, direct contact between fuel gas wake flow and the heat insulation layer can be hindered, the decomposition speed of the heat insulation layer is slowed down, and the working time of the heat insulation layer is prolonged.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of heat insulation equipment, specifically relates to a ceramic cladding high silica oxygen phenolic composite material heat insulation structure. BACKGROUND

[0002] As an important component of solid rocket engine, the performance of the heat insulation layer greatly influences the working time and stability of the engine, and with the continuous updating of the engine, higher requirements are put forward for the performance of the heat insulation layer. At present, the mainstream heat insulation layer is bonded to the inside of the metal shell to insulate most of the heat by using a composite material with low thermal conductivity.

[0003] At present, the tail end structure of this structure type is mainly bonded by a shell and a heat insulation layer. During the working period of the nozzle tail section of this structure, the high-temperature exhaust flame in the combustion chamber will directly burn the composite material of the heat insulation layer, and part of the composite material will be oxidized and decomposed at high temperature, so that the heat insulation layer is consumed and the thickness is reduced during working, and at this time, the heat insulation capacity of the heat insulation layer will be weakened, so this structure cannot work continuously for a long time at high temperature.

[0004] If the heat insulation layer is to work for a long time, it is necessary to slow down or prevent the decomposition of the heat insulation layer at high temperature to ensure the thickness and performance of the heat insulation layer. A protective layer that is not easy to decompose and resistant to high temperature can be bonded inside the heat insulation layer to isolate the engine exhaust flame and the heat insulation layer of the nozzle rear section, so as to slow down the decomposition of the heat insulation layer. SUMMARY

[0005] In view of the deficiencies in the prior art, the purpose of the embodiments of the utility model is to provide a ceramic cladding high silica oxygen phenolic composite material heat insulation structure to solve the problems in the background art.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical scheme:

[0007] A ceramic cladding high silica oxygen phenolic composite material heat insulation structure, comprising a shell, further comprising:

[0008] A heat insulation layer, the heat insulation layer is arranged on the inner wall of the shell, and the shell is attached to the heat insulation layer;

[0009] A cladding layer, the cladding layer is arranged in the heat insulation layer, and the cladding layer is attached to the heat insulation layer.

[0010] As a further scheme of the utility model, the shell adopts a metal shell.

[0011] As a further scheme of the utility model, the heat insulation layer adopts a high silica oxygen phenolic heat insulation layer.

[0012] As a further scheme of the utility model, the cladding layer adopts a ceramic cladding layer.

[0013] As a further scheme of the utility model, the heat insulation layer and the shell are integrally molded and connected, and the cladding layer is connected through high-temperature sintering.

[0014] Compared with the prior art, the utility model has the following beneficial effects:

[0015] The utility model prolongs the working time of the solid rocket engine nozzle in a high-temperature state by bonding a protective layer inside the heat insulation layer to slow down the decomposition of the heat insulation layer.

[0016] To make the structure features and effects of the utility model clearer, the utility model will be described in detail below in combination with the drawings and specific embodiments. DRAWINGS

[0017] Figure 1 It is a structural schematic view of the utility model embodiment.

[0018] Figure 2 It is a structural schematic view of the shell in the utility model embodiment.

[0019] Figure 3 It is a structural schematic view of the heat insulation layer in the utility model embodiment.

[0020] Figure 4 It is a structural schematic view of the cladding layer in the utility model embodiment.

[0021] Reference signs: 1 - cladding layer, 2 - heat insulation layer, 3 - shell. DETAILED DESCRIPTION

[0022] To make the structure features and effects of the utility model clearer, the utility model will be described in detail below in combination with the drawings and specific embodiments.

[0023] The specific implementation of the utility model will be described in detail below in combination with specific embodiments.

[0024] In one embodiment, a ceramic cladding high-silicon-oxide phenolic composite material heat insulation structure, referring to Figures 1-4 , comprises a shell 3, and further comprises:

[0025] An adiabatic layer 2 is arranged on the inner wall of the shell 3, and the shell 3 is attached to the adiabatic layer 2.

[0026] An overcoat layer 1 is arranged in the adiabatic layer 2, and the overcoat layer 1 is attached to the adiabatic layer 2.

[0027] Further, referring to Figures 1-4 The shell 3 is a metal shell.

[0028] Further, referring to Figures 1-4 The adiabatic layer 2 is a high-silica phenolic adiabatic layer.

[0029] Further, referring to Figures 1-4 The overcoat layer 1 is a ceramic overcoat layer.

[0030] Further, referring to Figures 1-4 The adiabatic layer 2 is integrally connected to the shell 3 by molding and curing, and the overcoat layer 1 is sintered at high temperature.

[0031] In the embodiment, the adiabatic layer protection structure is used to slow down the decomposition speed of the internal adiabatic layer, isolate the direct contact between the afterflame and the adiabatic layer, and reduce the decomposition speed of the adiabatic layer due to the high-temperature afterflame erosion.

[0032] The mixed adhesive is used to reinforce the gap connection between the protection layers, the ceramic powder is mixed with the adhesive, and the adhesive penetrates into the gap of the ceramic overcoat layer. The adhesive plays a major bonding role at room temperature, and the ceramic expands under heat and presses the ceramic powder under high-temperature conditions, thereby increasing the static friction and preventing the displacement of the protection layers.

[0033] The adiabatic layer protection material has low thermal decomposition speed, high-temperature ablation resistance, and stable performance, and the thermal stability of the ceramic is extremely high, and the ceramic is not easy to oxidize and decompose under high-temperature conditions, and the structure is not easy to deform after forming.

[0034] The structural designability can adapt to most structures, and the structure of the protection layer before forming is determined by molding design, and various structures can be designed by molding.

[0035] A layer of overcoat layer 1 is adhered inside the adiabatic layer 2 to slow down the decomposition of the adiabatic layer 2, thereby prolonging the working time of the solid rocket engine nozzle in the high-temperature state. The advantage of this structure is that it can hinder the direct contact between the gas afterflow and the adiabatic layer 2. Compared with the traditional adiabatic layer, an external layer of high-temperature-resistant overcoat layer 1 can slow down the decomposition speed of the adiabatic layer and increase the working time of the adiabatic layer.

[0036] The adiabatic layer 2 (high-silica phenolic adiabatic layer) is integrally connected to the shell 3 (metal shell) by molding and curing. The combination of the machined adiabatic layer 2 and the shell 3 is molded. The overcoat layer 1 (ceramic overcoat layer) is molded and sintered at high temperature after the ceramic powder is loaded into a mold of appropriate size.

[0037] Cut the cladding layer 1 into assemblies at an angle to ensure that the assemblies can be smoothly loaded into the combination heat insulation layer 2 and the shell 3, infiltrate the ceramic powder and glue mixture at the joint of the assembly, and vacuum hot-press forming. Polishing the finished product.

[0038] The above merely describes the preferred embodiments of the present application and is not intended to limit the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A ceramic-coated high-silica phenolic composite thermal insulation structure comprising a shell, characterized in that, Also include: Thermal insulation layer, the thermal insulation layer is arranged in the shell inner wall, the shell fits the thermal insulation layer; Cladding layer, the cladding layer is arranged in the thermal insulation layer, the cladding layer fits the thermal insulation layer; The shell adopts a metal shell; The thermal insulation layer adopts a high-silica phenolic insulation layer; The cladding layer adopts a ceramic cladding layer.

2. The ceramic-coated high-silica phenolic composite thermal barrier structure of claim 1, wherein, The thermal insulation layer and shell adopt integral mold curing connection, and the cladding layer is sintered by high temperature.

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