Method for monitoring the state of health of at least two vibration sensors of a twin-spool turbomachine
A vibration sensor, health state technology, applied in vibration measurement, vibration measurement in solids, vibration measurement in fluids, etc., can solve problems such as detection principle limitations, faulty vibration sensors, and suboptimal monitoring stages to ensure reliability. sexual effect
Pending Publication Date: 2021-09-07
SAFRAN AIRCRAFT ENGINES SAS
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Problems solved by technology
[0008] However, this detection principle has limitations, erroneously declaring the failure of false vibration sensors
[0009] - suboptimal monitoring phases, vibration levels in these phases are often below the detection level of sensor damage;
Method used
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Embodiment Construction
[0040] figure 1 Shown is a twin-flow twin-turbine of an aircraft comprising a ducted fan 1 , a primary annular flow space I and a secondary annular flow space II (secondary ducts) from upstream to downstream in the direction of air flow (according to the axis AA of the engine) , the primary annular flow space and the secondary annular flow space are bounded by the outer casing 2 and the inner hub 3 . In the main line I, the turbine comprises a low-pressure compressor 11 , a high-pressure compressor 12 , a combustion chamber 13 , a high-pressure turbine 14 and a low-pressure turbine 15 .
[0041] Thus, the turbine comprises a low-pressure body and a high-pressure body at the front and at the rear (in the direction of the air flow).
[0042] As mentioned at the beginning, vibration sensors are arranged at the front and rear to measure the vibration of the low-pressure body and the high-voltage body.
[0043] Such as figure 2 Schematically shown, according to one embodiment, ...
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The invention relates to a method for monitoring the state of health of at least two vibration sensors of a twin-spool turbomachine comprising a low-pressure spool and a high-pressure spool, one vibration sensor being located at the front of the turbomachine, and another vibration sensor being located at the rear of the turbomachine, each of the sensors being configured to measure the vibrations of the low-pressure spool and high-pressure spool at the front and at the rear of the turbomachine, the method being carried out in a processing unit (20) of the turbomachine, which processing unit is in communication with each of the sensors, the method comprising the following steps: receiving the low-pressure speed (NBP) and high-pressure speed (NHP) of the turbomachine and, when the speeds are simultaneously in predetermined ranges; receiving the front and rear vibration levels of the low-pressure and high-pressure spools which are recorded by each sensor; establishing the mean of the values of the vibration levels of the low-pressure and high-pressure spools received over a predetermined receiving time; establishing the state of health of the at least first and second vibration sensors from a comparison between the established mean values of the vibration levels of the low-pressure and high-pressure spools and predetermined thresholds.
Description
technical field [0001] The present invention relates to the monitoring of the state of health of the twin turbines of an aircraft, more particularly, the monitoring of the health of the twin turbines of an aircraft is achieved by monitoring the vibration levels in the turbines. And the invention relates more particularly to the monitoring of vibration sensors used for this purpose. Background technique [0002] The health status of the turbine is usually monitored by various sensors. Among them, the vibration sensor is indispensable, because the vibration sensor can quickly detect the damage of the parts, the increase of the gap and any other failure that can endanger the turbine. [0003] A twin-turbine generally includes a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine along the flow direction of the airflow. [0004] A known solution for monitoring vibrations of a turbine is to arrang...
Claims
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IPC IPC(8): F01D21/00F01D25/04G01H1/00F01D17/02G01H3/00
CPCF01D25/04F01D21/003G01H3/005G01H1/006F05D2260/80F05D2270/334F05D2260/83F05D2260/96F01D17/02F05D2220/323
Inventor 鲍里斯·亚历山大
Owner SAFRAN AIRCRAFT ENGINES SAS