A kind of rich combustion gas generation control system and control method
A gas generation and control system technology, applied in the field of control systems, can solve the problems of lack of research on the reaction mixed layer, lack of optical experimental research related to the reaction mixed layer, etc., and achieve the effect of solving the measurement problem of the reaction mixed layer
Active Publication Date: 2022-07-15
NAT UNIV OF DEFENSE TECH
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At present, the visualization experiments on the mixing layer of RBCC engines at home and abroad basically use the same temperature mixing layer, but there is a lack of research on the reaction mixing layer, and there is a lack of related optical experimental research on the reaction mixing layer.
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[0031] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.
[0032] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relationship between various components under a certain posture (as shown in the accompanying drawings). The relative positional relationship, the movement situation, etc., if the specific posture changes, the directional indication also changes accordingly.
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The invention discloses a rich combustion gas generation control system and a control method. The control system comprises a fuel storage tank, a fuel conduit, a gas generation section and a fuel injection section; the gas generation section is provided with a gas generation component to generate high-temperature gas; The fuel injection section is provided with an injection structure to inject fuel into the fuel injection section to form rich combustion gas; the fuel conduit is provided with a control component to control the fuel injection amount. First, the high-temperature gas is generated by the gas generating component, and then the fuel is injected into the high-temperature gas through the injection structure to generate high-temperature rich combustion gas, and then the visualization experiment of the reaction mixture layer can be more fully carried out. , which will lead to insufficient combustion reaction of gas and produce micron and even nano-scale carbon particles. The tiny carbon particles in the flow field can be used as tracer particles for visual and precise measurement methods to solve the reaction caused by the poor distribution of tracer particles in high-temperature gas. Mixed layer measurement challenges.
Description
technical field [0001] The invention relates to the technical field of control systems, in particular to a control system and a control method for generating rich combustion gas. Background technique [0002] At present, the test process of RBCC (Rocket-Based Combined Cycle, rocket-based combined cycle propulsion system) engine often involves the use of high-temperature and rich-burning gas, that is, the rocket fuel in the RBCC engine is more than the appropriate equivalence ratio, and its tissue combustion leads to the exit of the rocket. High-temperature rich combustion gas is generated, so it is necessary to study the reaction mixing layer caused by the rich combustion of rocket gas. At present, the visualization experiments on the mixed layer of RBCC engines at home and abroad basically use the same temperature mixed layer, but there is a lack of research on the reaction mixed layer, and there is a lack of related optical experimental research on the reaction mixed layer...
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IPC IPC(8): F02K9/56F02K9/44F02K9/52F02K9/96
CPCG01M15/02G01M15/14
Inventor 姚轶智孙明波蔡尊李佩波杨揖心顾瑞董泽宇
Owner NAT UNIV OF DEFENSE TECH