Combined throat liner spraying pipe of solid rocket engine and manufacturing method

A solid rocket and engine technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as increased process difficulty and complexity, poor product quality consistency, large dispersion of material strength, etc., to achieve quality consistency Easy to guarantee, reduce the difficulty of production and processing, the effect of uniform carburizing

Active Publication Date: 2016-10-26
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] For the large-size integral throat liner, due to the limitations of the manufacturing process and equipment, when the throat liner reaches a certain bottleneck size, the difficulty and complexity of the process will be greatly increased, and the quality of the formed product will be poor in consistency. Th

Method used

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  • Combined throat liner spraying pipe of solid rocket engine and manufacturing method
  • Combined throat liner spraying pipe of solid rocket engine and manufacturing method
  • Combined throat liner spraying pipe of solid rocket engine and manufacturing method

Examples

Experimental program
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Effect test

Embodiment 1

[0033] Example 1, such as figure 1 , figure 2 , image 3 , Figure 4 As shown, a combined throat liner nozzle of a solid rocket motor includes axisymmetric rotary body structural components: a converging section heat insulation layer (1), a throat liner (2), a backing (3), a diffusion section heat insulation layer (4 ), the nozzle casing (5), the steps (9) formed by the axial cylindrical surface and the end surface are connected and sealed to assemble the nozzle between the parts, and the throat liner (2) is a combined throat liner, It is formed by connecting and sealing multiple throat inserts (21) in a stepped (9) style.

[0034] In this embodiment, the throat liner block (21) is an axial throat liner block (211) divided in the axial direction, and the specific number of throat liner blocks (21) can be adjusted according to the actual size and product equipment capacity. The example is 3 pieces; all adopt " L " type step turning bending gap 10 less than 3 times between ...

Embodiment 2

[0036] Example 2, such as Figure 5 , Figure 6 , Figure 7 As shown, a combined throat liner nozzle of a solid rocket motor includes axisymmetric rotary body structural components: a converging section heat insulation layer (1), a throat liner (2), a backing (3), a diffusion section heat insulation layer (4 ), the nozzle casing (5), the steps (9) formed by the axial cylindrical surface and the end surface are connected and sealed to assemble the nozzle between the parts, and the throat liner (2) is a combined throat liner, It is formed by connecting and sealing multiple throat inserts (21) in a stepped (9) style.

[0037] In this embodiment, the throat lining block (21) is a radial throat lining block (212) divided in the radial direction, and the specific number of throat lining blocks (21) can be adjusted according to the actual size and product equipment capacity. For example, there are 3 pieces; the radial throat liner blocks (212) are connected and sealed by "L"-shape...

Embodiment 3

[0039] Example 3, such as Figure 5 , Figure 6 , Figure 7 As shown, a combined throat liner nozzle of a solid rocket motor includes axisymmetric rotary body structural components: a converging section heat insulation layer (1), a throat liner (2), a backing (3), a diffusion section heat insulation layer (4 ), the nozzle casing (5), the steps (9) formed by the axial cylindrical surface and the end surface are connected and sealed to assemble the nozzle between the parts, and the throat liner (2) is a combined throat liner, It is formed by connecting and sealing multiple throat inserts (21) in a stepped (9) style.

[0040] In this embodiment, the throat lining block (21) is a two-way throat lining block (213) that is divided axially or radially. The specific number of throat lining blocks (21) can be determined according to the actual size and product equipment capacity The situation is adjusted, and the present embodiment has 9 pieces, which are divided into 3 sections in ...

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PUM

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Abstract

The invention discloses a combined throat liner spraying pipe of a solid rocket engine and a manufacturing method. The spraying pipe comprises axisymmetric rotating body structural components comprising a convergent segment heat insulating layer, a throat liner, a backing, a diffusion segment heat insulating layer and a spraying pipe shell; the components are connected and sealed through steps formed by axial cylindrical faces and end faces so as to be assembled into the spraying pipe; and the throat liner is a combined throat liner and combined by connecting and sealing a plurality of throat liner blocks in a step manner. According to the combined throat liner spraying pipe of the solid rocket engine, the integral throat liner is divided into the multiple throat liner blocks each of a special structural type; every two throat liner blocks are connected and sealed through an assembling process so that the combined throat liner can be formed; and then the combined throat liner and the other axisymmetric rotating body structural components of the spraying pipe are assembled into the spraying pipe according to an existing corresponding assembling manner. Raw materials can be effectively saved, and the process preparing and machining cost is also reduced; and meanwhile, because the size of each single throat liner block is reduced, the thickness is reduced, the carburizing is even, and the product quality consistency can be guaranteed more easily.

Description

technical field [0001] The invention belongs to the field of solid rocket motors, in particular to a combined throat liner nozzle of the solid rocket motor and a manufacturing method. Background technique [0002] The throat diameter of the corresponding nozzle of the existing large-diameter solid rocket motor is large, that is, the throat lining of the nozzle is also large. The throat lining of the nozzle is generally an integral throat lining, which is integrally produced and machined, and the structure is an axisymmetric rotary structure. , the inner surface of the throat liner converges first and then expands, and the end surface of the outer surface and other axisymmetric rotary structural parts of the nozzle include the heat insulation layer of the convergent section, the backing, the heat insulation layer of the diffuser section, and the nozzle casing. The steps formed by the axial cylindrical surface and the end surface between the parts are connected and sealed to f...

Claims

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Application Information

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IPC IPC(8): F02K9/97
CPCF02K9/97F02K9/974F05D2230/51
Inventor 许玉荣钟志文周生攀徐节荣于泉陈文杰司学龙
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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