Combustion chamber with combustion area adjusted on basis of inlet swirl rectifying support plates, and special support plates thereof

Abstract

The invention discloses a combustion chamber with a combustion area adjusted on the basis of inlet swirl rectifying support plates, and the special support plates thereof. The combustion chamber comprises an outer casing, an inner casing, a central cone and a fuel injection system as well as a shunt ring located between the inner casing and the outer casing; the shunt ring is arranged around the inner casing concentrically, and the outer casing is arranged at the periphery of the shunt ring concentrically; the swirl rectifying support plates are fixed between the shunt ring and the inner casing; and each special swirl rectifying support plate comprises a side part and a plurality of blades connected to the side part, and the blades are rotated around the side part. According to the combustion chamber, active control over a high temperature area of the combustion chamber can be achieved; and the high-efficiency and low-flame retardance combustion of the combustion chamber is achieved.

Description

technical field [0001] The invention relates to an engine, in particular to a combustion chamber in the engine. Background technique [0002] The combustion chamber is an important part of an aero-engine. In recent years, the afterburner or the turbine / ramjet combined combustion chamber of a tandem turbine-based combined cycle engine (abbreviated as TBCC) has developed rapidly, although its mass only accounts for 1% of the total mass of the engine. About 20%, but it can greatly increase the engine thrust. The turbojet engine uses an afterburner, and the thrust increase ratio can reach 40% to 50%; the turbofan engine uses an afterburner, and the thrust increase ratio can reach 60% to 70% or even higher. With the advent of the 4th generation and near 4th generation aero-engines, they require high thrust-to-weight ratio, thrust vectoring capability, stealth characteristics, low fuel consumption, high reliability, etc. The almost harsh design requirements of the afterburner gr...

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Problems solved by technology

With the successive advent of the 4th generation and close to the 4th generation aero-engines, they are required to have high thrust-to-weight ratio, thrust vectoring capability, stealth characteristics, low fuel consumption, high reliability, etc. The almost harsh design requirements of the afterburner greatly increase the gas temperature at the inlet of the afterburner, which can reach 1300K or even higher. At the same time, the droplets evaporate quickly after the fuel is sprayed. There is almost no penetrating power in the airflow. After the fuel is sprayed, it will move with the airflow soon. It is difficult to spread and mix in the cross section, which is not conducive to the uniform and reasonable distribution of the fuel formed in the entire cross section, and reduces the combustion efficiency.

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