Aircraft turbofan engine fan rotor trim method and device
A technology of fan rotor and aviation turbine, which is applied in the field of fan rotor trimming of aviation turbofan engine, which can solve the problems of unbalanced amount of low-pressure turbine rotor, time-consuming, manpower, financial resources, and difficulty in achieving balance goals, etc.
Active Publication Date: 2020-01-31
AECC COMML AIRCRAFT ENGINE CO LTD
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Problems solved by technology
However, due to problems such as wear and tear during assembly and service, the low-pressure turbine rotor still has the possibility of exceeding the required unbalance, and the vibration sensor at the fan end is also sensitive to the unbalance of the low-pressure turbine rotor
If only the vibration sensor signal at the fan end is analyzed, it will not be possible to determine whether the unbalance comes from the fan rotor or the low-pressure turbine rotor
In this case, it will be difficult to achieve the balance target only by trimming at the fan end, which will result in failure to achieve the balance requirement after multiple drive balances, consuming time, manpower, financial resources and other resources
Method used
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Embodiment Construction
[0035] The technical solutions of the present invention will be further described in detail below through the accompanying drawings and embodiments.
[0036] The flow chart of an embodiment of the method for balancing a fan rotor of an aviation turbofan engine of the present invention is as follows figure 2 Shown.
[0037] In step 201, the vibration amplitude of the fan rotor and the vibration amplitude of the low-pressure turbine rotor are obtained in the start-up test. In an embodiment, vibration sensors may be respectively arranged at the fan rotor and the low-pressure turbine rotor to collect the vibration conditions of the fan rotor and the low-pressure turbine rotor respectively.
[0038] In step 202, the unbalanced position of the aviation turbofan engine is determined according to the vibration amplitude of the fan rotor and the vibration amplitude of the low-pressure turbine rotor, and the inherent vibration peak coefficient of the low-pressure turbine rotor. The ratio of ...
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The invention provides a method and device for balancing a fan rotor of an aviation turbofan engine, and relates to the field of aviation engines. The method for balancing the fan motor of the aviation turbofan engine comprises the steps of obtaining the vibration amplitude of the fan rotor and the vibration amplitude of a low-pressure turbine rotor; determining an imbalance position of the aviation turbofan engine according to the vibration amplitude of the fan rotor, the vibration amplitude of the low-pressure turbine rotor and an inherent vibration peak coefficient of the low-pressure turbine rotor; and balancing the aviation turbofan engine through balancing the imbalance position. According to the method provided by the invention, the vibration amplitude can be measured respectively at the fan rotor end and the low-pressure turbine rotor end, and the imbalance position of the aviation turbofan engine is analyzed and determined, thereby performing the balancing operation in a moretargeted manner, avoiding the problems of poor effect and low efficiency caused by blind balancing for the fan rotor when the low-pressure turbine rotor gives rise to imbalance, optimizing the balancing effect, and improving the balancing efficiency.
Description
Technical field [0001] The invention relates to the field of aviation engines, in particular to a method and device for balancing a fan rotor of an aviation turbofan engine. Background technique [0002] In order to increase the bypass ratio and reduce fuel consumption of modern civil aviation turbofan engines, the diameter of the fan is usually larger. The general dynamic balancer cannot meet the requirements of the balancer size and power of the large-diameter fan rotor. Therefore, it is usually carried out on the balancer first. The low-pressure turbine rotor is dynamically balanced and the fan disc shaft plus the booster stage rotor assembly is dynamically balanced, and then the entire low-pressure rotor is locally balanced during the bench test after the engine is assembled. [0003] In the prior art, the low-pressure rotor local balance system analyzes the low-pressure speed sensor signal with key phase and the vibration sensor signal at the fan end, and calculates the magnit...
Claims
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IPC IPC(8): G01M15/12
CPCG01M15/12
Inventor 刘青山牛菁
Owner AECC COMML AIRCRAFT ENGINE CO LTD