Combustion-supporting method by activating oxygen molecules by using laser

An oxygen molecule and laser technology, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve the problems of low combustion efficiency and unstable fuel combustion, achieve stable combustion performance, reduce ignition temperature, and accelerate reaction. effect of speed

Inactive Publication Date: 2011-08-10
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The invention solves the problem of unstable fuel combustion and low combustion efficiency in the existing engine technology, and provides a combustion-supporting method for laser activation of oxygen molecules, which is completed by the following steps:

Method used

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  • Combustion-supporting method by activating oxygen molecules by using laser
  • Combustion-supporting method by activating oxygen molecules by using laser
  • Combustion-supporting method by activating oxygen molecules by using laser

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Effect test

specific Embodiment approach 1

[0009] Step 1: Pass the mixed gas into the quartz circular tube 3, and ignite the mixed gas at the outlet of the quartz circular tube 3 to generate a Bunsen burner flame; the mixed gas is a mixture of oxygen and other combustible gases;

[0010] Step 2: Use the tunable dye laser 17 to emit a laser beam to the gas unburned area under the Bunsen burner flame mentioned in Step 1 to realize laser combustion.

[0011] This embodiment adopts the principle of laser activation of oxygen molecules to support combustion, combined with figure 2 and image 3 In this embodiment, the use of laser to activate oxygen molecules to support combustion is to use laser to excite the ground state oxygen molecules to an excited state to increase the activity of the reactants, thereby increasing the rate of the chain reaction and branched chain reaction that trigger the combustion of the mixed gas, and accelerate the combustion. . Table 1 shows the transitions corresponding to the excited state ox...

specific Embodiment approach 2

[0021] Embodiment 3: The difference between this embodiment and Embodiment 1 or Embodiment 2 is that the single pulse energy output by the tunable dye laser 17 ranges from 1 to 100 mJ.

specific Embodiment approach 3

[0022] Embodiment 4: The difference between this embodiment and Embodiment 1 or 2 is that the single pulse energy output by the tunable dye laser 17 ranges from 7 to 10 mJ.

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Abstract

The invention provides a combustion-supporting method by activating oxygen molecules by using laser, which relates to a combustion-supporting method, and solves the problem that fuel has unstable combustion and low efficiency during the burning in the prior engine art. The method has the following implementation steps of: 1, introducing mixed gas into a quartz round tube, and igniting the mixed gas at an outlet of the quartz round tube to generate Bunsen flame, wherein the mixed gas is mixture of oxygen and other combustible gases; and 2, transmitting a laser beam to an unburnt gas area underthe Bunsen flame in the step 1 by adopting a tunable dye laser to realize laser combustion supporting. The method can be widely applied to the design of aerospace engine technology.

Description

technical field [0001] The invention relates to a combustion-supporting method. Background technique [0002] With the advancement of aerospace technology, the need for the development of high-thrust rockets and hypersonic aero-engines puts forward higher requirements on the reaction rate of fuel combustion. In rocket engine design, the increase in rocket load due to the need to carry oxidant itself is also one of the bottlenecks in the development of rocket technology. Therefore, how to effectively increase the combustion reaction rate and reduce the fuel ignition temperature has become a current research hotspot. The combustion chamber technology of the scramjet engine is the main difficulty in its design. When the scramjet engine is working, the incoming flow flows at supersonic speed when burning in the combustion chamber, and the stagnation time is only a few milliseconds. It is very difficult to realize fuel injection, atomization, mixing, ignition and stable combust...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/60
Inventor 于欣孙锐彭江波杨鹏陈德应刘辉于俊华邵强伊亚超杨晓川
Owner HARBIN INST OF TECH
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