基于分级优化的微型涡喷发动机模型修正

张伟罡; 陈毓智; 缑林峰; 贾琳渊

doi:10.13224/j.cnki.jasp.20240835

基于分级优化的微型涡喷发动机模型修正

doi: 10.13224/j.cnki.jasp.20240835

西北工业大学动力与能源学院，西安 710129

基金项目: 国家自然科学基金（52402520）

详细信息

作者简介:
张伟罡（1999-），男，博士生，研究方向为航空发动机总体性能与健康管理。E-mail：zhangweigang@mail.nwpu.edu.cn

通讯作者:
陈毓智（1989-），男，副教授，博士，研究方向为燃气涡轮发动机总体性能与健康监测。E-mail：yuzhi.chen@nwpu.edu.cn

中图分类号: V235.1
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出版历程
- 收稿日期: 2024-12-12
- 网络出版日期: 2025-08-02

Model adaptation of micro turbojet engines based on hierarchical optimization

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China

摘要

摘要:
为了提高微型涡喷发动机性能模型的仿真精度，提出一种分级优化的发动机模型修正算法，首先建立了通用仿真模型并与商用软件对比验证可靠性；其次，开展微型涡喷发动机试车实验，获取发动机含慢车在内的14组非设计点稳态和过渡态实验数据；再次，设计了综合设计点参数和特性线修正的两级优化方法，实现宽工况范围的高精度稳态仿真；最后，基于动态效应修正，改善过渡态模型的仿真精度。与试车数据相比，稳态模型最大相对误差为2.4%，相较于不优化设计点参数降低了88%，考虑4种过渡态效应与仅优化转动惯量相比，过渡态模型最大相对误差为12.9%，压气机和涡轮出口总温的误差分别降低了9.2%和31.7%。因此，基于分级优化的微型涡喷发动机模型修正方法能够有效提高稳态和过渡态仿真精度。
- 微型涡喷发动机 /
- 模型修正 /
- 分级优化 /
- 设计点优化 /
- 过渡态效应
Abstract:
In order to enhance the simulation accuracy of the micro turbojet engines performance model, a model adaptation algorithm based on hierarchical optimization was proposed. Firstly, a general simulation model was established and its reliability was verified by comparison with commercial software. Secondly, engine test runs of micro turbojet engines were carried out to obtain 14 sets of engine test data for both steady-state and transient conditions at off-designed point, including idle conditions. Thirdly, a two-level optimization algorithm for design point parameters and characteristic lines was designed to achieve high-precision steady-state simulation over a wide range of working conditions. Finally, based on the correction of dynamic effects, the simulation accuracy of the transient model was improved. Compared with the test data, the maximum relative error of the steady-state model was 2.4%, which was 88% lower than that without optimizing the design point parameters. Considering four transient effects, compared with that only optimizing the moment of inertia, the maximum relative error of the transient model was 12.9%, and the errors of compressor and turbine exit total temperature were reduced by 9.2% and 31.7%, respectively. Therefore, the model adaptation method for micro turbojet engines based on hierarchical optimization can effectively improve the simulation accuracy of both steady-state and transient conditions.
- micro turbojet engine /
- model adaptation /
- hierarchical optimization /
- design point optimization /
- transient effect

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图 1 通用模型组成

Figure 1. Components of general modelling

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图 2 压缩部件和膨胀部件数学模型计算流程

Figure 2. Calculation process of mathematical model for compression and expansion components

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图 3 微型涡喷发动机结构和编号

Figure 3. Structure and numbering of micro turbojet engine

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图 4 模型稳态验证

Figure 4. Validation under steady-state conditions

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图 5 PTE-1200A2涡喷发动机外观图

Figure 5. PTE-1200A2 turbojet engine appearance diagram

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图 6 工艺进气道测点布局示意

Figure 6. Process inlet measuring point layout

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图 7 压气机后测点布局示意图

Figure 7. Layout diagram of measuring point after compressor

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图 8 涡轮后测点布局示意

Figure 8. Turbine rear measuring point layout

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图 9 转速控制计划

Figure 9. Control schedule of speed

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图 10 三级模型修正流程

Figure 10. Three-step model revision process

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图 11 耦合系数对于特性图的影响

Figure 11. Effect of coupling coefficient on the component map

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图 12 稳态修模相对误差

Figure 12. Relative error of steady-state after model adaptation

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图 13 部件特性图修正前后对比

Figure 13. Component map comparison before and after model adaptation

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图 14 S变化规律

Figure 14. Variation rule of S

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图 15 过渡态模型仿真对比及相对误差

Figure 15. Comparison and relative error of transient model simulation

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图 16 考虑热浸效应前后T_t7的对比

Figure 16. Comparison of T_t7 before and after the heat soak was considered

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表 1 涡喷发动机设计点参数

Table 1. Design point specification for the turbojet engine

参数	数值
飞行马赫数	0
高度/m	0
进口空气流量/（kg/s）	31.68
物理转速/（rad/min）	14000
进气道压力损失系数	0.99
压气机压比	12
压气机效率	0.85
燃烧室出口温度/K	1450
燃烧室效率	0.999
燃烧室压力损失系数	0.97
涡轮效率	0.89
轴的机械效率	0.9999
涡轮出口压力损失系数	0.98

