航空发动机双辐板涡轮盘结构强度分析

韩枫; 徐伟建; 江文涛; 陈娇娜; 金易璇; 魏嵩; 毛军逵

doi:10.13224/j.cnki.jasp.20250436

航空发动机双辐板涡轮盘结构强度分析

doi: 10.13224/j.cnki.jasp.20250436

韩枫^{1, 2,},
徐伟建^{1, 2},
江文涛^{1, 2},
陈娇娜^{1, 2},
金易璇¹,
魏嵩¹,
毛军逵^1,*, ,

1.
南京航空航天大学能源与动力学院，南京 210016
2.
南京航空航天大学综合能源研究院，南京 210016

基金项目: 国家自然科学基金（52406048，52476077）；航空发动机及燃气轮机基础科学中心项目（P2022-A-Ⅱ-007-001）；江苏省基础研究计划（BK20252025）；国家科技重大专项（Y2022-Ⅲ-0003-0012）

详细信息

作者简介:
韩枫（1989-），男，副教授，博士，从事航空发动机热端部件流动与换热研究。E-mail：hanfeng@nuaa.edu.cn

通讯作者:
毛军逵（1976-），男，教授，博士，从事航空发动机热管理和高效热防护研究。E-mail：mjkpe@nuaa.edu.cn

中图分类号: V231.1
计量
- 文章访问数: 169
- HTML浏览量: 122
- PDF量: 13
- 被引次数: 0
出版历程
- 收稿日期: 2025-09-21
- 网络出版日期: 2026-04-18

Structural strength analysis of twin-web turbine disk for aero-engines

Han Feng^{1, 2
,},
Xu Weijian^{1, 2},
Jiang Wentao^{1, 2},
Chen Jiaona^{1, 2},
Jin Yixuan¹,
Wei Song¹,
Mao Junkui^{1,*
, ,}

1.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Integrated Energy Institute，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
面向高推质比航空发动机设计要求，以某航空发动机单辐板涡轮盘为基准，采用ANSY Fluent数值计算温度场和ABAQUS计算应力场，对比分析了单辐板涡轮盘和双辐板涡轮盘周向应力、径向应力和Von-Mises等效应力分布特点；重点研究了双辐板涡轮盘辐板倾角（θ）变化（8°≤θ≤ 12°）对双辐板涡轮盘应力水平影响规律。结果表明：与基准单辐板涡轮盘相比，双辐板涡轮盘结构减重效果明显，θ=8°，9°，10°，11°和θ=12°双辐板涡轮盘质量分别降低22.78%、23.23%、23.42%、23.2%以及23.16%。双辐板双传力路径结构特征使得双辐板涡轮盘的载荷和应力分布更加均匀，θ=12°双辐板涡轮盘应力水平在所研究倾角范围内最优，其最大周向应力、最大Von-Mises等效应力、关键点最大平均周向应力和关键点最大Von-Mises等效应力分别比θ=8°双辐板涡轮盘降低了15.66%、16.03%、15.65%和17.09%。未来进行双辐板涡轮盘结构设计时，应该将辐板倾角θ作为关键因素。
- 双辐板涡轮盘 /
- 辐板倾角 /
- 周向应力 /
- 径向应力 /
- 等效应力
Abstract:
In response to the design requirements of high thrust-to-weight ratio aero-engines, a single-web turbine disk of an aero-engine was selected as the benchmark. The temperature field was numerically calculated using ANSYS Fluent and the stress field was calculated using ABAQUS. The distribution characteristics of circumferential stress, radial stress and Von-Mises equivalent stress of single-web and twin-web turbine disks were compared and analyzed. The influence law of the web inclination angle (θ) on the stress level of the twin-web turbine disk was mainly studied. Results show that compared with the reference single-web turbine disk, the structural weight reduction effect of the twin-web turbine disk is obvious. The weights of the twin-web turbine disks with θ=8°, θ=9°, θ=10°, θ=11° and θ=12° are reduced by 22.78%, 23.23%, 23.42%, 23.2% and 23.16% respectively. The structural characteristics of the twin-web transmission path make the load and stress distribution of the twin-web turbine disk more uniform. The stress level of the twin-web turbine disk with θ=12° is the best in the study range, and its maximum circumferential stress, maximum Von-Mises equivalent stress, maximum average circumferential stress at the key points and maximum Von-Mises equivalent stress at the key points are respectively reduced by 15.66%, 16.03%, 15.65% and 17.09% compared with the twin-web turbine disk with θ=8°. In the future, the web inclination angle θ should be regarded as a key factor when designing the structure of the twin-web turbine disk.
- twin-web turbine disk /
- web inclination angle /
- circumferential stress /
- radial stress /
- Von-Mises stress

