射流控制反推力装置流场数值研究

推进技术 ›› 2014, Vol. 35 ›› Issue (9): 1181-1187.

射流控制反推力装置流场数值研究

陈　著¹,单　勇¹,沈锡钢²,张靖周¹,邵万仁²

江苏省航空动力系统重点实验室，南京航空航天大学能源与动力学院，江苏南京 210016;江苏省航空动力系统重点实验室，南京航空航天大学能源与动力学院，江苏南京 210016;沈阳发动机设计研究所，辽宁沈阳 110015;江苏省航空动力系统重点实验室，南京航空航天大学能源与动力学院，江苏南京 210016;沈阳发动机设计研究所，辽宁沈阳 110015

发布日期:2021-08-15
作者简介:陈　著(1990—)，硕士生，研究领域为传热传质。
基金资助:
江苏省自热科学基金(BK20130790)；国家自然科学基金(51306088)。

Numerical Study on Thrust Reverser Controlled with

Jiangsu Province Key Laboratory of Aerospace Power Systems，College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China;Jiangsu Province Key Laboratory of Aerospace Power Systems，College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China;Shenyang Aero-Engine Design and Research Institute，Shenyang 110015，China;Jiangsu Province Key Laboratory of Aerospace Power Systems，College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China;Shenyang Aero-Engine Design and Research Institute，Shenyang 110015，China

Published:2021-08-15

摘要/Abstract

摘要： 针对涵道比为8的涡扇发动机无阻流门叶栅式反推装置，利用CFD技术，计算分析了二次射流孔的位置、角度、孔数以及流量对反推力性能和外涵通道内流场流动特征的影响。计算结果表明:外涵流体与二次射流相互作用后，在二次射流下游产生了一个主涡和副涡，阻碍外涵气体向下游流动；射流孔位置对涡扇发动机的影响不仅体现在反推力效率，而且影响上游风扇后的气体压力不均匀度和背压；二次流射流角度对反推力性能的影响在诸多影响因素中占主导地位，存在一个最佳射流角度；二次流质量流量增加，反推力效率呈增加趋势；二次流入射孔的个数关系到相邻入射气流在周向的覆盖程度，从而影响反推效率；二次流射流位置、角度以及流量对反推性能的影响是相互耦合的，在反推力装置设计时需要综合考虑三者间的相互影响；在研究参数范围内，最佳的射流孔位置范围L=110mm~150mm，最佳射流角度[α]在10°~20°范围内。

关键词: 涡扇发动机；叶栅；反推力装置；数值模拟；二次流

Abstract: For the turbofan engine with bypass ratio 8，the CFD simulations were performed to analyze the effects of the position，inject angle，hole numbers and mass flow rate of the secondary jet flow on the performances of the blocker-less thrust reverser and flow characteristics of bypass flow. The numerical results show that the bypass flow interacts with the secondary jet flow to produce two vortexes located on the downstream of the secondary jet . The vortex block the passage of bypass flow and turn the flow direction of the bypass flow. The position of secondary flow relates to the thrust reverser efficiency and the pressure distribution on the outlet of the engine fan. The inject angle of the secondary flow has a dominant effect on thrust reverser performance. The jet angle is also a determining factor for the thrust reverser. The thrust reverser efficiency improves as the increase of the secondary jet flow rate. The numbers of the jet holes relate to the coverage area of the secondary flow circumferentially. The effects of jet hole position，angle and jet flow rate are connected to consider on the design of the block-less thrust reverser. In this paper，the jet hole position is recommend ranging from 110mm to 150mm，and the inject angle is between 10° to 20°.

Key words: Turbofan engine；Cascade；Thrust reverser；Numerical simulation；Secondary jet

陈　著,单　勇,沈锡钢,张靖周,邵万仁. 射流控制反推力装置流场数值研究[J]. 推进技术, 2014, 35(9): 1181-1187.

CHEN Zhu¹,SHAN Yong¹,SHEN Xi-gang²,ZHANG Jing-zhou¹,SHAO Wan-ren². Numerical Study on Thrust Reverser Controlled with[J]. Journal of Propulsion Technology, 2014, 35(9): 1181-1187.

参考文献

[1] Colley R H,Sutton J M O.Thrust Reversers for Civil STOL Aircraft[R].SAE 71-730358 .
[2] 刘大响.进排气系统/航空发动机设计手册(第7册)[M].北京: 航空工业出版社,2000.
[3] 靳宝林,邢伟红,刘殿春.飞机/发动机推进系统反推力装置[J].航空发动机,2004,30(4):49-52.
[4] Yetter J A.Why Do Airlines Want and Use Thrust Reversers?[R].NASA TM 95-109158.
[5] Hall S,Cooper R,Raghunathan S.Fluidic Flow Control in a Natural Blockage Thrust Reverser[R].AIAA 2006-3513.
[6] Gilbert B,Marconit F.Innovative Concept For Cascade Thrust Reverser Without Blocker Doors[R].AIAA 97-0823.
[7] Marconi F.Computational Fluid Dynamics Support of the Development of a Blockerless Engine Thrust Reverser Concept[R].AIAA 97-3151.
[8] Fernando Oliveira de Andrade,Sandro Barros Ferreira,Luís Fernando Figueira da Silva.Study of the Influence of Aircraft Geometry on the Computed Flowfield During Thrust Reversers Operation[R].AIAA 2006-3673.
[9] 王占学,傅鹏哲,刘春阳.新型无阻流板反推装置流场结构和影响参数研究[J].航空发动机,2010,36(2):1-5.
[10] 陈著,单勇,张靖周,等.无阻流门叶栅式反推力装置数值研究[J].航空计算技术,2012,42(6): 50-53.
[11] Nobel T P,Wooden P A,Arledge R G.Experimental Thrust Reverser Design with Computational Analysis[R].AIAA 94-0021.
[12] Yao H,Cooper R K,Benard E,et al.The Effect of the Porous Diverter Fairing on the Aerodynamic Performance of Natural Blockage Thrust Reverser[R].AIAA 2004-1239.
[13] 邓明.航空燃气涡轮发动机原理与构造[M].北京: 国防工业出版社,2008.
[14] 廉筱纯,吴虎.航空发动机原理[M].西安: 西北工业大学出版社,2006.
[15] 刘春阳,王占学,付鹏哲.大涵道比涡扇发动机射流控制反推模型数值模拟[J].航空动力学报,2010,25(8) : 1811-1817.(编辑:史亚红)收稿日期:2013-09-24；修订日期:2013-11-15。基金项目:江苏省自热科学基金(BK20130790)；国家自然科学基金(51306088)。作者简介:陈著(1990—),硕士生,研究领域为传热传质。E-mail:716092606@qq.com