轴对称分开排气喷管改混合排气喷管设计方法

王亚骏; 吉洪湖; 陈宝延; 李俊萍

doi:10.13224/j.cnki.jasp.2017.07.015

轴对称分开排气喷管改混合排气喷管设计方法

doi: 10.13224/j.cnki.jasp.2017.07.015

1.
南京航空航天大学能源与动力学院，南京 210016
2.
中国航天科工集团公司北京动力机械研究所，北京 100074

基金项目: 中央高校基本科研业务费(NZ2016103)

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出版历程
- 收稿日期: 2015-10-29
- 刊出日期: 2017-07-28

Modified verison design method of axisymmetric unmixed-flow nozzle to mixed-flow nozzle

摘要

摘要: 为将涡扇发动机轴对称分开排气喷管改型设计为混合排气喷管以获取混合推力增益且改变其红外辐射(IR)特征，提出了一套基于CFD数值计算评估的轴对称分开排气喷管改型设计方法。研究结果包括：①提出了内、外涵气流不同程度掺混时推力的估算方法，估算值与真实值的误差在所研究参数范围内不超过0.005；②分析了内、外涵气流掺混对改型设计的影响，喷管外涵气流与内涵气流的总压比在0.8~1.5之间且掺混度大于0.1时混合排气最有可能产生推力增益，且掺混越好，增益越高；③轴对称分开排气喷管改型设计为带环形混合器的混合排气喷管后，推力系数增加0.0087~0.0126，而采用波瓣混合器时喷管的推力系数则增加0.0289；④相比于分开排气，混合排气喷管在0°~15°方向上的红外辐射强度有所增加，但在其他所有方位角上均大幅下降，最大降幅为77.5%。
- 涡扇发动机 /
- 分开排气喷管 /
- 混合排气喷管 /
- 改型设计 /
- 推力增益 /
- 红外辐射
Abstract: In order to achieve the increased gross thrust and different spatial distributions of infrared radiation (IR) characteristics, a modified version design method of axisymmetric unmixed-flow nozzle based on CFD numerical simulation was established to change it into mixed-flow nozzle. Results indicated that: (1) An estimating method of nozzle thrust was proposed when the core and fan flow were mixed at various degrees, the error between the estimated value and the true one was basically less than 0.005 in the parameter scope. (2) Influence on modified version design of the core and fan flow condition was analyzed, increased thrust may be achieved when the total-pressure ratio of fan flow to core flow was between 0.8 and 1.5, and the mixing degree should be larger than 0.1. (3) Increased gross thrust was achieved after the modified version design, the thrust coefficient of mixed-flow nozzles with confluent mixer increased by 0.0087-0.0126 in comparison with the unmixed-flow nozzle; when lobed mixer was adopted, the thrust coefficient increased by 0.0289. (4) The integral IR intensity of mixed-flow nozzle increased in the azimuth angles of 0°-15°, but it significantly decreased in all the other azimuth angles, the largest decline was 77.5%.
- turbofan engine /
- unmixed-flow nozzle /
- mixed-flow nozzle /
- modified version design /
- increased gross thrust /
- infrared radiation

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参考文献(17)

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