Test platform for rocket engine nozzle atomization test

Abstract

The invention discloses a test platform for a rocket engine nozzle atomization test, which comprises a transparent combustion chamber and a swirl atomization nozzle arranged on the transparent combustion chamber, and is characterized in that a first injection flow channel and a second injection flow channel with the same injection direction are formed in the swirl atomization nozzle; the first injection flow channel is located in the second injection flow channel, the inlet end of the first injection flow channel is closed, a water inlet tangent to the peripheral wall of the first injection flow channel is formed in the inlet end of the first injection flow channel, and the inlet end of the second injection flow channel is closed. A gas inlet tangent to the peripheral wall of the second injection flow channel is formed in the inlet end of the second injection flow channel, the water inlet is communicated with a pressure water source, and the gas inlet is communicated with a pressure nitrogen source. The test platform overcomes the defects that an existing engine supply system is large in scale, high in risk and the like, meanwhile, the test platform does not relate to the open firecombustion process, and researchers can conveniently conduct a nozzle atomization test manually.

Description

technical field [0001] The invention belongs to the field of aerospace power systems, in particular to a test platform for rocket engine nozzle atomization test. Background technique [0002] As the aerospace industry continues to expand into outer space, higher requirements are gradually put forward for aerospace power systems. As the main power system for space exploration, the liquid rocket engine has the advantages of high thrust, no pollution, economic reliability and so on. As an essential part of fuel supply, the liquid rocket engine supply system can supply fuel and oxidant under different working conditions to the engine combustion chamber according to the test requirements. Therefore, the supply system design is a key technology in the field of liquid rocket engine test. [0003] At present, the fuel supply systems designed in my country are all supporting the hot test of rocket engines, which have the characteristics of large scale, high cost, and high risk. At ...

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Problems solved by technology

[0003] At present, the fuel supply systems designed in my country are all supporting the hot test of rocket engines, which have the characteristics of large scale, high cost, and high risk. At the same time, the fuel required in the test process is expensive and stored unchanged, so it is not conducive to carrying out scientific experiments. Research

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