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A scramjet double-throat combustion chamber and scramjet

A scramjet and combustion chamber technology, which is applied in combustion chambers, continuous combustion chambers, combustion methods, etc., can solve the problems of easy thermal blockage and unstable combustion of the engine, reduce shock loss and expand the flight Mach number. The effect of the lower limit

Active Publication Date: 2022-05-13
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At low Mach number, when high equivalence ratio fuel is injected, the combustion is too strong and heat blockage may easily occur, which makes the engine prone to combustion instability

Method used

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  • A scramjet double-throat combustion chamber and scramjet
  • A scramjet double-throat combustion chamber and scramjet
  • A scramjet double-throat combustion chamber and scramjet

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Embodiment Construction

[0029] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0030] 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 the components in a certain posture (as shown in the accompanying drawings). Relative positional relationship, movement conditions, etc., if the specific posture changes, the directional indication will also change accordingly.

[0031] In addition, in t...

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PUM

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Abstract

The invention discloses a scramjet double-throat combustion chamber and a scramjet engine, which comprise the upstream equivalent section of the combustion chamber, the first-stage concave cavity, the first-stage throat, and the second-stage concave Cavity, secondary throat, and equivalent section downstream of the combustion chamber; the primary throat is smoothly connected with the primary concave cavity and the secondary concave cavity, and the secondary throat is connected with the secondary The stage concave cavity and the equivalent section downstream of the combustion chamber are smoothly connected. The double-throat design is adopted to form a secondary combustion chamber to provide additional combustion organization space, effectively reduce the shock wave loss, and expand the lower limit of the combustion chamber flight Mach number.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a scramjet double-throat combustion chamber and a scramjet. Background technique [0002] Most of the existing scramjet combustor configurations use angled combustor throats, such as figure 1 shown. Usually, a subsonic-supersonic transition (sonic line) occurs after the throat corner, and there is a strong shock wave behind the sonic line, and there is a sudden pressure drop, resulting in a huge shock wave loss. [0003] In the existing scramjet combustion chamber configuration, the combustion zone at high Mach number is moved to the straight section downstream of the concave cavity, and the flame is in an unoptimized combustion state. At low Mach number, when high equivalence ratio fuel is injected, the combustion is too strong and heat blockage may easily occur, which makes the engine prone to combustion instability. Contents of the invention [0004] Aiming at the deficie...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/26
CPCF23R3/26
Inventor 孙明波赵国焱王前程蔡尊杨揖心
Owner NAT UNIV OF DEFENSE TECH