| 贾文杰.航空发动机燃烧室参数化设计[J].航空发动机,2022,48(6):56-63 |
| 航空发动机燃烧室参数化设计 |
| Research on Parametric Design Method of Aeroengine Combustion Chamber |
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| DOI： |
| 中文关键词: 参数化 燃烧室 数值仿真 软件开发 航空发动机 |
| 英文关键词:parametric combustion chamber numerical simulation software development aeroengine |
| 基金项目:航空动力基础研究项目资助 |
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| 摘要点击次数: 1173 |
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| 中文摘要: |
| 为解决现有燃烧室设计方法中人工介入多、计算周期长的缺点，以及现有参数化方法中存在的局限性，提出采用参数化
数值仿真方法，将燃烧室数值仿真过程中的几何参数、网格参数和边界条件等需要多次修改的参数改为变量并提取，编程实现了
从几何建模、网格生成到求解和后处理环节的完全自动化；基于燃烧室设计流程建立燃烧室的一体化设计平台，通过该平台初步
计算得到了一种带直叶片3级旋流器燃烧室的几何模型，并采用参数化方法对其几何结构进行优化，优化后的燃烧室出口温度分
布系数达到0.235，接近设计要求值0.2。结果表明：采用参数化数值仿真方法可以将燃烧室初步设计周期降为不足传统方法的1/10，
证明了该参数化数值仿真方法的有效性好，一体化设计平台的可靠性高。 |
| 英文摘要: |
| Aiming at addressing the shortcomings of excessive manual intervention and long calculation cycle in the existing combus?
tion chamber design methods，as well as the limitations of existing parametric methods，a parametric numerical simulation method was pro?
posed，geometric parameters，grid parameters and boundary conditions that need to be modified multi-times during the numerical simula?
tion of the combustor were transformed to variables and extracted，and a fully automatic numerical simulation process which covers geomet?
ric modeling，mesh generation，solution and post-processing was accomplished through software programming. Based on combustor design
process，an integrated design platform for combustor design was established. The preliminary design module of the platform was used to ob?
tain the geometric model of a three-stage swirler combustor with flat vanes ，then the parametric method was used for geometry optimiza?
tion. The optimized combustion chamber outlet temperature distribution factor reaches 0.235，which is close to the design value of 0.2. By
applying the parametric numerical simulation method，the preliminary design cycle of the combustion chamber can be reduced to less than
1/10 of the traditional method，which demonstrate the effectiveness of the parametric design method and the reliability of the integrated de?
sign platform. |
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