Aero-engine ignition control system with monitoring device

An aero-engine and ignition control technology, which is applied in the direction of machines/engines, rocket engine devices, jet propulsion devices, etc., can solve problems such as increasing the probability of misfire, and achieve the effects of simple structure, improved reliability, and high device stability

Active Publication Date: 2015-12-30
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

In order to improve the reliable control of a single ignition nozzle by a single channel, and considering that too many ignition relays will inc

Method used

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  • Aero-engine ignition control system with monitoring device

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[0013] In order to better understand the aero engine ignition control system with a monitoring device according to the scheme of the present invention, a preferred embodiment of the aero engine ignition control system with a monitoring device of the present invention will be further explained with reference to the accompanying drawings.

[0014] Such as figure 1 As shown, the aero engine ignition control system with monitoring device provided by the present invention includes a first channel A and a second channel B set in the engine electronic controller. The first channel A and the second channel B are controlled and The first ignition relay a and the second ignition relay b connected to it realize the ignition power supply control to the ignition switch. The aircraft engine interface control unit is also provided with a first backup ignition relay c and a second backup ignition relay d, where: The first channel A and the second channel B control the pull-in of the first backup...

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Abstract

The invention provides an aero-engine ignition control system with a monitoring device, and relates to the design technology of aero-engines. The aero-engine ignition control system with the monitoring device is used for controlling ignitor plugs of an engine, on the basis of control through a dual-redundancy ignition relay of an engine electronic controller, a path of ignition relay is added on an interface unit of the engine of aircraft equipment, the relays of each ignitor plug are increased to three, and the ignition function of the engine can be achieved through closing of each relay. The contact state and the front end input ignition voltage quality of the ignition relay installed in an EEC are monitored in real time through the EEC, the contact state and the front end input ignition voltage quality of the ignition relay in an EIU are monitored in real time through the EIU, monitored information is fed back to the EEC through a bus, and the EEC monitors the three ignition relays and outputs a merged current finally. By means of the aero-engine ignition control system with the monitoring device, the reliability of the engine ignition system is improved, testability and the fault diagnosis capability of the engine are improved, and the safety of an aircraft is enhanced.

Description

technical field [0001] The invention relates to an aeroengine design technology, in particular to an aeroengine ignition control system with a monitoring device. Background technique [0002] The aircraft requires that the engine can be ignited under any flight conditions. For aeroengines using digital electronic controllers, dual-redundant ignition relays are usually built in each channel of the engine electronic controller, and each channel can control the ignition of two ignition nozzles. Any one of them can achieve dual redundancy ignition design, but due to the limited space of the engine electronic controller, the control of each ignition nozzle by each channel of the engine electronic controller is still single redundancy. In order to improve the reliable control of a single ignition nozzle by a single channel, and considering that too many ignition relays will increase the probability of misfiring, the technical problem that needs to be solved urgently is how to desi...

Claims

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Application Information

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IPC IPC(8): F02C7/266F02K9/95
Inventor 张伟杨保江秦浩吴宇
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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