| 张瑞霞，许 羚，巩亚南，夏子龙.单环调节轴对称收扩喷管全包线推力特性数值分析[J].航空发动机,2024,50(4):82-87 |
| 单环调节轴对称收扩喷管全包线推力特性数值分析 |
| Numerical Analysis of Full-envelope Thrust Characteristics of Axisymmetric Convergent-divergentNozzle with Single Actuating Ring |
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| DOI： |
| 中文关键词: 单环调节 收扩喷管 推力特性 落压比 面积比 快速分析程序 |
| 英文关键词:single actuating ring convergent-divergent nozzle thrust characteristics pressure drop ratio area ratio fast analysis
program |
| 基金项目:国家级研究项目资助 |
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| 中文摘要: |
| 为了研究单环调节轴对称收扩喷管的全包线推力系数变化规律，采用经模型试验验证的数值仿真方法，对该类型喷管
推力系数的影响因素、面积比设计方法和全包线推力特性开展数值分析。结果表明：在非加力状态下，喷管常用落压比为3～4，
处于低落压比状态，喷管推力系数在面积比为1.1～1.2时较优；在加力状态下，喷管常用落压比为4～8，推力系数在面积比为1.3
～1.5时较优。基于包线内结构可达目标，开展推力特性全局优化，优化后在非加力状态下，喷管推力系数为0.959～0.992；在加力
状态下，喷管推力系数为0.956～0.993；随着飞行高度的增加，包线内喷管实际使用落压比区间逐渐右移，推力系数先增大后减
小。编制了单环调节轴对称收扩喷管推力特性的快速分析程序，可实现全包线推力性能点群的高效预估。 |
| 英文摘要: |
| In order to study the variation law of the full-envelope thrust coefficient of an axisymmetric convergent-divergent nozzle
with single actuating ring， numerical simulation methods verified by model tests were used to conduct numerical analysis on the influenc?
ing factors of thrust characteristics， the area ratio design method， and the full-envelope thrust characteristics of this type of nozzle. The
results show that， under non-afterburning states， the frequently used nozzle pressure drop ratio is 3 to 4， which is a low pressure ratio
state， the nozzle thrust coefficient is better when the area ratio is 1.1 to 1.2； under afterburning states， the frequently used nozzle pressure
drop ratio is 4 to 8， the nozzle thrust coefficient is better when the area ratio is 1.3 to 1.5. Based on the objective of structural attainable
within the flight envelope， global optimization of thrust characteristics was carried out. After the optimization， under the non-afterburning
states， the nozzle thrust coefficient ranges from 0.959 to 0.992， under afterburner states， the nozzle thrust coefficient ranges from 0.956 to
0.993. With the increase of flight altitude， the actual nozzle pressure ratio within the envelope moves to the right gradually， and the thrust
coefficient first increases and then decreases. A fast analysis program of thrust characteristics of axisymmetric convergent-divergent
nozzles with single actuating rings was established， which can effectively predict full-envelope thrust performance point groups. |
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