分开排气系统特性校准试验研究

李秋锋; 李密; 高翔; 王定奇

doi:10.11729/syltlx20220056

分开排气系统特性校准试验研究

doi: 10.11729/syltlx20220056

中国飞行试验研究院，西安　710089

基金项目: ××基金（6141B05110201）

详细信息

作者简介:
李秋锋：（1989—），男，陕西旬邑人，硕士，工程师。研究方向：动力装置性能特性试飞技术。通信地址：陕西省西安市阎良区凌云路5号（710089）。E-mail：liqiufeng1989@126.com

通讯作者:
E-mail：liqiufeng1989@126.com

中图分类号: V211.6
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- 文章访问数: 46
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- 被引次数: 0
出版历程
- 收稿日期: 2022-06-27
- 修回日期: 2022-10-12
- 录用日期: 2022-10-19
- 网络出版日期: 2022-12-06

Experimental study on characteristic calibration of separated exhaust system

Chinese Flight Test Establishment, Xi’an　710089, China

摘要

摘要: 飞行试验时，采用燃气发生器法间接获取航空发动机飞行推力。为提高飞行推力计算精度，需准确获取航空发动机排气系统特性。采用某大涵道比分开排气系统缩比模型开展了实验室校准箱吹风试验及数值仿真研究，结果表明：采用实验室校准箱吹风试验、数值仿真两种方法获取的单独内涵喷管特性趋势一致、数值接近，最大内涵喷管压比为1.44时，喷管流量和推力偏差分别为0.73%、0.18%；两种方法获取的内、外涵分开排气系统特性趋势一致、数值接近，最大外涵喷管压比为1.46时，喷管流量和推力偏差分别为0.64%、0.18%；对大涵道比分开排气系统物理模型与几何模型进行合理简化后，两种方法获取的分开排气系统特性偏差满足工程精度要求。
- 排气系统 /
- 喷管特性 /
- 校准 /
- 大涵道比
Abstract: In flight testing, the aeroengine flight thrust is indirectly obtained by the gas generator method. In order to improve the calculation accuracy of the flight thrust, it is necessary to accurately obtain the characteristics of the exhaust system. The laboratory calibration test and numerical simulation research were carried out by using the large bypass ratio separated exhaust system scale model. The results show that: the core nozzle characteristics obtained by the two methods are consistent, and the values are close. When the maximum core nozzle pressure ratio is 1.44, the deviations of the mass flow and the thrust are 0.73% and 0.18%, respectively; the characteristics of the separated exhaust system obtained by the two methods have the same trend and close values. When the max bypass nozzle pressure ratio equals 1.46, the deviations of the mass flow and the thrust are 0.64% and 0.18%, respectively; when the physical model and geometric model of the large bypass ratio separated exhaust system are reasonably simplified, the characteristic deviations of the separated exhaust system obtained by the two methods are in good agreement.
- exhaust system /
- nozzle characteristic /
- calibration /
- large bypass ratio

HTML全文

图 1 翼吊式气动布局示意图

Figure 1. Schematic diagram of pneumatic layout of wing crane

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图 2 分开排气系统示意图

Figure 2. Schematic of separated exhaust system

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图 3 分开排气系统试验模型剖面图

Figure 3. Separated exhaust system test model

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图 4 数值模拟采用的简化几何模型

Figure 4. Simplified geometric model for numerical simulation of test model

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图 5 校准箱试验设备

Figure 5. Calibration box test equipment

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图 6 试验模型及附属结构示意图

Figure 6. Schematic of test model and auxiliary structure

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图 7 计算域核心区网格分布

Figure 7. Grids in the core of computing domain

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图 8 外涵喷管模拟模型网格设计

Figure 8. Grids of simulation model for bypass nozzle

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图 9 内涵喷管模拟模型网格设计

Figure 9. Grids of simulation model for core nozzle

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图 10 单独内涵喷管流量对比

Figure 10. Mass flow of single core nozzle

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图 11 单独内涵喷管推力对比

Figure 11. Thrust of single core nozzle

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图 12 内外涵喷管总流量对比

Figure 12. Mass flow of separated exhaust system

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图 13 内外涵喷管总推力对比

Figure 13. Thrust of separated exhaust system

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图 14 数值模拟的喷管轴向截面速度云图

Figure 14. Velocity contour for numerical simulation of nozzle axial section

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图 15 数值模拟的喷管特征截面速度云图

Figure 15. Velocity contour for numerical simulation of nozzle characteristic section

