Effect of geometric parameters on fretting fatigue life of turbine attachment: test

被引：0

作者：

Jiang K. ^{[1
]}

Yan L. ^{[2
]}

Chen J. ^{[1
]}

Xu L. ^{[1
]}

Mao J. ^{[3
,4
,5
]}

Hu D. ^{[3
,4
,5
]}

Wang R. ^{[2
,4
,5
]}

机构：

[1] Hunan Aviation Powerplant Research Institute, Aero Engine Corporation of China, Hunan, Zhuzhou

[2] School of Energy and Power Engineering, Beihang University, Beijing

[3] Research Institute of Aero-Engine, Beihang University, Beijing

[4] United Research Center of Mid-Small Aero-Engine, Beijing

[5] Beijing Key Laboratory of Aero-Engine Structure and Strength, Beihang University, Beijing

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2023年 / 38卷 / 06期

关键词：

attachment; crack initiation; fretting fatigue; geometric parameter; high and low cycle load;

D O I：

10.13224/j.cnki.jasp.20230090

中图分类号：

学科分类号：

摘要：

Test and simulation studies were conducted to investigate the fretting fatigue behaviour and damage characterization of turbine attachment. Seven types of turbine attachment with different pressure angles, tooth angles, and tooth spacing were designed, and fatigue tests were carried out under high and low cycle loads. The second tooth of the tenon of all types suffered fretting fatigue failure. And the effect of the geometric parameters of the tenon on fretting fatigue was obtained: with the increase of pressure angle and tooth pitch, the fretting fatigue life gradually decreased; while with the increase of tooth shape angle, the fretting fatigue life was first kept basically the same, and then increased significantly. Critical evidence was provided to reveal the failure mechanism under combined high and low cycle loads, meanwhile important data were generated for determining the controlling parameter and validating the established model of the fretting fatigue for turbine tenons. © 2023 BUAA Press. All rights reserved.

引用

页码：1474 / 1480

页数：6

共 19 条

[1] WANG R Q, WEI J M, HU D Y, Et al., Investigation on experimental load spectrum for high and low cycle combined fatigue test, Propulsion and Power Research, 2, 4, pp. 235-242, (2013)
[2] RAYKOWSKI A, HADER M., Blast cleaning of gas turbine components: deposit removal and substrate deformation, Wear, 249, 1, pp. 126-131, (2001)
[3] XIE M L, ZHONG P D., Analysis of fracture failure of fir-tree serrations of stage Ⅱ: turbine disks, Engineering Failure Analysis, 7, 4, pp. 249-260, (2000)
[4] (1994)
[5] ZHENG Xudong, YU Duokui, WANG Zhaofeng, Et al., Mechanical analysis of crack failures in turbine blade and disk serration of an aeroengine, Aeroengine, 31, 3, pp. 35-38, (2005)
[6] GU Yuanxing, Research on fretting fatigue life of dovetail joint under HCF-LCF load, (2007)
[7] YAO Huaxing, YAN Shalin, A research on cracked failures of Fir-tree serration in aeroengine turbine disc, Journal of Aerospace Power, 6, 1, pp. 51-53, (1991)
[8] (1993)
[9] WEI Dasheng, WANG Yanrong, Effects of profile of contact surfaces on the stress distribution for tenon jointing in blade disk assesmblies, Jounal of Aerospace Power, 25, 2, pp. 407-411, (2010)
[10] UCHINO K，, KAMIYAMA T，, INAMURU T，, Et al., Three-dimensional photoelastic analysis of aeroengine rotary parts, Proceedings of International Symposiumon Photoelasticity, pp. 209-214, (1986)

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