Multipoint unit direct jetting staged combustion chamber

Abstract

The invention relates to a multipoint unit direct jetting staged combustion chamber. A head part of the combustion chamber is provided with an on-duty stage and a main combustion stage; the on-duty stage and the main combustion stage both adopt a direct mixed combustion manner, spontaneous combustion and fire return phenomena are effectively avoided, and the risk of vibration combustion is reduced; in the low-speed running state, only the on-duty stage works, the on-duty stage adopts strong cyclone design, the local equivalence ratio is relatively rich, the stable work of the combustion chamber is guaranteed, along with increase of the working state of the combustion chamber, the main combustion stage is gradually opened, the main combustion stage adopts weak cyclone design, and the fuel gas staying time is effectively shortened; and in the high state, the main combustion stage and the on-duty stage work at the same time, the designed combustion area average equivalence ratio is 0.4-1.2, the combustion area average temperature is effectively reduced, and the contaminant generating quantity is reduced.

Description

technical field [0001] The invention belongs to the field of gas turbine combustion chambers, and relates to a multi-point unit direct injection staged combustion chamber. Background technique [0002] With the continuous progress of society, people's awareness of environmental protection is constantly improving. At present, the fundamental challenge facing civil aviation gas turbines and military aviation gas turbines is how to effectively ensure combustion stability and reduce pollutants while continuously improving the cycle efficiency and performance of aviation gas turbines. emission. International Civil Aviation Organization (ICAO) on nitrogen oxides (NOx) in civil aviation gas turbines in aircraft takeoff and landing cycles (LTO) x ), carbon monoxide and unburned hydrocarbon emissions set reference values. From CAEP / 1, CAEP / 2, CAEP / 4, CAEP / 6 to CAEP / 8, its requirements have become increasingly stringent. In 2017, the International Civil Aviation Organization recentl...

AI Technical Summary

Problems solved by technology

At present, domestic gas turbine combustors widely adopt a staged combustion strategy, and the main combustion stage generally adopts a premixed pre-evaporation combustion method, which can effectively solve the problem of smoke emission under large working conditions and the problem of lean flameout under small working conditions, but With the substantial improvement of the working state of the engine in the future, the inlet temperature and inlet pressure of the combustion chamber will increase significantly, shortening the ignition time of fuel spontaneous combustion, and the use of premixed pre-evaporation will bring backfire and spontaneous combustion risks, and may cause serious incombustibility. Stability issues, so in view of the working state of future aero-engines, there is an urgent need for a combustion chamber that can not only ensure the stable operation of the combustion chamber, but also reduce pollution emissions

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