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Fuel supply system and method for shock tunnel scramjet engine air intake test

A fuel supply system, shock tunnel technology, applied in gas turbine engine testing, jet engine testing, aerodynamic testing, etc., can solve problems such as weakness, achieve stable fuel injection pressure, ensure safety, and ensure safety Effect

Active Publication Date: 2018-08-14
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the current high Mach number (Ma ≥ 8) scramjet technology (specially matched experimental equipment and test technology) for space entry is very weak
There are no research results in this area

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  • Fuel supply system and method for shock tunnel scramjet engine air intake test

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Embodiment Construction

[0033] A fuel supply system for a shock tunnel super-combustion engine inlet test, the system includes a hydrogen filling branch 1, a nitrogen replacement branch 2, an emptying branch 3, a vacuuming branch 4, a fuel injection branch Flow branch 5 and fuel injection flow control part 6;

[0034] The hydrogen filling branch 1 includes a hydrogen gas source 101, a hydrogen pressure reducing valve 102, a one-way valve 103, a hydrogen tempering device 104, a hydrogen branch valve 105 and pipelines;

[0035] The nitrogen replacement branch 2 includes a nitrogen gas source 201, a nitrogen branch pneumatic valve 202, a nitrogen branch valve 203 and pipelines;

[0036] The evacuation branch 3 includes a hydrogen safety valve 301, an evacuation valve 302, a hydrogen temperer 303 and pipelines;

[0037] The vacuum branch 4 includes a vacuum branch valve 401, a vacuum pump 402 and pipelines;

[0038]The fuel injection branch 5 includes a buffer tank 501, a buffer tank pressure sensor 50...

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Abstract

The invention relates to a fuel supply system and method for a shock tunnel scramjet engine air intake test and belongs to the hypersonic velocity shock tunnel test technical field. According to the fuel supply system and method of the invention, with the reasonable matching of pipelines and the coordinated matching of a jet flow high-speed valve and the software and hardware of a control system adopted, a shock tunnel fuel supply and tunnel incoming flow time sequence control problem can be solved; a buffer tank and a pressure stabilizing chamber are built in a test section, and therefore, the linear loss of an air supply pipeline can be decreased, the injection pressure of fuel can be more stable; and the opening time of valves is set through the control system, and therefore, the amountof hydrogen of an injection test section can be strictly controlled, and the safety of the test can be ensured.

Description

technical field [0001] The invention relates to a fuel supply system and method for a shock tunnel super-combustion engine inlet test, and belongs to the technical field of hypersonic shock tunnel tests. Background technique [0002] The scramjet engine decelerates and supercharges through the inlet surface, sucks in the air in the flight environment, and mixes with the fuel in the combustion chamber to form supersonic combustion. High, low cost, reusable and other advantages are highly valued by foreign aerospace powers. However, it is an important means to carry out the development process of the super-combustion engine to carry out the super-combustion engine inlet test in the shock wave wind tunnel. [0003] Hydrogen is mainly used as the fuel in the inlet test of the super-combustion engine in the shock tunnel. . However, the running time of the high Mach number and high enthalpy shock tunnel is very short, especially the test time at high Mach number is almost a few...

Claims

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Application Information

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IPC IPC(8): G01M15/14G01M9/00
CPCG01M9/00G01M15/14
Inventor 宋可清卢洪波纪锋陈星林键李海燕孙日明丁杰
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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