Ignition device for micro turbojet engine and gas turbine combustor

Abstract

The invention discloses an ignition device for a micro-miniature turbojet engine and gas turbine combustion chamber. The ignition device is composed of a kerosene nozzle, a kerosene chamber seat, a fastening nut, an oil inlet pipe and a heating core, the whole body is mounted on an engine shell through an air inlet cover, six air inlet holes are formed in the cylindrical surface of the air inlet cover, air can enter an ignition device combustion area through the air inlet holes to be mixed with the kerosene, the kerosene nozzle is provided with a pre-combustion hole and a main oil hole, the kerosene can be sprayed out through the pre-combustion hole and the main oil hole correspondingly so as to achieve layered combustion of the kerosene, the heating core adopts a silicon nitride ceramic electric heating plug, so that the power is large, the air enters the ignition area from the air inlet cover, the kerosene enters the kerosene chamber seat from the oil inlet pipe, and is sprayed out from the pre-combustion hole and the main oil hole in two paths through the kerosene nozzle. The oil discharge amount near the pre-combustion hole is relatively small, moreover, a pre-combustion area with a lower air flow speed is provided, the flame combusting stably existing in the pre-combustion area in the wide working condition range can help to ignite the kerosene sprayed out of the main oilhole, and then it is guaranteed that the igniter can work stably and reliably in the wider working condition range.

Description

technical field [0001] The invention belongs to the field of micro turbojet engines and gas turbines, and relates to a method for igniting a combustion chamber of a micro turbojet engine and a gas turbine and an ignition device for implementing the method, which can be applied to the ignition process of a micro turbojet engine and a gas combustion chamber of a gas turbine. Background technique [0002] Micro turbojet engines and gas turbines that use kerosene as aviation fuel are limited by size and structure. The structure of the combustion chamber and fuel nozzle is relatively simple. There is no special ignition and kerosene atomization device, so it is difficult to ensure that the engine starts The poor quality of kerosene atomization makes it difficult to start ignition and flame propagation. This is also the reason why many micro turbojet engines and gas turbines do not directly ignite kerosene but use propane gas to ignite. The propane gas injected into the combustion...

AI Technical Summary

Problems solved by technology

The main disadvantage of this ignition method: on the one hand, the aerodynamic resonance technology is still in the exploratory stage and is not very mature

On the other hand, pneumatic resonance requires compressed gas as the working medium for generating heat, so an additional compressed gas tank is required, which greatly increases the cost and volume weight of the entire ignition system

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