High energy solid state discharge igniting module

An ignition module, solid-state technology, applied in jet propulsion devices, gas turbine devices, machines/engines, etc., can solve the problems of inconvenient radioactive disposal, large size of ignition devices, and low reliability, and achieve high electrical conversion efficiency and high electrical efficiency. , Electromagnetic compatibility effect is good

Active Publication Date: 2013-05-15
四川泛华航空仪表电器有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The ignition devices used in domestic aero-engines generally have disadvantages such as large size, heav

Method used

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  • High energy solid state discharge igniting module
  • High energy solid state discharge igniting module
  • High energy solid state discharge igniting module

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Embodiment Construction

[0015] exist figure 1 In one embodiment described, the high-energy solid-state discharge ignition module is mainly composed of a power input interface 8 and a high-voltage output interface 1 arranged on the same side of the housing assembly 6, and is fixedly connected in the casing of the housing assembly 6, including an inverter assembly, a rectifier The functional circuit board 4 of the component and the discharge control component, the filter 7 electrically connected to the power input interface 8, the step-up transformer 5, the capacitor component 3 and the high-frequency transformer 2 are composed. The inverter circuit composed of the pulse width modulation PWM control chip and its auxiliary circuit is electrically connected between the filter and the step-up transformer. The high-voltage boost circuit composed of the thyristor and its trigger circuit and the high-frequency transformer 2 is electrically connected between the energy storage capacitor assembly 3 and the hig...

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Abstract

The invention relates to a high energy solid state discharge igniting module, a inverter component is composed of a PWM control chip U1 which enables electric connection between a filter circuit and a boosting transformer and its auxiliary circuit, the boosting transformer is electrically connected to an energy-storage capacitor component through a high voltage silicon stack D1, a discharge control component is electrically connected to a part between the energy-storage capacitor component and a high voltage boost circuit, the high voltage boost circuit is composed of a high-frequency transformer electrically connected to a mutual inductance coil L1 and an oscillation capacitance C8, a dc source DC is electrically connected to the filter through a power supply input interface for completing the filtering, and converted to high voltage AC pulse through an inversion circuit and the boosting transformer, and is charged through the silicon stack rectification backward energy-storage capacitor component, and high voltage is output to a high voltage output interface can be completed by the discharge control circuit and the high voltage boost circuit. The high energy solid state discharge igniting module has the advantages of high loss of gas discharge tube energy, low transition efficiency and short life, and the output energy and transition efficiency can be increased by about 30%. The high energy solid state discharge igniting module has the characteristics of high efficiency, long life and no radioactivity.

Description

technical field [0001] The invention relates to an ignition device for igniting the fuel mixture gas of an aeroengine during starting and running. Background technique [0002] Ignition device is an important part of modern aero-engine, and it is a key component of engine ground start and air parking restart. success rate. The ignition device for aero-engines works in a short-time repetitive manner, and the power input is divided into two types: DC 28V and AC 115V / 400Hz. Among various ignition devices, the ignition type commonly used in aero-engines is the DC inverter capacitive discharge ignition device, which accounts for more than 90%. [0003] In the prior art, the DC inverter capacitive discharge ignition device of an aero-engine generally consists of a filtering component, an inverter circuit, a boosting component, a rectifying component, an energy storage component and a discharge control component. Its working principle is: after the DC power supply is filtered by...

Claims

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Application Information

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IPC IPC(8): F02C7/266
Inventor 彭进田钟俊穆成勇
Owner 四川泛华航空仪表电器有限公司
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