Identification and completion method for blade tip timing signal loss
A timing signal and signal loss technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of blade tip timing sensor signal and speed sensor signal loss, blade vibration information extraction obstacles and other problems, to achieve effective guarantee Extract, improve processability, overcome the effects of signal loss
Active Publication Date: 2019-06-11
XI AN JIAOTONG UNIV
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Problems solved by technology
The traditional strain gauge method cannot meet the needs of aero-engine blade monitoring. Therefore, in order to monitor common accidents such as high-cycle fatigue cracks of blades, it is necessary to develop a blade health monitoring system based on blade tip timing technology.
However, due to the influence of the internal working environment of the aero-engine and the instability of signal transmission, the signals of the timing sensor at the tip of the blade and the signal of the speed sensor are often lost, which has caused great obstacles to the extraction of blade vibration information.
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[0047] S1. According to the experiment, the number of rotor blades is 16, and the number of blade-end timing sensors is 8, such as image 3 As shown, theoretically the relationship between adjacent speed signals and blade tip timing signals is:
[0048] N(Fr k ≤tk+1 )=N b ×N p =16×8
[0049] Due to the loss of the blade tip timing signal itself, the allowable range of setting error is 30%, and the position where the speed signal is lost is identified (159, 205, 220, 319, 503, 575, 638, 758, 795), and the speed signal is lost The number is 10.
[0050] S2. According to the signal loss rate calculation formula, the signal loss rate is obtained as 1.07%, and the rotational speed signal is evenly supplemented.
[0051] S3. Taking the arrival time of the first leaf in each circle as the center of the pane at that time, calibrate the offset of the center of the pane of the circle, and divide the panes. The number of panes is the same as the number of leaves is 16, and the signa...
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The invention discloses an identification and completion method for blade tip timing signal loss, which comprises the following steps: based on an interpolation relation between a rotating speed signal sequence and a blade tip timing signal sequence, identifying positions and the number of rotating speed signal loss; calculating a rotating speed signal loss rate, and executing a rotating speed signal completion scheme according to the rotating speed signal loss rate; The invention discloses a single-circle blade signal loss identification method based on pane division. identifying the positionof blade signal loss; judging whether the blade end timing signal loss is continuous loss or discontinuous loss according to the position of the blade signal loss; if so, adopting a signal completionmethod based on pane division; and if so, adopting a signal complementing method based on front and rear effective circles. The method can effectively cope with the phenomenon of signal loss in the blade tip timing signal acquisition process, improves the signal processability, and facilitates subsequent blade vibration displacement information extraction.
Description
technical field [0001] The invention relates to a method for identifying and complementing the loss of blade end timing signals, which belongs to the field of non-contact testing of blades. Background technique [0002] The strain gauge method is the most commonly used vibration measurement method. This method needs to paste the strain gauge on the blade, which is not easy to install, and can only monitor the vibration at the position of the strain gauge. Blade tip timing is a non-contact measurement method that overcomes the above three shortcomings of the traditional strain gauge method and can monitor the vibration of all blades at the same time. For aero-engines, in order to ensure light weight and dynamic performance, the mass of the blades should be as small as possible and the load capacity of the blades should be as large as possible, resulting in frequent blade failures. The traditional strain gauge method cannot meet the needs of aeroengine blade monitoring. There...
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IPC IPC(8): G06F17/50
Inventor 杨志勃王增坤陈雪峰吴淑明李浩琪翟智田绍华乔百杰
Owner XI AN JIAOTONG UNIV