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Engine thrust chamber, rocket engine, liquid rocket

A thrust chamber and engine technology, used in rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as melting and damage to the cavity of the thrust chamber.

Active Publication Date: 2022-03-15
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The above-mentioned high-temperature and high-pressure environment will cause the cavity of the thrust chamber to be damaged or even have the risk of melting

Method used

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  • Engine thrust chamber, rocket engine, liquid rocket
  • Engine thrust chamber, rocket engine, liquid rocket
  • Engine thrust chamber, rocket engine, liquid rocket

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0038] Such as Figure 1 to Figure 4 As shown, an engine thrust chamber provided in this embodiment includes: a housing wall 1, in which a plurality of flow channels 11 are arranged at intervals, and the flow channels 11 are suitable for extending in the flow direction of gas; the housing wall 1 also includes: The first inlet 12 and the first outlet 13, the first inlet 12 and the first outlet 13 are respectively arranged at the two ends of the flow channel 11; the partition 14 is arranged between two adjacent flow channels 11; the engine thrust chamber also includes : The liquid cooling module 2 is arranged on the shell wall 1, and at least one first chamber 21 is arranged on it, and the first chamber 21 communicates with at least one flow channel 11; wherein, the partition 14 is provided with a liquid cooling channel 141 , one end of the liquid cooling channel 141 communicates with the first chamber 21 , and the other end communicates with the combustion chamber 3 .

[0039]...

Embodiment 2

[0066] This embodiment provides a rocket engine, including the engine thrust chamber in Embodiment 1 above, and has all its technical advantages, which will not be repeated here.

Embodiment 3

[0068] This embodiment provides a liquid rocket, including the rocket motor in Embodiment 2 above, and has all its technical advantages, which will not be repeated here.

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Abstract

The invention relates to the technical field of rocket engines, in particular to an engine thrust chamber, a rocket engine and a liquid rocket. A thrust chamber of an engine includes: a housing wall, in which several flow channels are arranged at intervals, and the flow channels are suitable for extending in the flow direction of gas; the housing wall also includes: a first inlet and a first outlet, a first inlet and a first The outlets are respectively arranged at both ends of the flow passages; the partition is arranged between two adjacent flow passages; the engine thrust chamber also includes: a liquid cooling module arranged on the shell wall, on which at least one first chamber is arranged , the first chamber communicates with at least one flow channel; wherein, a liquid cooling channel is provided on the separator, one end of the liquid cooling channel communicates with the first chamber, and the other end communicates with the combustion chamber. In the present invention, a cooling liquid film is formed on the inner wall of the combustion chamber to isolate the high temperature in the combustion chamber from the cavity wall, so as to avoid the problem that the cavity wall of the engine thrust chamber is affected by high temperature and the service life is shortened or even melted.

Description

technical field [0001] The invention relates to the technical field of rocket engines, in particular to an engine thrust chamber, a rocket engine and a liquid rocket. Background technique [0002] The thrust chamber is the core component of the liquid rocket engine. The liquid rocket propellant fuel enters the combustion chamber through the injector, atomizes, mixes, and burns to generate high-temperature and high-pressure gas, which converts chemical energy into heat energy, which is then sprayed out by the nozzle at high speed. Kinetic energy, which creates the thrust that propels the rocket upward. Because the thrust chamber carries high-temperature, high-pressure, and high-velocity gas, the temperature of the gas in the thrust chamber is as high as 3500°C, and the gas pressure is generally around 10MPa, with a maximum of 30MPa. The above-mentioned high-temperature and high-pressure environment will cause the cavity of the thrust chamber to be damaged or even have the ri...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/64F02K9/62
CPCF02K9/64F02K9/62
Inventor 高翔宇张玺刘岳曦鲍启林何佳丽
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD