Ignition electric nozzle for improving ignition stability of aero-engine

Abstract

The invention relates to an ignition electric nozzle for improving the ignition stability of an aero-engine. The ignition electric nozzle comprises an ignition tube, an ignition electrode, an air inlet and an adapter, wherein the ignition tube is of a cylindrical structure, the tail end of the ignition tube is hermetically and fixedly connected to the adapter, and the head end of the ignition tubeis of a cone-shaped nozzle structure; the ignition electrode is located at the axial center of the ignition tube; the air inlet is of a rectangular tube structure and is connected to the ignition tube, an included angle exists between the air inlet and the ignition tube, at least two baffle plates are distributed in the air inlet, and the baffle plates are arranged in a staggered manner; the adapter is hermetically and fixedly connected to a cartridge, an ignition electric nozzle mounting hole is formed in the cartridge, the pore diameter of the ignition electric nozzle mounting hole is greater than the diameter of the ignition tube, and the pore diameter of the ignition electric nozzle mounting hole is smaller than the diameter of the adapter; an adapter plate is arranged on the orificeof the air inlet, the adapter plate is parallel to the axial central line of a flame tube, and the air inlet is fixedly connected to the flame tube through the adapter plate; and the cone-shaped nozzle of the ignition tube and the orifice of the air inlet face the inner side of the flame tube, and the axial central line of the ignition tube is vertical to the axial central line of the flame tube.

Description

technical field [0001] The invention belongs to the technical field of aero-engines, in particular to an ignition nozzle for improving the ignition stability of an aero-engine. Background technique [0002] With the rapid development of aerospace equipment such as hypersonic vehicles and aerospace aircraft, it provides an effective guarantee for future space travel and national defense. Since the main range of activities of hypersonic vehicles and aerospace aircraft is in the atmosphere and transatmosphere, and have a high flight Mach number, the air will enter the combustion chamber of the engine at a high flow rate, and the mixing time of air and fuel is extremely short. This will have a great impact on the quality of the mixture, and the high flow rate of the mixture will easily blow out the ignition core, thereby reducing the ignition stability of the engine combustion chamber, and even the risk of air parking. Contents of the invention [0003] Aiming at the problems...

AI Technical Summary

Problems solved by technology

Since the main range of activities of hypersonic vehicles and aerospace aircraft is in the atmosphere and transatmosphere, and have a high flight Mach number, the air will enter the combustion chamber of the engine at a high flow rate, and the mixing time of air and fuel is extremely short. This will have a great impact on the quality of the mixture, and the high flow rate of the mixture will easily blow out the ignition core, thereby reducing the ignition stability of the engine combustion chamber, and even the risk of air parking

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