Liquid film cooling injection rocket engine thrust chamber for rocket ramjet combined engine

A technology for ejecting rockets and engines, which is applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems that the engine cannot work for a long time, the structure of the jacket cooling thrust chamber is complicated, etc., and achieves good atomization and mixing effect. , Simple and efficient structure

Active Publication Date: 2018-11-27
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to provide a thrust chamber of a rocket ram jet combined engine with liquid film cooling ejection rocket, so as to solve the problems in the prior art that the traditional passive cooling engine cannot work for a long time, and the body structure of the jacket cooling thrust chamber is complicated

Method used

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  • Liquid film cooling injection rocket engine thrust chamber for rocket ramjet combined engine
  • Liquid film cooling injection rocket engine thrust chamber for rocket ramjet combined engine
  • Liquid film cooling injection rocket engine thrust chamber for rocket ramjet combined engine

Examples

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Embodiment

[0040] In the i experiment, the engine as a whole is figure 1 Assembled, including spark plug igniter 1, oxygen through joint 2, pressure measuring seat 3, head 4, gas-liquid coaxial nozzle 7, kerosene through joint 8, liquid film flange 9, thrust chamber shell 11, measuring The temperature seat 13 and the nozzle gland 15 are made of stainless steel 1Cr18Ni9Ti. Considering the harsh thermal environment of the throat, the nozzle is made of high-temperature-resistant graphite. The spark plug type igniter 1 and the spark plug seat of the head adopt the threaded connection of the thrust chamber 1 of the ejection rocket engine thrust chamber 1 of the M16 rocket stamping combined engine; 4 flanges, liquid film flanges 9, and the upper and lower flanges of the thrust chamber shell 11 have 8 equally spaced openings with a diameter of 13 mm, the wall thickness of the head flange is 20 mm, and the wall thickness of the remaining flanges is 15 mm; The liquid coaxial nozzle 7 is 29mm lon...

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Abstract

The invention discloses a liquid film cooling injection rocket engine thrust chamber of a rocket ramjet combined engine, which comprises a head part, wherein the head part comprises a head shell, andone end of the head shell is provided with an ignition device; the head shell is also provided with an oxygen through joint and a kerosene through joint, and the oxygen through joint and the kerosenethrough joint are both communicated with a gas-liquid coaxial nozzle; the gas-liquid coaxial nozzle comprises an oxygen direct flowing spraying hole arranged in the head shell and coaxially arranged with the gas-liquid coaxial nozzle, and also comprises a segmented direct flowing slit nozzle for kerosene circulation, wherein the segmented direct flowing slit nozzle which is arranged outside the oxygen direct flowing spraying hole, is a three-section slit; the other end of the head shell is coaxially communicated with a liquid film flange plate, a thrust chamber shell and a graphite spraying pipe through a graphite gasket. The problems that the engine cannot work for a long time by using a passive cooling mode in the prior art, and the structure of a jacket cooling thrust chamber body is complex are solved.

Description

【Technical field】 [0001] The invention belongs to the technical field of liquid rocket engines, and in particular relates to a thrust chamber of a rocket ram jet combined engine with liquid film cooling ejection rocket engine. 【Background technique】 [0002] The thrust chamber is the main place where the propellant burns and releases heat in the liquid rocket engine. In the thrust chamber, the propellant is sprayed through the nozzle to complete the atomization, evaporation, mixing and combustion process, converting the chemical energy into the heat energy of the high-temperature gas, and converting the heat energy of the gas through the Laval nozzle with contraction-expansion profile For kinetic energy, thrust is generated. [0003] Usually, in order to improve the combustion efficiency and specific impulse performance of the engine, on the one hand, it is necessary to design a high-performance injector to improve the atomization and mixing quality of the propellant; on th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/52F02K9/64
CPCF02K9/52F02K9/64
Inventor 魏祥庚杨甲甲王伟良秦飞张铎石磊何国强
Owner NORTHWESTERN POLYTECHNICAL UNIV
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