An edge distribution plasma cracking activation refueling device and method

A technology of plasma and edge distribution, applied in the direction of fuel heating of jet propulsion devices, rocket engine devices, turbine/propulsion devices, etc., can solve problems such as difficult to realize, high detonation energy, etc., to reduce detonation energy and improve detonation Frequency, the effect of shortening the detonation time

Active Publication Date: 2021-11-16
AIR FORCE UNIV PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, kerosene-air detonation has always been the core technology and international problem of rotary detonation engines. The direct detonation energy of kerosene-air mixture is very large and difficult to realize.

Method used

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  • An edge distribution plasma cracking activation refueling device and method
  • An edge distribution plasma cracking activation refueling device and method
  • An edge distribution plasma cracking activation refueling device and method

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Experimental program
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Effect test

Embodiment 1

[0038] Such as figure 1 , 2 As shown, a kind of edge distribution plasma activated refueling device comprises a pre-combustion cracking chamber 1 with openings at both ends and a plasma control chamber 3 connected to one end of the pre-combustion cracking chamber 1, and a pre-combustion cracking chamber 1 is provided with The fuel injection nozzle 2 is provided with a discharge structure in the plasma control chamber 3, wherein the fuel injection nozzle 2 communicates with the oil supply device.

[0039] The shape of the plasma control chamber 3 is a hollow cylinder with openings at both ends. First connecting flanges 8 are arranged at both ends of the plasma control chamber 3. The first connecting flange 8 can facilitate the connection between the plasma control chamber 3 and the plasma control chamber 3. communicate with other components.

[0040] Such as figure 1 , 2 As shown, wherein, the pre-combustion cracking chamber 1 is cylindrical, and the two ends of the pre-com...

Embodiment 2

[0052] A cracking method, characterized in that: comprising the following steps:

[0053] Step 1: create a high temperature environment in the pre-combustion cracking chamber 1;

[0054] Step 2: After waiting for the temperature in the pre-combustion cracking chamber 1 to rise, fuel is injected into the pre-combustion cracking chamber 1, and the fuel is pyrolyzed;

[0055] Step 3: The pyrolyzed fuel is passed into the plasma control chamber, and the plasma formed by the discharge at the circumferential inner wall will activate the pyrolyzed fuel, thereby regulating the distribution of the pyrolyzed fuel components.

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Abstract

The present invention relates to an edge distribution plasma cracking activation refueling device and method, comprising a pre-combustion cracking chamber with openings at both ends and a plasma control chamber connected to one end of the pre-combustion cracking chamber, the pre-combustion cracking chamber is provided with The fuel injection nozzle is connected to the oil supply device, and the inner wall of the plasma control chamber is provided with a discharge structure in the circumferential direction. The small molecular gaseous fuels and active groups formed after pre-combustion cracking and plasma cooperative cracking have high reactivity, so when these cracked small molecule fuels and active groups are passed into the rotary detonation engine, it can be significantly The detonation energy is reduced, the detonation time is shortened, and the detonation frequency is increased to achieve the purpose of liquid fuel-air detonation.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to an edge-distributed plasma cracking activation refueling device and method. Background technique [0002] With the rapid development of the aerospace industry, the demand for high-performance propulsion and power systems is increasing, and the performance indicators of the propulsion and power systems are also related to the design parameters of the aircraft. In order to improve the performance of the propulsion system, the use of efficient combustion organization and energy utilization has become an important means of research. Conventional power systems, such as turbine engines and rocket engines, all use isobaric combustion, and the cycle efficiency is low. In addition to deflagration, the combustion method also has an approximately constant volume detonation combustion method. Studies have shown that the thermal cycle efficiency of detonation combustion is high, the en...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/68F02K9/44F02C7/22F02C7/224
Inventor 吴云宋飞龙金迪贾敏陈鑫
Owner AIR FORCE UNIV PLA
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