HTML

图 1 计算模型

Figure 1. Computational model

下载: 全尺寸图片幻灯片

图 2 网格独立性验证

Figure 2. Verification of grid independence

下载: 全尺寸图片幻灯片

图 3 计算网格和温度场

Figure 3. Computational grid and temperature field

下载: 全尺寸图片幻灯片

图 4 计算模型与周向应力结果

Figure 4. Computational model and circumferential stress results

下载: 全尺寸图片幻灯片

图 5 关键点周向应力数值模拟和试验结果

Figure 5. Numerical simulation and experimental results of the circumferential stress at the key points

下载: 全尺寸图片幻灯片

图 6 涡轮盘的关键点

Figure 6. Turbine disk key points

下载: 全尺寸图片幻灯片

图 7 涡轮盘周向应力分布云图

Figure 7. Circumferential stress distribution in turbine disk

下载: 全尺寸图片幻灯片

图 8 单辐板和双辐板涡轮盘平均周向应力沿着关键点变化

Figure 8. The average circumferential stress of single-web and twin-web turbine discs varies along the key points

下载: 全尺寸图片幻灯片

图 9 不同倾角θ双辐板涡轮盘平均周向应力沿着关键点分布

Figure 9. Distribution of the average circumferential stress along the key points of the twin-web turbine disk with different inclination angles θ

下载: 全尺寸图片幻灯片

图 10 涡轮盘径向应力分布云图

Figure 10. Radial stress distribution in turbine disks

下载: 全尺寸图片幻灯片

图 11 单辐板/双辐板涡轮盘平均径向应力沿着关键点

Figure 11. Average radial stress of single-web and twin-web turbine discs varies along the key points

下载: 全尺寸图片幻灯片

图 12 不同倾角θ双辐板涡轮盘平均径向应力沿关键点

Figure 12. Distribution of the average radial stress along the key points of the twin-web turbine disk with different θ

下载: 全尺寸图片幻灯片

图 13 涡轮盘等效应力分布云图

Figure 13. Von-Mises stress distribution in turbine disks

下载: 全尺寸图片幻灯片

图 14 单辐板/双辐板涡轮盘平均等效应力沿关键点变化

Figure 14. Average Von-Mises stress of single-web and twin-web turbine discs varies along the key points

下载: 全尺寸图片幻灯片

图 15 不同θ双辐板涡轮盘平均等效应力沿关键点分布

Figure 15. Distribution of the average Von-Mises stress along the key points of the twin-web turbine disk with different in θ

下载: 全尺寸图片幻灯片

图 16 涡轮盘沿传力路径的截面平均应力

Figure 16. Cross section average stress of turbine disk along load path

下载: 全尺寸图片幻灯片

图 17 不同倾角θ双辐板涡轮盘应力情况

Figure 17. Stress of twin-web turbine disk with different θ

下载: 全尺寸图片幻灯片

表 1 GH4169物性表

Table 1. GH4169 material properties table

参数	温度t/℃
参数	20	100	200	300	400	500	600	700
热膨胀系数α/10⁻⁶ K⁻¹	13.2	13.5	13.6	13.8	14	14.6	15	15.4
弹性模量 E/GPa	223	217	213	207	201	194	187	179
导热系数 $ \lambda $/（W/（m$ \cdot $K））	9.3	9.98	11.26	12.54	14.07	15.66	17.47	18.15
泊松比 $ \mu $	0.4	0.39	0.38	0.3	0.3	0.31	0.31	0.32

下载: 导出CSV

表 2 单辐板与双辐板涡轮盘质量对比

Table 2. Mass comparison between single-web and twin-web turbine disks

参数	单辐板涡轮盘	双辐板涡轮盘
参数	单辐板涡轮盘	θ=8°	θ=9°	θ=10°	θ=11°	θ=12°
m/kg	0.340547	0.26296	0.261422	0.260776	0.26153	0.26166
Δm/kg	0	0.07758	0.079125	0.079771	0.07901	0.07889
降幅/%	0	22.78	23.23	23.42	23.20	23.16

下载: 导出CSV

参考文献(25)

