A kind of turbine engine and self-starting method thereof

Abstract

The invention relates to a turbine engine and its self-starting method. The turbine engine comprises: a body, a combustion chamber is formed in the body, and a guide vane is installed at one axial end of the combustion chamber; a gas generator is installed on the combustion chamber Indoor: fuel chamber, oxidant chamber and thrust chamber are formed inside the gas generator, the thrust chamber communicates with the turbine through the air injection port of the guide vane, and the fuel chamber and oxidant chamber communicate with the thrust chamber. The technical solution of the present invention is to install an independent gas generator in the combustion chamber, and the fuel containing catalyst in the fuel chamber and the oxidant in the oxidant chamber can be injected into the thrust chamber for mutual impact collision atomization, and then a combustion reaction occurs to generate high-temperature and high-pressure gas , the generated high-temperature and high-pressure gas passes through the gas injection port of the guide vane to drive the turbine to do work, so as to drive the rotor system to accelerate the rotation before ignition, which can effectively reduce the efficiency loss of energy conversion and reduce the mass and volume of the starting equipment.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a turbine engine and a self-starting method thereof. Background technique [0002] The structure and cycle process of the aviation gas turbine engine determine that it cannot be ignited and started autonomously like a car engine. This is because if fuel is injected directly into a stationary turbine engine for ignition, the compressor has not yet rotated, there will not be enough air to enter, the combustion conditions cannot be met, and the combustion chamber cannot build pressure, so the jet thrust cannot be generated, and the turbine cannot be driven to do work. Therefore, the starting characteristic of the gas turbine engine is that the necessary flow of air must be pressed in before the ignition and combustion can be completed, that is, the rotor system of the turbine engine must reach a certain speed in advance before the ignition can be started. For this starting fea...

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Problems solved by technology

Among them, the gunpowder starter has poor safety and reliability, and there are problems with the storage and transportation of the powder column, and the number of starts is extremely limited; the air turbine starter needs an external high-pressure air source, and the engine cannot be started alone. Compared with the electric starter, the entire starting mechanism is much more complicated. There are also restrictions on the lubrication of the air turbine starter; the gas turbine starter is actually a complete small turboshaft engine with a complex system and heavy weight; the motor itself and the battery in the electric starter are heavy and require a large power supply , especially for small turbine engines, the aircraft needs to carry heavy batteries, which is not worth the loss; while for large turbine engines, it is limited by the current technical level of the starter motor, and the starter motor will generate a lot of heat during operation. Therefore, for continuous starting There are large restrictions

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