A blade leading edge high cycle fatigue simulation part and design method

Abstract

The invention relates to a blade leading edge high cycle fatigue simulation part and a design method thereof. The simulation part adopts a three-point bending structure and is composed of an outer loading area and an inner test assessment section. The overall loading area is "U-shaped" with a groove in the middle The loading position and both ends are pin hole support positions. The cross-section of the assessment section is in the shape of the leading edge of the blade, which forms a "T-shaped" cross-section with the load-bearing area. The top of the cross-section is the dangerous part (maximum stress) under the loaded state. The main design steps are: ( 1) According to the geometric dimensions of the leading edge of the blade, the cross-sectional geometric dimensions of the assessment section are designed to ensure the geometric consistency of the two; (2) By adjusting the length, height and load of the assessment section, the stress level of the dangerous part reaches the high cycle fatigue limit of the material, At the same time, the displacement of the loading point meets the requirements of the amplitude-frequency characteristics of the high-cycle fatigue testing machine; (3) Design and check the strength of the loading pin and the pin hole, and make the safety factor meet the design requirements by adjusting the aperture of the pin hole.

Description

Technical field [0001] The present invention is a high-cycle fatigue simulation part and design method for the leading edge of the aircraft engine compressor blade, which is a high-week fatigue simulation part design method that can consider the geometry of the leading edge of the compressor blade, specific hazardous parts, loading stability, machinability and high-cycle fatigue testing machine amplitude frequency characteristics, which belongs to the field of aerospace engine technology. Background [0002] Due to the performance requirements of aero engines, compressor blades are often thin in thickness and distorted in shape, and under the action of airflow excitation, they face a severe risk of high-cycle fatigue failure. In addition, in the field working environment, it is difficult to avoid inhaling foreign bodies such as sand and gravel, causing damage to the leading edge of the compressor blade. In order to study the effect of foreign object damage on the high-cycle fati...

AI Technical Summary

Problems solved by technology

[0004] In short, the existing technical solutions have their own shortcomings, and it is difficult to meet the requirements of the high cycle fatigue test of the leading edge of the blade:

[0005] (1) The existing real blade test piece used in the vibration test bench is difficult to control the leading edge of the blade as a dangerous point

[0006] (2) The existing uniaxial tensile simulation parts have poor rigidity and large displacement under load, which is difficult to meet the amplitude-frequency characteristic requirements of high-frequency fatigue machines

[0007] (3) The existing three-point bending test piece is open-loaded and prone to slipping problems

At the same time, its structure is in the form of equal height, which cannot guarantee the processing quality after the shape of the leading edge of the blade exists

[0008] (4) At present, the design of the leading edge simulation parts of the blade is only designed from the perspective of geometric similarity, and the problem of matching the deformation under load with the high-frequency fatigue machine is not considered

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