一种面向航空发动机数学模型的新型修正方法

钟文城; 汪勇; 宋劼; 张海波

doi:10.13224/j.cnki.jasp.20220114

一种面向航空发动机数学模型的新型修正方法

doi: 10.13224/j.cnki.jasp.20220114

南京航空航天大学能源与动力学院，南京 210016

基金项目: 航空发动机及燃气轮机重大专项基础研究项目（HT-J2019-Ⅲ-0009-0053）；科研与实践创新计划项目（XCXJH20210216）

详细信息

作者简介:
钟文城（1997-），男，硕士生，主要从事航空发动机建模与控制研究。E-mail：2392360116@qq.com

通讯作者:
汪勇（1994-），男，讲师，博士，研究方向为航空发动机建模、控制与故障诊断。E-mail：wangyong199427@163.com

中图分类号: V211.3
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出版历程
- 收稿日期: 2022-03-06
- 网络出版日期: 2023-04-11

A new correction method for aero-engine mathematical model

College of Energy and Power Engineering， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
为了建立高置信度的航空发动机热力性能模型，以准确掌握发动机的性能变化，实现航空发动机非设计性能的高精度预测，提出了一种面向航空发动机数学模型的新型修正方法。在对发动机部件特性线平移和缩放的基础上，考虑旋转自由度，达到对压气机特性线旋转调整的目的。引入非线性缩放因子函数与旋转因子函数以实现在不同的工况下适应性调节压气机特性数据。基于某型涡轴发动机，开展模型修正方法仿真验证。仿真结果表明：相比于仅考虑平移与缩放双自由度的模型修正方法，所提出的考虑平移、缩放与旋转的三自由度修正方法能使模型稳态平均误差从0.901%降至0.344%，大功率变化下的模型动态平均误差从1.295%降至0.889%，模型稳动态整体修正效果分别提升了62.99%和31.31%，可满足航空发动机数学模型的高精度要求。
- 航空发动机数学模型 /
- 模型修正 /
- 部件特性 /
- 粒子群优化 /
- 旋转自由度
Abstract:
In order to establish an aero-engine thermal performance model with high confidence, precisely master the engine performance changes and accurately predict performance of the aero-engine at off-design conditions, a new correction method for the aero-engine mathematical model was proposed. On the basis of the translation and scaling of the component characteristic line, the rotation degree of freedom was considered to achieve the purpose of rotation adjustment of the compressor characteristic line. Nonlinear scaling factor function and rotation factor function were introduced to realize adaptive adjustment of compressor characteristic data under different operating conditions. Based on a certain turboshaft engine, the simulation verification of model correction method was carried out. The simulation results showed that, compared with the model correction method only considering translation and scaling two degrees of freedom, the proposed three-degree-of-freedom correction method considering translation, scaling and rotation can reduce the model steady-state average error from 0.901% to 0.344%, the model dynamic average error under high-power changed from 1.295% to 0.889%, and the overall correction effect of model steady state and dynamics was improved by 62.99% and 31.31% , respectively, which can meet the requirements of higher aero-engine model accuracy.
- aero-engine mathematical model /
- model correction /
- component characteristics /
- particle swarm optimization /
- rotational degree of freedom

HTML

图 1 压气机特性线旋转示例

Figure 1. Compressor characteristic line rotation example

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图 2 模型修正流程图

Figure 2. Model correction flow chart

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图 3 涡轴发动机部件级建模流程

Figure 3. Process of turboshaft engine component level model

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图 4 修正因子变化图

Figure 4. Correction factor variation diagram

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图 5 模型修正结果参数对比

Figure 5. Comparison of model correction results

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图 6 模型修正相对误差对比

Figure 6. Comparison of model correction relative error

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图 7 动态过程参数对比

Figure 7. Parameters comparison of dynamic process

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图 8 动态过程相对误差对比

Figure 8. Comparison of relative error of dynamic process

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图 9 压气机特性线变化情况

Figure 9. Variation of compressor characteristic line

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表 1 工况点的选取

Table 1. Selection of working points

$ {n_{{\text{gt,rel}}}} $/%	工况点
79	修正点
89	测试点
90.25	测试点
92.51	修正点
94.14	测试点
95.64	修正点
96.12	测试点
96.66	修正点
97.76	测试点
98.23	修正点
98.96	测试点
99.96	修正点

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表 2 修正因子函数系数结果

Table 2. Coefficient results of correction factor function

修正因子	二次项系数	数值
${S_{\dot m}}$	a	1.0388
	b	−0.4362
	c	0.1624
${S_{\pi}}$	a	1.0171
	b	−0.7011
	c	−0.4943
${S_{\eta}}$	a	1.0198
	b	−0.1492
	c	−0.2079
$ {\theta _{\pi}} $	e	0.1301
$ {\theta _{\pi}} $	f	0.0929
$ {\theta _{\eta}} $	e	0.1062
$ {\theta _{\eta}} $	f	0.0835

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表 3 稳态精度对比结果

Table 3. Comparison results of steady-state precision

参数	平均误差/%			提升效果/%
参数	Original	2-DOF	3-DOF	提升效果/%
$ {n_{{\text{gt,rel}}}} $	2.204	0.494	0.107	74.97
$ {p_{\text{3}}} $	2.464	1.249	0.359	68.83
$ {T_{45}} $	4.517	0.961	0.568	45.18
总平均误差/%	3.062	0.901	0.344	62.99
误差小于1% 的占比/%	22.23	69.44	97.22

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表 4 动态精度对比结果

Table 4. Comparison results of dynamic precision

参数	平均误差/%			提升效果/%
参数	Original	2-DOF	3-DOF	提升效果/%
$ {n_{{\text{gt,rel}}}} $	4.366	1.187	0.765	35.55
$ {p_{\text{3}}} $	2.636	1.249	1.018	18.49
$ {T_{45}} $	5.801	1.448	0.885	38.88
总平均误差/%	4.267	1.295	0.889	31.31
误差小于2% 的占比/%	23.242	80.724	96.208

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