TBCC旋流燃烧涡扇模态下的流动特性研究

推进技术 ›› 2019, Vol. 40 ›› Issue (1): 130-139.

TBCC旋流燃烧涡扇模态下的流动特性研究

翟文辉,范育新,陶华,陈玉乾

南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
基金资助:
南京航空航天大学研究生创新基地(实验室)开放基金( kfjj20170206)。

Flow Characteristics of TBCC Swirled Combustion in Turbofan Mode

Jiangsu Province Key Laboratory of Aerospace Power System，College of Energy and Power Engineering， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Jiangsu Province Key Laboratory of Aerospace Power System，College of Energy and Power Engineering， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Jiangsu Province Key Laboratory of Aerospace Power System，College of Energy and Power Engineering， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and Jiangsu Province Key Laboratory of Aerospace Power System，College of Energy and Power Engineering， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为减小整流段和钝体造成的损失，针对涡轮基组合循环发动机( TBCC)燃烧室，基于离心力燃烧加速火焰传播的机理，通过数值模拟方法研究了不同旋流进口位置、旋流角度及其组合方式下的流场特征，以及不同燃油喷射粒径在离心力场下的油雾场分布特性。研究发现:相比于单一位置的旋流进口及旋流角度，利用不同旋流位置及不同旋流角度的组合方式，总压损失虽然有所增大，但切向速度衰减较快；对于不同的燃油喷射粒径， 70μm粒径的油珠相比于 50μm的受到的离心力较大，所需掺混距离缩短，其油雾分布特性更符合燃烧室温度分布要求。

关键词: 涡轮基组合循环发动机；涡扇模态；旋流；超紧凑；离心力燃烧

Abstract: In order to reduce the losses caused by the rectifier section and the bluff body，through the use of the centrifugal force accelerating flame propagation principle，a combustion chamber of a turbine based com. bined cycle engine(TBCC)is designed. The flow field characteristics of different swirl inlet positions，swirlingangles and the combination of both are studied with numerical simulation methods and the fuel particle size influ.ence on the oil field distribution under centrifugal force field is studied. The results show that，compared with the swirling inlet and swirling angle at a single position，the total pressure loss increases with the combination of dif. ferent swirling positions and angles，while the tangential velocity attenuates rapidly. Results of different fuel parti. cles size simulation show that，comparing with 50μm diameter fuel droplets，the mixing distance of 70μm ones is shorter due to the larger centrifugal force they born，and the fuel spray distribution is more in line with the com.bustion chamber temperature distribution requirements.

Key words: Turbine based combined cycle engine；Turbofan mode；Swirl；Super compact；Centrifugal combustion

翟文辉,范育新,陶华,陈玉乾. TBCC旋流燃烧涡扇模态下的流动特性研究[J]. 推进技术, 2019, 40(1): 130-139.

ZHAI Wen-hui,FAN Yu-xin,TAO Hua,CHEN Yu-qian. Flow Characteristics of TBCC Swirled Combustion in Turbofan Mode[J]. Journal of Propulsion Technology, 2019, 40(1): 130-139.

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