[1]	Bi Shuai, Mao Junkui, Wang Lei, et al. An optimized time-adaptive aerothermal coupling calculation method for aerothermal analysis of disc cavity system[J]. Chinese Journal of Aeronautics, 2024, 37(9): 164-177. doi: 10.1016/j.cja.2024.06.017
[2]	孔祥灿, 张子卿, 朱俊强, 等. 航空发动机气冷涡轮叶片冷却结构研究进展[J]. 推进技术, 2022, 43(5): 200632. Kong Xiangcan, Zhang Ziqing, Zhu Junqiang, et al. Research progress on cooling structure of aeroengine air-cooled turbine blade[J]. Journal of Propulsion Technology, 2022, 43(5): 200632. (in Chinese Kong Xiangcan, Zhang Ziqing, Zhu Junqiang, et al. Research progress on cooling structure of aeroengine air-cooled turbine blade[J]. Journal of Propulsion Technology, 2022, 43(5): 200632. (in Chinese)
[3]	Han Feng, Bi Shuai, Mao Junkui, et al. Film cooling effectiveness of a leading-edge cooling array of a rotating turbine blade with twist[J]. Applied Thermal Engineering, 2023, 225: 120175. doi: 10.1016/j.applthermaleng.2023.120175
[4]	Han Feng, Bi Shuai, Chen Jiaona, et al. Numerical investigation on the effects of squealer scale on the blade tip clearance leakage flow and heat transfer characteristics[J]. Aerospace Science and Technology, 2025, 166: 110567. doi: 10.1016/j.ast.2025.110567
[5]	Harding B R, Curtiss D H. Contoured disk bore: US20050025627A1[P]. 2005-02-03.
[6]	Kors D L. Integrated high performance turbine engine technology (IHPTET) program review: WL-TR-91-2038[R]. Wright-Patterson AFB: Wright Laboratory, 1991.
[7]	张乘齐, 黄文周, 刘学伟, 等. 低惯量涡轮转子结构设计与优化[J]. 燃气涡轮试验与研究, 2013, 26(4): 33-36, 50. Zhang Chengqi, Huang Wenzhou, Liu Xuewei, et al. Design and optimization of low inertia turbine rotor structure[J]. Gas Turbine Experiment and Research, 2013, 26(4): 33-36, 50. (in Chinese Zhang Chengqi, Huang Wenzhou, Liu Xuewei, et al. Design and optimization of low inertia turbine rotor structure[J]. Gas Turbine Experiment and Research, 2013, 26(4): 33-36, 50. (in Chinese)
[8]	陆山, 李伦未. 航空发动机高负荷涡轮盘双辐板结构优化设计[J]. 推进技术, 2011, 32(5): 631-636. Lu Shan, Li Lunwei. Twin-web structure optimization design for heavy duty turbine disk based for aero-engine[J]. Journal of Propulsion Technology, 2011, 32(5): 631-636. (in Chinese Lu Shan, Li Lunwei. Twin-web structure optimization design for heavy duty turbine disk based for aero-engine[J]. Journal of Propulsion Technology, 2011, 32(5): 631-636. (in Chinese)
[9]	陆山, 赵磊. 双辐板涡轮盘/榫结构优化设计方法[J]. 航空动力学报, 2014, 29(4): 875-880. Lu Shan, Zhao Lei. Structural optimization design method of twin-web turbine disk with tenon[J]. Journal of Aerospace Power, 2014, 29(4): 875-880. (in Chinese Lu Shan, Zhao Lei. Structural optimization design method of twin-web turbine disk with tenon[J]. Journal of Aerospace Power, 2014, 29(4): 875-880. (in Chinese)
[10]	董少静, 申秀丽, 康滨鹏, 等. 高推质比双辐板涡轮盘结构研究及光弹试验验证[J]. 航空动力学报, 2015, 30(1): 114-120. Dong Shaojing, Shen Xiuli, Kang Binpeng, et al. Structure research and photoelastic test verification of twin-web turbine disk with high thrust-weight ratio[J]. Journal of Aerospace Power, 2015, 30(1): 114-120. (in Chinese Dong Shaojing, Shen Xiuli, Kang Binpeng, et al. Structure research and photoelastic test verification of twin-web turbine disk with high thrust-weight ratio[J]. Journal of Aerospace Power, 2015, 30(1): 114-120. (in Chinese)
[11]	吴倩. 轮毂一体化双辐板涡轮盘换热及应力优化研究[D]. 长沙: 中南大学, 2023. WU Qian. Study on heat transfer and stress optimization of hub-integrated dual-spoke turbine disk[D]. Changsha: Central South University, 2023. (in Chinese WU Qian. Study on heat transfer and stress optimization of hub-integrated dual-spoke turbine disk[D]. Changsha: Central South University, 2023. (in Chinese)
