An aero-engine combustion chamber main combustion stage fuel nozzle and a fuel control method

Abstract

The application belongs to the technical field of aero-engines, and discloses an aero-engine combustion chamber main combustion stage fuel nozzle and a fuel control method. The aero-engine combustion chamber main combustion stage fuel nozzle comprises a same center axis, a duty class fuel nozzle, a swirler and a main combustion stage fuel nozzle which are sequentially sleeved from inside to outside, and the outlet of the main combustion stage fuel nozzle is sleeved with a sleeve. The fuel control method ensures that the fuel jet flow of the duty class fuel nozzle is unchanged, the swirler rotates around the duty class fuel nozzle, the fuel jet flow of the main combustion stage fuel nozzle is adjusted, and then the total fuel jet flow of the aero-engine combustion chamber main combustion stage fuel nozzle is changed. The fuel control method of the aero-engine combustion chamber main combustion stage fuel nozzle realizes efficient fuel injection under different working conditions, guarantees the combustion efficiency and stability of the combustion chamber, controls the combustion temperature distribution of the main combustion zone, and reduces the pollutant emission of the combustion chamber.

Images