Invention Grant
- Patent Title: Ignition system of an aircraft turbine engine
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Application No.: US16161941Application Date: 2018-10-16
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Publication No.: US10697420B2Publication Date: 2020-06-30
- Inventor: Richard Ambroise , Xavier Collas
- Applicant: Airbus Operations SAS
- Applicant Address: FR Toulouse
- Assignee: AIRBUS OPERATIONS SAS
- Current Assignee: AIRBUS OPERATIONS SAS
- Current Assignee Address: FR Toulouse
- Agency: Greer, Burns & Crain, Ltd.
- Priority: com.zzzhc.datahub.patent.etl.us.BibliographicData$PriorityClaim@566b7a6c
- Main IPC: F02P17/12
- IPC: F02P17/12 ; F02C7/266 ; F02P15/00 ; F23Q23/10

Abstract:
A turbine engine ignition system comprising a spark plug having excitation and return terminals, and a spark plug exciter connected to the excitation terminal. The return terminal is connected to an equipotential reference-forming structure, the exciter device is connected to a command line for a signal to supply an excitation signal to the spark plug. The ignition system comprises a control device comprising current and voltage sensors, a first voltage comparator, a second current comparator, and a microcontroller receiving output from the two comparators. The first comparator compares the voltage sensor signal to a first reference value and the second comparator compares the current sensor signal to a second reference value. The microcontroller generates a signal indicating a malfunction of the ignition system if the current sensor signal is lower than the second reference value while the voltage sensor signal is higher than the first reference value.
Public/Granted literature
- US20190120199A1 IGNITION SYSTEM OF AN AIRCRAFT TURBINE ENGINE Public/Granted day:2019-04-25
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