双转子航空发动机中介支点动载荷控制研究

王东; 洪杰; 李其建; 王永锋; 王楚君

doi:10.13224/j.cnki.jasp.20230252

双转子航空发动机中介支点动载荷控制研究

doi: 10.13224/j.cnki.jasp.20230252

王东^{1, 3,},
洪杰²,
李其建¹,
王永锋²,
王楚君¹

1.
中国航发沈阳发动机研究所，沈阳 110015
2.
北京航空航天大学能源与动力工程学院，北京 100191
3.
北京航空航天大学航空发动机研究院，北京 100191

基金项目: “两机”专项基础研究项目“航空发动机总体结构快速建模及结构布局技术研究”（2017-Ⅰ-0008-0009）

详细信息

作者简介:
王东（1983-），男，研究员，博士生，主要从事航空发动机总体结构设计。E-mail：foreverwangd@126.com

中图分类号: V231.96
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出版历程
- 收稿日期: 2023-04-15
- 网络出版日期: 2024-10-01

Dynamic load control of intermediate fulcrum of dual rotor aero-engine

1.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
2.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China
3.
Research Institute of Aero-Engine，Beihang University，Beijing 100191，China

摘要

摘要:
针对中介支点动载荷控制问题，建立质量和刚度等效的中介支点-双转子系统动力学模型，基于敏感度分析识别出不平衡激励载荷、陀螺力矩载荷、转轴弹性变形恢复力等影响中介支点动载荷的关键因素，并结合型号研制经验，提出了基于转子平衡品质控制与变形状态协调的中介支点动载荷控制方法，通过转子平衡品质控制、涡轮盘角向变形控制以及中介支点轴向位置选取等措施，分别使中介支点应变能占比和动载荷降低26%和55%。上述研究在型号研制中的得到验证，提高了整机结构系统可靠性。
- 航空发动机 /
- 中介支点 /
- 动载荷 /
- 平衡品质 /
- 陀螺力矩
Abstract:
In order to solve the problem of dynamic load control for intermediate fulcrum, a dynamic model of the intermediate fulcrum dual rotor system with equivalent mass and stiffness was established, and the key factors significantly affecting the dynamic load of intermediate fulcrum were identified through sensitivity analysis of unbalanced excitation load, gyro moment load, shaft elastic deformation restoring force, etc. Combining the project development experience, a series of methods for controlling the dynamic load of intermediate fulcrum based on the coordination of rotor balance quality and deformation status were proposed, such as rotor balance quality control, turbine disk angular deformation control, and selection of axial position of intermediate fulcrum. The proportion of strain energy and dynamic load at intermediate fulcrum were reduced by 26% and 55%, respectively. The above research was validated in project development, improving the reliability of the overall structural system.
- aero-engine /
- intermediate support /
- dynamic load /
- balance quality /
- gyro moment

HTML

图 1 中介支点双转子发动机总体结构布局方案

Figure 1. Overall structural layout scheme of dual rotor engine with intermediate support

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图 2 带中介支点双转子系统力学模型^[13]

Figure 2. Mechanical model of dual rotor system with intermediate support^[13]

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图 3 中介支点双转子发动机振动耦合试车频谱

Figure 3. Vibration coupling test spectrum of dual rotor engine with intermediate support

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图 4 含中介支点双转子有限元模型

Figure 4. Dual rotor model of finite element method with intermediate support

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图 5 质心偏移与惯性主轴倾斜^[17]

Figure 5. Centroid shift and inertia spindle tilt^[17]

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图 6 各支点处振幅频域响应

Figure 6. Amplitude response of each support in frequency domain

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图 7 各支点动载荷时域响应

Figure 7. Dynamic load response of each support in time domain

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图 8 含中介支点高压转子系统简化模型

Figure 8. Simplified model of high pressure rotor system with intermediate support

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图 9 高压涡轮质心处位移及支点动载荷幅频曲线

Figure 9. Amplitude frequency curve of displacement and support dynamic load at center of mass of high pressure turbine disk

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图 10 高压转子结构及其自由模态弹性线

Figure 10. High pressure rotor structure and its free mode elastic line

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图 11 双转子系统模态振型

Figure 11. Modal vibration mode of dual rotor system

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图 12 中介轴承轴向位置对其动载荷的影响

Figure 12. Effect of axial position of intermediate bearing on its dynamic load

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图 13 转子平衡品质控制流程

Figure 13. Control process of rotor balance quality

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图 14 典型高转子结构示意图

Figure 14. Schematic diagram of typical high pressure structure

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图 15 中介支点应变能与高压涡轮后轴颈刚度

Figure 15. Strain energy of intermediate support and stiffness of high pressure turbine disk rear journal

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图 16 涡轮端支点径向同环设置双转子

Figure 16. Dual rotor with supports of turbine end at same axial position

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表 1 双转子模型质量和刚度参数

Table 1. Mass and stiffness parameters of dual rotor model

参数	数值
风扇质量/kg	130
压气机质量/kg	88
高压涡轮质量/kg	136
高压涡轮极转动惯量/（kg·m²）	5.25
低压涡轮质量/kg	87
低压涡轮极转动惯量/（kg·m²）	4.70
高压鼓筒轴半径/mm	130
低压涡轮轴半径/mm	60
1#-2#支点跨度/mm	680
2#-5#支点跨度/mm	1400
3#-4#支点跨度/mm	1120
4#-5#支点跨度/mm	75
中介轴承支承刚度/10⁷ （N/m）	25
其他轴承支承刚度/10⁷ （N/m）	5

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表 2 转子平衡品质控制参数

Table 2. Control parameters of rotor balance quality

级别	长径比	平衡及精度要求		平衡面相位差/（°）
零件级	$ {L \mathord{\left/ {\vphantom {L D}} \right. } D} \leqslant 0.2 $	静平衡	初始静不平衡G40/剩余不平衡G6.3	−30～30
零件级	$ {L \mathord{\left/ {\vphantom {L D}} \right. } D} > 0.2 $	动平衡	初始静不平衡G40/剩余不平衡G6.3	150～210
组件级	$ {L \mathord{\left/ {\vphantom {L D}} \right. } D} \leqslant 0.2 $	静平衡	初始静不平衡G8
	$ {L \mathord{\left/ {\vphantom {L D}} \right. } D} > 0.2 $	动平衡	初始静不平衡G10	−30～30
	$ {L \mathord{\left/ {\vphantom {L D}} \right. } D} > 0.2 $	动平衡	初始静不平衡G8/平衡面初始不平衡G10	150～210
系统级	$ {L \mathord{\left/ {\vphantom {L D}} \right. } D} \leqslant 0.2 $	静平衡	剩余静不平衡G4
	$ {L \mathord{\left/ {\vphantom {L D}} \right. } D} > 0.2 $	动平衡	剩余静不平衡量G4	−30～30
	$ {L \mathord{\left/ {\vphantom {L D}} \right. } D} > 0.2 $	动平衡	剩余静不平衡G2.5/平衡面剩余不平衡G4	150～210

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