High-cycle fatigue test design method for aviation turbojet and turbofan engine
A technology of high-cycle fatigue and test design, applied in jet engine testing, gas turbine engine testing, vibration testing, etc., can solve the problems of immature and perfect high-cycle fatigue test methods, achieve short test period, good economic benefits, EFFECTS OF SIMPLICITY OF THE EXPERIMENTAL DESIGN PROCESS
Pending Publication Date: 2022-07-12
CHENGDU ENGINE GROUP
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[0003] The current high-cycle fatigue test design method, especially for the high-cycle fatigue test method of the aviation gas turbine engine is not mature and perfect
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[0021] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
[0022] It should be noted that the embodiments in the present application and the features of the embodiments may be combined with each other in the case of no conflict. The present invention will be described in detail below with reference to the accompanying drawings and the embodiments, and the technical solutions of the present invention will be described clearly and completely. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.
[0023] like figure 1 As shown, an aviation turbojet and turbofan engine high-cycle fatigue test design method according to an embodimen...
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The invention provides an aviation turbojet and turbofan engine high-cycle fatigue test design method. The method comprises the following steps: determining a blade sweep frequency measurement standard, a test design reference level and a rotating speed step; according to the requirement of the blade high-cycle fatigue cycle number, calculating the theoretical total time of operation of each rotating speed step and the theoretical total time of operation of the whole test run by using a test design reference level; decomposing the theoretical total operation time of each rotating speed step, determining the operation time of each rotating speed step in each test run, and rounding to obtain the total operation time required by the whole test run; comparing the total running time required by the whole test run with the total theoretical running time of the whole test run, if the increased time does not exceed a set threshold value, continuing the design step, otherwise, rounding again; and arranging each rotating speed step and the corresponding engine running time according to a rule to obtain a high-cycle fatigue test run program. The method has the advantages of being simple in test design process, sufficient in assessment, short in test period, good in economic benefit and the like.
Description
technical field [0001] The invention relates to the technical field of complete machine testing of aviation gas turbine engines, in particular to a high-cycle fatigue test design method for aviation turbojet and turbofan engines. Background technique [0002] High-cycle fatigue damage of parts such as blades is a typical damage mode of aviation gas turbine engines. In order to obtain good engine performance, aero-engine blade parts are generally designed to be as thin and light as possible, with complex profiles, but high performance and high reliability are contradictory, and the airflow flowing through the engine will excite the blades to generate stress. Low level but high frequency vibration. If the vibration frequency of the blade caused by the excitation coincides with or is close to the natural frequency of the blade, it will cause the blade to resonate. At this time, the vibration stress of the blade will increase significantly. Under the condition of high frequency ...
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Login to View More IPC IPC(8): G01M15/14G01M7/02
CPCG01M15/14G01M7/02G01M7/022Y02T90/00
Inventor 蒋全维吴盟冯祥金钟华科吴国炜段红春陈登勇
Owner CHENGDU ENGINE GROUP