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Liquid rocket engine combustion chamber outer wall and assembling process thereof

A liquid rocket and combustion chamber technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of unfavorable sandwich structure design in the production and assembly of liquid rocket engine combustion chambers, and ensure structural integrity and structural strength. The effect of reduced weight, ease of assembly and manufacturing

Pending Publication Date: 2020-12-11
航天科工火箭技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of this, the purpose of the present invention is to overcome the deficiencies of the prior art. In the first aspect, a liquid rocket engine combustion chamber is provided to solve the problem that the sandwich structure design of the throat section in the prior art is not conducive to the liquid rocket engine combustion chamber. Technical problems in production and assembly

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  • Liquid rocket engine combustion chamber outer wall and assembling process thereof
  • Liquid rocket engine combustion chamber outer wall and assembling process thereof
  • Liquid rocket engine combustion chamber outer wall and assembling process thereof

Examples

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Embodiment 1

[0040] The invention provides a liquid rocket engine combustor outer wall, such as figure 1 and figure 2 As shown, it includes three parts: a straight section 1 , a throat section 2 and an expansion section 3 , wherein the throat section 2 includes two parts: a first throat section 21 and a second throat section 22 . The straight section 1 and the expansion section 3 are integral cylinder structures respectively, and the minimum inner diameter D2 of the expansion section 3 is larger than the inner diameter D1 of the straight section 1 to facilitate the assembly of the expansion section 3 . The throat section 2 is in the shape of a Laval tube as a whole to meet the requirements for assembly with the inner wall 4 of the combustion chamber. Between the ends of the straight section 1 and the throat section 2, between the ends of the throat section 2 and the expansion section 3, and between the fractures of the first throat section 21 and the second throat section 22, positioning...

Embodiment 2

[0050] The present invention also provides an assembly process for the outer wall of the liquid rocket engine combustor, such as Figure 5 As shown, the outer wall of the combustor of the above-mentioned liquid rocket engine is adopted. First, since the minimum inner diameter D2 of the expansion section 3 is greater than the inner diameter D1 of the straight section 1, the expansion section 3 can be inserted from one end of the straight section 1 to the outer surface of the combustion chamber wall 4, and the expansion section 3 and the combustion chamber wall 4 Fitted ends. Then, the first throat section 21 and the second throat section 22 are respectively assembled on the outer surface of the combustion chamber wall 4, and the first throat section 21 and the second throat section 22 pass through the first stop 51 and The second spigot 52 is positioned to form the throat section 2 in the shape of a Laval tube. The entire throat section 2 slides butts with the expansion secti...

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Abstract

The invention discloses a liquid rocket engine combustion chamber outer wall and an assembling process thereof, and relates to the technical field of liquid rocket engines. Through the liquid rocket engine combustion chamber outer wall and the assembling process thereof, the technical problem that the sandwich structure design of a throat section in the prior art is not beneficial to production and assembly of a liquid rocket engine combustion chamber is solved. The liquid rocket engine combustion chamber outer wall comprises a straight tube section, a throat section and an expansion section;the straight tube section and the expansion section are of integrated structures respectively; the minimum inner diameter of the expansion section is larger than the inner diameter of the straight tube section; the throat section is of a split structure, and the whole throat section is in the shape of a Laval tube; and positioning connecting parts which are butt-jointed with each other in a sliding mode are arranged between the end parts of the straight cylinder section, the throat section and the expansion section. According to the liquid rocket engine combustion chamber outer wall and the assembling process thereof, as the straight cylinder section, the throat section and the expansion section are positioned and connected through the positioning connecting parts in a sliding fit mode, the assembling precision of all parts is guaranteed, so that the structural integrity and the structural strength of the outer wall of the combustion chamber are effectively guaranteed; and the whole throat section is made into the shape of the Laval tube, and the design of a sandwich structure is eliminated.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engines, in particular to an outer wall of a liquid rocket engine combustor and an assembly process thereof. Background technique [0002] The manufacturing schemes of grooved structure combustion chambers of liquid rocket engines at home and abroad are divided into two methods: electroforming and diffusion welding (including brazing). Among them, the electroforming solution has long production cycle, low efficiency, heavy weight and serious environmental pollution during the production process. The diffusion welding scheme has a short production cycle, high efficiency, and the outer wall can be made of lighter high-strength steel or high-temperature alloy steel, which is more and more favored by liquid rocket engine engineers at home and abroad. However, it is difficult to design the structural scheme of the engine combustion chamber by diffusion welding. Most of the structural design sche...

Claims

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Application Information

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IPC IPC(8): F02K9/62B23K20/02B23K1/00B23K15/00B23K26/21
CPCF02K9/62B23K20/02B23K1/0008B23K15/0006B23K26/21
Inventor 姬威信刘鑫鹏孙晓伟邵艳刘岳朱丹高翔查雄权姚少君
Owner 航天科工火箭技术有限公司