Fractional combustion chamber

Abstract

The invention provides a staged combustion chamber. The staged combustion chamber comprises an annular flame barrel and a main combustion stage assembly, wherein the annular flame barrel comprises a flame barrel inner ring and a flame barrel outer ring which are coaxial with each other; the front section of the annular flame barrel is in the form of a cone of which the inner diameter is increased gradually; and the main combustion stage assembly is positioned at the front section of the annular flame barrel, is used for providing fuel and air needed by combustion of a main combustion stage, and comprises an annular bluff body, an inner / outer ring oil cavity a plurality of duty stage assemblies; the inner ring surface of the annular bluff body constructs an inner ring air flow channel together with the inner surface of the flame barrel inner ring and the outer ring surface of the annular bluff body constructs an outer ring air flow channel together with the inner surface of the flame barrel outer ring; the inner / outer ring oil cavity is attached to the inner / outer side of the annular bluff body and by the inner / outer ring oil cavity, accommodated fuel can be ejected onto the inner ring air flow channel through a plurality of inner ring ejection holes positioned in the inner / outer ring surface of the annular bluff body; and the plurality of duty stage assemblies which are positioned in a space encircled by the annular bluff body. In the staged combustion chamber provided by the invention, main combustion stage air enters the combustion chamber in a full ring air inlet way, so that the pressure loss of the combustion chamber is reduced, and the fuel consumption of an engine is lowered.

Description

technical field [0001] The invention relates to the field of low-pollution combustors of aero-engines, in particular to a staged combustor for direct injection of main combustion stage air full-circle intake fuel. Background technique [0002] In order to meet the requirements that the civil large duct is more economical, more environmentally friendly and safer than the turbofan engine, the combustion chamber of the aero-engine is required to have a small pressure loss, uniform outlet temperature distribution, and pollutants, especially NO x Low emissions. Combustion chamber NO x The level of production is closely related to the flame temperature in the combustion zone, and the temperature in the combustion zone exceeding 1800K will cause NO x Due to the diffusion combustion method used in the head of the conventional combustion chamber, the equivalent ratio of the combustion zone is close to 1, and the temperature of the combustion zone is close to the temperature of the ...

AI Technical Summary

Problems solved by technology

The TAPS combustion chamber adopts the strategy of split head air intake and oil supply, and the torch-shaped flame form generated by its combustion is easy to cause local high temperature at the outlet, which is not conducive to the uniformity of outlet temperature distribution;

[0008] (3) The head of the TAPS combustion chamber adopts a three-stage swirler structure, and there are complicated oil supply pipelines, cooling air passages, and air passages for blowing off carbon deposits, resulting in a very complicated structure of the combustion chamber, which affects the reliability of the combustion chamber. Detrimental effects on sex and weight loss

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