Test system and method for measuring vibration damping characteristics of blisk structure with friction damping device
A friction damping and test system technology, applied in the field of aviation systems, can solve problems such as vibration of the foundation bench and the influence of test measurement results, and achieve the effects of high measurement accuracy, convenient measurement, and accurate test results.
Active Publication Date: 2021-01-01
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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[0005] Chinese Patent Application No. 201410728989.8 discloses "a damping structure optimization blade test bench and its experimental method". The exciter is fixedly connected to the entire foundation frame, so when the vibrator is excited, it will cause the vibration of the foundation frame, which will have a certain impact on the test measurement results
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[0041] Below in conjunction with embodiment the present invention will be further described.
[0042] Such as Figure 1-6 As shown, a test system for determining vibration damping characteristics of a blisk structure with a friction damping device includes a base frame, a loading device, an excitation device and a measuring device. Applying a loading force, the excitation device applies an exciting force to the blades 1-7; wherein:
[0043] The basic platform includes a base 1-1 installed on the lower end of the support 1-2, an upper cover plate 1-5 installed on the top end of the support 1-2, and a wheel disc 1-3 set on the middle shaft section of the support 1-2 and a plurality of blades 1-7 fixed on the circumference of the outer edge of the wheel disc 1-3, and the friction damping sheet 1-4 is installed under the edge plate between two adjacent blades 1-7;
[0044] The loading device includes several loading bases 2-1 fixed on the circumference of the base 1-1 and eyebol...
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The invention, which belongs to the testing device in the technical field of aeronautical systems, discloses a test system for measuring vibration damping characteristics of a blade disc structure with a friction damping device, thereby measuring the dynamic characteristic parameters of the blade disc system with a friction damping device. The test system is mainly composed of a basic rack, a loading device, a measurement device, and an excitation device. A support unit, a wheel disc, and an upper cover plate are installed on a base; blades are installed on the wheel disc. According to the test system, the mounting number of the blades can be adjusted based on the test needs. A friction damping device is connected in series with a dynamometer by a turnbuckle and a nylon wire; the tensile force of the nylon wire is changed by adjusting the length of the turnbuckle and the dynamometer is used for measuring the tensile force to simulate the centrifugal force generated by the damping device at different working speeds. Exciting force forces are applied to the blades by a multi-channel signal generator, a power amplifier, and an exciter; and different exciting forces with different phases can be simulated; and then a laser displacement sensor is used for measuring the dynamic response of the blade.
Description
technical field [0001] The invention belongs to the technical field of aviation systems, and in particular relates to a test system and a method for measuring the damping characteristics of a blisk structure with a friction damping device. Background technique [0002] The damping on aeroengine blades can be roughly divided into four types: material damping, frictional damping, aerodynamic damping and impact damping. Among these forms of blade damping, friction damping and impact damping are two promising blade damping structures. At this stage, there are still relatively few studies on impact damping, and it is believed that when the engine is working normally, its contribution to vibration reduction is relatively small. Frictional damping is currently the most effective vibration reduction technology. It does not need to change the quality and stiffness of the blade. As long as a suitable friction pair is added at an appropriate place, the effect of consuming energy and s...
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IPC IPC(8): G01M13/00G01M7/02
CPCG01M7/025G01M13/00
Inventor 漆文凯殷啸宇徐颖
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS