| 摘要: |
| 为满足小型无人机和导弹等航空器使用的航空发动机的要求，基于轴流式压气机结构，提出了一种主轴固定、内静子、外转子的新型“静轴式压气机”构型。通过对压气机基元级运动模型简化分析，建立了空气在压气机基元级压缩过程的动力学模型，确定两段压气机与中间泄气隔断结构参数，进一步计算得出各级出口温度变化曲线。结合理论计算，对静轴式压气机部件进行三维建模，运用Fluent软件验证基元级增压原理，并在Workbench软件中开展关键转子部件的静力学仿真与性能分析。结果表明：静轴式压气机整体采用前四级后五级的九级压缩方式，总压比达到12，静温变化量达到51.5℃，满足高增压比、分段燃烧的需求；压气机基元级数值模拟结果满足增压原理，应力应变满足强度要求，转子结构设计最大变形量较传统压气机减小，可以满足小型飞行器用压气机的设计要求。 |
| 关键词: 静轴式压气机 结构设计 分段压缩 力学性能 数值模拟 |
| DOI：10.13675/j.cnki.tjjs.201002 |
| 分类号:V232 |
| 基金项目: |
|
| Structural Design and Static Performance Analysis of Static Shaft Compressor |
|
MA Rong1, JIN He-rong2,3, YI Ya-li1, YANG Jing-sheng4
|
|
1.School of Mechanical Engineering，Yanshan University，Qinhuangdao 066004，China;2.Key Laboratory of Advanced Forging and Stamping Technology and Science of Ministry of National Education， Yanshan University，Qinhuangdao 066004，China;3.Parallel Robot and Mechatronic System Laboratory of Hebei Province，Yanshan University， Qinhuangdao 066004，China;4.Bureau of the Retired Personnel，Ministry of Industry and Information Technology，Beijing 100804，China
|
| Abstract: |
| In order to meet the requirements of aeroengines used in small unmanned aerial vehicles and missiles， a new configuration of “static shaft compressor” with fixed spindle， inner stator and outer rotor was proposed based on the structure of axial compressor. Based on the simplified analysis of the movement model of the compressor elementary level， the dynamic model of the air in the compressor elementary level compression process was established， and the structural parameters of the partition between the two-stage compressor and the middle vent gas stage were determined， and the temperature variation curves at the outlet of each stage were obtained. Combined with the theoretical calculation， the three-dimensional modeling of the stator shaft compressor components is carried out， Fluent software was used to verify the principle of elementary level pressurization， and the static simulation and performance analysis of the key rotor components are carried out in the Workbench software. The results show that， the static shaft compressor adopts a nine-stage compression mode of the first four stages and the second five stages， the total pressure ratio reaches 12， and the static temperature change reaches 51.5℃， which meets the requirements of high pressure ratio and segmenting combustion. The numerical simulation results of the compressor elementary level meet the pressurization principle， the stress and strain can meet the strength requirements， and the maximum deformation of the rotor structure is less than that of the traditional compressor， which can meet the design requirements of the compressor for small aircraft. |
| Key words: Static shaft compressor Structural design Segmental compression Mechanical properties Numerical simulation |