[12]	李磊, 杨子龙, 唐仲豪, 等. 具有盘腔扰流柱群的双辐板涡轮盘对流换热特性分析[J]. 热能动力工程, 2019, 34(8): 63-70. Li Lei, Yang Zilong, Tang Zhonghao, et al. Convective heat transfer characteristics of twin web turbine disk with staggered pin fins in cavity[J]. Journal of Engineering for Thermal Energy and Power, 2019, 34(8): 63-70. (in Chinese Li Lei, Yang Zilong, Tang Zhonghao, et al. Convective heat transfer characteristics of twin web turbine disk with staggered pin fins in cavity[J]. Journal of Engineering for Thermal Energy and Power, 2019, 34(8): 63-70. (in Chinese)
[13]	毕绍康. 双辐板涡轮盘流热固耦合计算及优化设计[D]. 哈尔滨: 哈尔滨工业大学, 2020. Bi Shaokang. Thermal-solid coupling calculation and optimization design of turbine disk flow with two spokes[D]. Harbin: Harbin Institute of Technology, 2020. (in Chinese Bi Shaokang. Thermal-solid coupling calculation and optimization design of turbine disk flow with two spokes[D]. Harbin: Harbin Institute of Technology, 2020. (in Chinese)
[14]	Shen Xiu, Dong Shao. Structure optimization and welding residual stress analysis of twin-web turbine disc[J]. Advanced Materials Research, 2012, 622/623: 309-314.
[15]	Shen Xiuli, Hu Wentong, Dong Shaojing. Multidisciplinary and multifidelity optimization for twin-web turbine disc with asymmetric temperature distribution[J]. Structural and Multidisciplinary Optimization, 2019, 60(2): 803-816. doi: 10.1007/s00158-019-02237-3
[16]	Vasilyev B, Salnikov A, Semenov A, et al. Twin-web turbine discs: part 1: design and analysis of their efficiency[C]//ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, 2018
[17]	Vasilyev B, Magerramova L, Salnikov A, et al. Twin-web turbine discs: part 2: fabrication and processing[C]//ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, 2018
[18]	Cairo R R. Twin-web rotor disk: US5961287[P]. 1999-10-05.
[19]	Wang R Q, Li D, Hu D Y, et al. Effects of heat-treatment residual stress on low cycle fatigue life of a turbine disk in PM superalloy[C]//ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, 2015.
[20]	Joseph C B. Gas turbine compressor spool with structural and thermal upgrades: US6267553[P]. 2001-07-31.
[21]	Ubulom I A, shankar K, Neely A J. Turbine blade life prediction using fluid-thermal-structural interaction modelling[R]. ASME Paper GT2015-43071, 2015.
[22]	Keller S. A practical approach to implementing linear elastic fracture mechanics in gas turbine rotor disk analyses[R]. ASME Paper GT2015-43303, 2015.
[23]	洪杰, 马艳红. 航空燃气涡轮发动机结构与设计[M]. 北京: 科学出版社, 2021. Hong Jie, Ma Yanhong. Structure and design of aircraft gas turbine engine[M]. Beijing: Science Press, 2021. (in Chinese Hong Jie, Ma Yanhong. Structure and design of aircraft gas turbine engine[M]. Beijing: Science Press, 2021. (in Chinese)
[24]	Roy R P, Xu G, Feng J. A study of convective heat transfer in a model rotor-stator disk cavity[J]. Journal of Turbomachinery, 2001, 123(3): 621-632. doi: 10.1115/1.1371776
[25]	《中国航空材料手册》编辑委员会. 中国航空材料手册: 第5卷[M]. 北京: 中国标准出版社, 2001. Editorial Committee of China Aviation Materials Handbook. China Aviation Materials Handbook: Volume 5 [M]. Beijing: China Standards Press, 2001. (in Chinese Editorial Committee of China Aviation Materials Handbook. China Aviation Materials Handbook: Volume 5 [M]. Beijing: China Standards Press, 2001. (in Chinese)