A solid gas starter

Abstract

The invention discloses a solid gas starter applied to a turbojet engine. The solid gas starter comprises an igniting tool, a combustion chamber, a propellant, a filter screen, an end socket and a gas pipeline. The igniting tool adopts a double-bridge igniting circuit, is in threaded connection with the combustion chamber and adopts a copper gasket and O-shaped ring double-layer sealing structure; the combustion chamber and the end socket are in threaded connection with each other and are sealed by adopting a copper gasket; the propellant adopts a double-base propellant and an unsaturated polyester coating layer; the propellant form is of a combustion structure with two ends which are each provided with an inner taper hole; the combustion chamber is freely filled with the propellant; the filter screen is formed in a columnar shape by adopting a molybdenum wire by means of one-time mold pressing and is embedded inside the end socket; the end socket and the gas pipeline are in threaded connection with each other and are sealed by adopting an O-shaped ring; and an outlet end of the gas pipeline is provided with an external interface thread by means of machining. The solid gas starter disclosed by the invention can solve the problems that the gas of a start source for a conventional turbojet engine is high in temperature and unstable in gas flow and contains lots of gas residues. The solid gas starter disclosed by the invention can output low-temperature clean gas and is stable in output flow.

Description

technical field [0001] The invention relates to a solid gas starter for a turbojet engine, which is mainly applicable to the field of solid gas generators. technical background [0002] The starting methods for turbojet engines mainly include pressure gas cylinder starting, electric motor starting, and pyrotechnic starter starting. Among them, the use of pressure gas cylinders is limited due to factors such as high maintenance costs and large volume after long-term storage, complicated additional structures for motor start-up, and the need to configure power supplies. [0003] At present, turbojet engines generally use pyrotechnic starters as the starting source, but pyrotechnic starters have the following disadvantages: pyrotechnics have high energy characteristics, and the combustion temperature is generally above 3000K. Damage; there is a large amount of solid particle residue in the pyrotechnic agent combustion product, and the residue enters the key parts such as the t...

AI Technical Summary

Problems solved by technology

Among them, the use of pressure gas cylinders is limited due to factors such as high maintenance costs and large volume after long-term storage, complicated additional structures for motor start-up, and the need to configure power supplies.

[0003] At present, turbojet engines generally use pyrotechnic starters as the starting source, but pyrotechnic starters have the following disadvantages: pyrotechnics have high energy characteristics, and the combustion temperature is generally above 3000K. Damage; there is a large amount of solid particle residue in the pyrotechnic agent combustion product, and the residue enters the key parts such as the turbine bearing gap, causing the turbine shaft to wear, reducing the working efficiency of the turbojet engine, and causing damage to the turbojet engine in severe cases; When working for a long time, the gas flow is prone to instability, which affects the starting effect of the turbojet engine

Images