Slotted coaxial pintle type injector thrust chamber

A technology of injectors and thrust chambers, which is applied in the field of liquid rocket engines, can solve problems such as technical difficulties, achieve broad application prospects, improve combustion performance, and reduce the effect of splashing

Active Publication Date: 2014-12-24
NO 11 INST OF NO 6 ACADEMY OF CHINA AEROSPACE SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Due to relying on the injector, it is necessary to organize efficient combustion and achieve the goal o

Method used

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  • Slotted coaxial pintle type injector thrust chamber
  • Slotted coaxial pintle type injector thrust chamber
  • Slotted coaxial pintle type injector thrust chamber

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] Such as figure 1 , Figure 4 The central cylinder 7 shown is one of the key parts of the embodiment. The end notches 16 of the central cylinder 7 are evenly spaced, different in size, and staggered T-shaped grooves and rectangular grooves. The T-shaped groove 13 is the main groove. The rectangular groove 14 is an auxiliary groove, and the impact of multiple radial jets ejected from the radial nozzle 13 and the annular liquid film of the axial outer ring ejected from the annular nozzle 15 ensures that the two propellants are collided to form a good friction The large-gradient radial mixing ratio distribution not only improves the efficiency but also realizes the penetration of part of the fuel to fully cool the body. Part of the jet flows along the surface of the splash plate 9 after hitting the click wall. The notch design is optimized according to the blocking rate, the proportion of auxiliary grooves and the number of grooves, the injection pressure drop ratio (or m...

Embodiment 2

[0035]The main spring 5 and the auxiliary spring 6 are one of the key parts of the implementation plan. They are made of 65Mn spring steel through heat treatment, wire cutting, surface treatment and pressure treatment to meet the high spring stiffness and large compression required by the design. When shutting down, the outer sleeve 2 and the inner sleeve 4 are in a sealed state by relying on the pre-compression pre-tightening force.

Embodiment 3

[0037] Such as figure 1 , Figure 4 As shown, the end notches 16 of the central cylinder 7 are T-shaped slots and rectangular slots with uniform intervals, different sizes, and staggered arrangements. The T-shaped slots 13 are the main slots, and the rectangular slots 14 are auxiliary slots. The impact of multiple radiated radial jets and the annular liquid film of the axial outer ring ejected from the annular nozzle 15 ensures that the two propellants collide to form a good radial mixing ratio distribution with a large gradient, which not only improves the efficiency The partial fuel that can realize penetration again fully cools down the body. Part of the jet flows along the surface of the splash plate 9 after hitting the click wall.

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PUM

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Abstract

The invention relates to a slotted coaxial pintle type injector thrust chamber. The slotted coaxial pintle type injector thrust chamber comprises a center barrel and a shell, an inner sleeve and an outer sleeve are arranged between the center barrel and the shell, an outer passage and an annular nozzle are formed by the outer sleeve and the shell, a center passage and a radial nozzle are formed by the inner sleeve and the center barrel, the upper end of the outer sleeve is connected with the center barrel through a main spring and a washer, and the upper end of the inner sleeve is connected with the center barrel through an auxiliary spring and the washer. The slotted coaxial pintle type injector thrust chamber is high in efficiency and low in cost.

Description

technical field [0001] The invention belongs to the field of liquid rocket engines, and relates to a liquid-film-free cooling thrust chamber, in particular to a slotted coaxial pintle type injector thrust chamber. It can be used for a liquid rocket orbit control engine with high thrust, high chamber pressure and fast response. Background technique [0002] In the context of the rapid development of my country's military spacecraft, it is imperative to improve the capabilities of the existing liquid orbital control rocket engines, which requires the orbital control engines to have fast response, high performance, and lightweight capabilities. Due to the high technical difficulty, conventional liquid rail-controlled engines with a response time of less than 30ms, a thrust of 10,000N, and a thrust-to-mass ratio greater than 500 have not yet been developed in China. [0003] Traditional liquid rocket engine injectors such as straight-line injectors, centrifugal injectors and pi...

Claims

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Application Information

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IPC IPC(8): F02K9/62F02K9/52
Inventor 凌前程高坤林革李军刘新华章荣军宋大亮种衡阳刘永兴丰雪平
Owner NO 11 INST OF NO 6 ACADEMY OF CHINA AEROSPACE SCI & TECH
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