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L	流向特征尺寸
D	截面特征尺寸
NPR_cr	喷管临界压比
NPR	喷管压比
NPR₉	内涵喷管压比
NPR₁₉	外涵喷管压比
C_d	喷管流量系数
C_fg	喷管推力系数
C_fg9	内涵喷管推力系数
C_fg19	外涵喷管推力系数
F_G	推力/内外涵喷管总推力
F_G9	内涵喷管推力
F_G19	外涵喷管推力
F_{G, act}	内外涵喷管实际总推力
F_{G9, act}	内涵喷管实际推力
F_{G9, id, non}	内涵喷管无量纲理想推力
F_{G9, id}	内涵喷管理想推力
F_{G19, id}	外涵喷管理想推力
F_id	内外涵喷管理想总推力
F_{act, exp}	内外涵实际总推力（校准试验）
F_{act, cfd}	内外涵实际总推力（数值模拟）
ΔF_act	F_{act, cfd}与F_{act, exp}之间的偏差
W	流量
W_id	内外涵喷管理想总流量
W_{9, act}	内涵喷管实际流量
W_{19, act}	外涵喷管实际流量
W_{act, exp}	内外涵实际总流量（校准试验）
W_{act, cfd}	内外涵实际总流量（数值模拟）
ΔW_act	W_{act, cfd}与W_{act, exp}之间的偏差
W₉	内涵喷管流量
V₉	喷管出口速度
A₉	内涵喷管出口面积
p_s0	环境压力
p_s9	内涵喷管出口静压
p_t9	内涵喷管出口总压
p_t19	外涵喷管出口总压
T_t9	内涵喷管出口总温
k	绝热指数
S	系统偏差
B	固定偏差
t	测量值或计算结果
j	t的影响因素的总数
x_i	t的第i个影响因素
u_i	第i个因素对t的不确定度
U_t	t的不确定度
c_i	t对第i个因素的敏感系数

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表 1 试验传感器采集精度

Table 1. Sensor precision

传感器	精度
压力传感器	±0.1%
温度传感器	±0.5 K
流量计	±0.05%
六分量测力天平	±0.03%

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表 2 单独内涵喷管试验主要状态参数

Table 2. The core nozzle test parameter

NPR₉	p_t9 /kPa	T_t9 /K	W_{9, act} /（kg·s⁻¹）
1.08	107.7	299.3	0.202
1.10	109.4	298.4	0.226
1.12	111.4	298.4	0.259
1.14	113.0	298.4	0.282
1.16	115.2	298.4	0.307
1.19	118.5	298.5	0.334
1.23	122.3	298.4	0.357
1.28	127.6	298.2	0.379
1.37	135.9	298.3	0.408
1.44	142.9	298.2	0.431

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表 3 内外涵喷管试验主要状态参数

Table 3. The separated exhaust system test parameter

NPR₁₉	NPR₉	p_t19 /kPa	p_t9 /kPa	T_t9 /K	W_{9, act} /（kg·s⁻¹）	W_{19, act}/（kg·s⁻¹）
1.02	1.004	100.6	99.2	274.9	0.031	0.350
1.07	1.015	105.5	100.3	276.6	0.065	0.662
1.14	1.040	112.4	102.8	278.3	0.109	0.915
1.22	1.079	120.1	106.6	280.2	0.157	1.131
1.29	1.113	127.7	109.9	281.9	0.198	1.321
1.37	1.140	135.8	112.6	283.8	0.230	1.509
1.46	1.193	143.8	117.8	285.6	0.269	1.670

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