轮盘低周疲劳模拟件设计及试验

doi:10.7527/S1000-6893.2023.28320

Abstract

Abstract:

The discs in aero-engines are continuously subjected to large cyclic loading， of which the bores， bolt holes， curvic couplings and other feature areas are susceptible to Low Cycle Fatigue （LCF） failure. To accurately predict the fatigue life of the discs， it is necessary to design simulating specimens to reflect the stress gradient and perform fatigue experiments， which will provide an important basis for the design of the aero-engine structure. The existing simulating specimen design methods usually require that the stress and strain distribution within a certain range of the hotspot of simulating specimen should be consistent with those of the disc. However， the definition of "certain range" in these methods lacks theoretical basis and no uniform understanding has been reached. This study proposes a simulating specimen design method considering the consistency of SWT parameter distribution at the hotspots of simulating specimens and discs. The simulating specimens for the bores， bolt holes， curvic couplings of the disc are designed. A series of LCF experiments on simulating specimens are conducted. The average fatigue life of the curvic coupling simulating specimens corresponding to 100% rotational speed is compared with the results of the turbine disc rotational fatigue experiment， and the relative error is 7%， with both cracks initiating from the weak crystallographic facets on the surface. Finally， the robustness of the simulating specimen design method is discussed.

Key words: aero-engine disc, low cycle fatigue, theory of critical distances, simulating specimen design, simulating specimen for bore, simulating specimen for bolt hole, simulating specimen for curvic coupling

CLC Number:

V231.95

Miaodong ZHAO, Dianyin HU, Jianxing MAO, Haihe SUN, Shiyong QIN, Yuanxing GU, Rongqiao WANG, Tengyue TIAN, Lin YAN, Zhixing XIAO. Simulating specimen for low cycle fatigue of aero-engine disc: Design and experiment[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(18): 228320-228320.

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References 33

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材料	密度/（g·cm^-3）	温度/℃	弹性模量/GPa	剪切模量/GPa	泊松比	线膨胀系数/（10^-6 ℃）
FGH96	8.32	200	208		0.31	11.9
FGH96	8.32	700	176		0.37	14.0

DD6 ［001］取向	8.78	650	107.5	100	0.37	13.3
DD6 ［001］取向	8.78	980	80.5	74.2	0.38	14.9

最大载荷/kN	对应转速/%	载荷比	数量
53.28	120	0.05	4
57.80	125	0.05	4
60.60	128	0.05	4
62.53	130	0.05	4
53.28	120	0.20	4
57.80	125	0.20	4
60.60	128	0.20	4
62.53	130	0.20	4

最大载荷/kN	对应转速/%	载荷比	数量
55.89	90	0.05	2
62.27	95	0.05	4
69.00	100	0.05	4
55.89	90	0.20	1
62.27	95	0.20	8
69.00	100	0.20	8

最大载荷/kN	对应转速/%	载荷比	数量
28.00	100	0.1	3
28.00	100	0.2	3

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Simulating specimen for low cycle fatigue of aero-engine disc: Design and experiment

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