Rotary detonation combustion chamber suitable for gas-liquid two-phase dual fuel
A combustor and dual-fuel technology, applied in deflagration-type combustors, combustors, continuous combustors, etc., can solve the problems of poor initiation characteristics and poor stable propagation characteristics of liquid fuel rotating detonation waves, and achieve optimal injection methods, Easy to work stably and realize the effect of stable work
Pending Publication Date: 2022-02-01
XIAN THERMAL POWER RES INST CO LTD
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Problems solved by technology
[0004] The purpose of the present invention is to propose a rotary detonation combustor suitable for gas-liquid two-phase dual-fuel, which is intended to solve the problems of poor initiation characteristics and poor stable propagation characteristics of rotary detonation waves based on liquid fuels, and can use a variety of gaseous and liquid fuels at the same time , the present invention can be applied to fields such as aero-engines and gas turbines
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[0028] In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connected, or integrally connected; it may be mechanically connected or electrically connected; it may be directly connected or indirectly connected through an intermediary, and it may be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.
[0029] refer to figure 1 with figure 2 As shown, the present invention provides a rotating detonation combustor suitable for gas-liquid two-phase dual fuel, which is composed of a gaseous fuel supply chamber 1 , a liquid fuel supply ring chamber 2 , a combustion chamber ring chamber 6 , and film cooling holes 12 . The gaseous fue...
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The invention discloses a rotary detonation combustion chamber suitable for gas-liquid two-phase dual fuel. The rotary detonation combustion chamber is mainly composed of a liquid fuel supply cavity, a gaseous fuel supply cavity, a rotary detonation combustion annular cavity and gas film cooling holes. In order to solve the problems of poor detonation characteristics and poor stable propagation characteristics of liquid fuel rotating detonation waves, in the detonation stage, gas fuel with good detonation performance is jetted in rotating detonation combustion, stable transmission based on the gas fuel rotating detonation waves is achieved firstly, and then stable propagation based on the liquid fuel rotating detonation waves is achieved. When the structural complexity of the combustion chamber is not obviously increased, the gas fuel injection structure is additionally arranged, the success rate of detonation of the liquid fuel rotating detonation waves is increased, the stable transmission characteristic of the rotating detonation waves is improved, and the invention is very important for engineering application of the rotating detonation combustion chamber.
Description
technical field [0001] The invention belongs to the technical field of rotary detonation combustion chambers, and in particular relates to a rotary detonation combustion chamber suitable for gas-liquid two-phase dual-fuel. Background technique [0002] In nature, according to the intensity of the combustion reaction, it can be divided into slow combustion and detonation combustion. Most of the existing power devices such as aero-engines and rocket engines adopt the circulation mode based on isobaric combustion, and its technical level tends to be mature, so it is very difficult to further improve the thermal cycle efficiency. Compared with isobaric combustion, detonation combustion has a normal shock wave before its chemical reaction zone, and the unreacted gas is compressed by the shock wave, its reaction pressure is higher, the reaction rate is faster, and the corresponding thermal cycle efficiency is higher . Therefore, applying detonation fuel to the existing aerospace...
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Login to View More IPC IPC(8): F23R3/52F23R3/28F23R7/00F02K7/02
CPCF23R3/52F23R3/28F23R7/00F02K7/02
Inventor 肖俊峰王致程王玮王峰李晓丰高松胡孟起
Owner XIAN THERMAL POWER RES INST CO LTD