Classified combustion chamber adopting multi-point injection combustion stabilization classes for improving combustion stability

Abstract

The invention relates to a classified combustion chamber adopting multi-point injection combustion stabilization classes for improving combustion stability. A structure of an oil gas mixing device at the head portion of the classified combustion chamber comprises center combustion stabilization class assemblies, periphery combustion stabilization class assemblies and main combustion class assemblies. The center combustion stabilization class assemblies are located in the centers of the main combustion class assemblies, and every two periphery combustion stabilization class assemblies are located between the corresponding two adjacent main combustion class assemblies. When ignition is conducted in the combustion chamber, an igniter firstly ignites the periphery combustion stabilization class assemblies close to an outer ring of a flame tube and then ignites the other periphery combustion stabilization class assemblies and the center combustion stabilization class assemblies. Due to the fact that energy of the igniter does not need to penetrate main combustion class air stream, the ignition performance of the classified combustion chamber is greatly improved; and when the combustion chamber works in a large-power state, the center combustion stabilization class assemblies, the periphery combustion stabilization class assemblies and the main combustion class assemblies supply oil at the same time, the center combustion stabilization class assemblies and the periphery combustion stabilization class assemblies have a stabilizing function on main combustion class flames at the same time, and the stability of large-power-state main combustion class combustion is improved.

Description

technical field [0001] The invention is applied to the field of aero-engine combustors, and in particular relates to civil low-pollution combustors and military high-temperature rise combustors using staged combustion technology. Background technique [0002] At present, there are two main application directions for staged combustors. One is a low-pollution combustor, which is mainly used in civil aero engines, with high combustion efficiency and low pollutant emissions (mainly nitrogen oxides and carbon monoxide) as its main technical features. , and its typical representatives are the TAPS combustor applied to the GEnx engine and the TAPS II combustor applied to the GE9x engine. The TAPS and TAPS II combustors adopt the concept of staged and partitioned combustion. Most of the fuel and air are mixed through the main combustion stage to achieve premixed and partially premixed combustion, thereby reducing the temperature of the main combustion zone and thermal nitrogen oxide...

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is: the air flow rate of the main combustion stage at the head of the graded combustion chamber is relatively large, and the ignition energy generated by the igniter is difficult to penetrate the airflow of the main combustion stage to ignite the pre-combustion stage, resulting in difficulty in igniting the graded combustion chamber; The high flow rate of the combustion stage makes it difficult for the pre-combustion stage flame to effectively stabilize the main combustion stage flame, and the combustion chamber is prone to main combustion stage flameout and thermoacoustic shock

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