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表 2 设计点模型验证

Table 2. Model validation at design point

参数	数值		相对误差/%
参数	GasTurb	TurboWorkX	相对误差/%
T_t3/K	630.4	631.1	0.11
p_t3/kPa	1204	1204	0
T_t4/K	1450	1450	0
p_t4/kPa	1168	1168	0
T_t5/K	1091	1092	0.09
p_t5/kPa	360	360.3	0.08
A₈/m²	0.0742	0.0742	0
推力/kN	26.09	26.11	0.08
耗油率/（kg/（h·kN））	91.33	91.47	0.15
注：表中T_t为总温，p_t为总压，下标数值对应图3中的截面编号。

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表 3 涡喷发动机试车实验的测量参数情况

Table 3. Measurement parameter situation in the running test of the turbojet engine

参数	量符号	传感器类型	测点数
大气压力	p_t0	大气压力传感器	1×1
大气温度	T_t0	T型热电偶	1×1
燃油流量	W_f	科氏流量计/齿轮流量计	2×1
转速	N	线性霍尔元件SS49E	1×1
流量管静压	p_s1	硅压阻	4×1
进气总压	p_t1	硅压阻	4×3
进气总温	p_t1	T型热电偶	4×3
压气机后总压	p_t3	硅压阻	4×1
压气机后总温	T_t3	K型热电偶	4×1
涡轮后总压	p_t7	硅压阻	4×1
涡轮后总温	T_t7	K型热电偶	4×1

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表 4 涡喷发动机稳态工况点数据

Table 4. Data of steady-state operating points for the turbojet engine

序号	W_f	N	p_t3	T_t3	p_t7	T_t7
1	32.4	0.360	116647	356.2	99222	937.9
2	36.5	0.408	123044	353.0	100412	916.2
3	41.7	0.458	131083	362.7	101855	917.8
4	47.0	0.506	139719	373.7	103559	916.0
5	52.4	0.556	150872	385.9	105567	910.7
6	58.2	0.606	163051	400.1	107938	909.7
7	64.3	0.654	176361	415.7	110688	907.8
8	71.1	0.704	193293	432.7	114102	907.9
9	78.7	0.752	211527	451.1	117936	913.3
10	87.8	0.802	232441	472.4	122801	922.3
11	98.8	0.853	256514	494.1	128957	940.0
12	111.5	0.900	282425	517.0	135843	966.8
13	127.7	0.951	312174	541.3	144528	1006.8
14	149.4	1.000	343102	567.0	567.0	1056.6

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表 5 设计点参数优化的上下限

Table 5. Upper and lower limits for the optimization of design point parameters

参数	下限值	上限值
进口空气流量/（kg/s）	1.6	2.3
压气机效率	0.49	0.9
压气机压比	3	4
燃烧室效率	0.8	0.999
燃烧室压损	0.8	1
燃油热值/（kJ/kg）	40900	45400
燃烧室负载系数	1.5	1.7
涡轮效率	0.8	1
轴机械效率	0.98	1
涡轮出口压损	0.95	1
进气道压损	0.99	1

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表 6 稳态修模误差

Table 6. Error of steady-state after model adaptation

方法	参数	平均误差/%	最大误差/%
1	N	10.8	19.9
	p_t3	3.7	7.4
	p_t7	10.2	16.4
	T_t3	2.3	4.5
	T_t7	2.0	4.6
2	N	8.0	20.2
	p_t3	5.7	8.3
	p_t7	9.7	16.4
	T_t3	3.4	17.1
	T_t7	5.5	15.9
3	N	0.8	2.4
	p_t3	1.6	2.2
	p_t7	1.5	2.3
	T_t3	1.1	1.6
	T_t7	1.0	1.8

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表 7 过渡态模型误差

Table 7. Model error at transient state

方法	参数	最大误差/%
1	N	11.8
	p_t3	13.7
	p_t7	5.8
	T_t3	14.0
	T_t7	14.5
2	N	11.4
	p_t3	13.2
	p_t7	5.7
	T_t3	14.2
	T_t7	14.2
3	N	12.8
	p_t3	12.8
	p_t7	6.8
	T_t3	12.9
	T_t7	9.7

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