ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Design and performance analysis of a three-dimensional TBCC exhaust system
Received date: 2024-08-27
Revised date: 2024-09-13
Accepted date: 2024-10-15
Online published: 2024-10-29
Supported by
Fundamental Research Funds for the Central Universities(NS2023008);Natural Science Foundation of Jiangsu Province(BK20241367);Project 1912(2019-JCJQ-DA-001-072);National Natural Science Foundation of China(12332018)
Based on the axisymmetric flowfield with optimal thrust under geometric constraints， a circular-to rectangular three-dimensional single expansion ramp nozzle is designed by using the streamline tracing method， and trimming the configuration of nozzle to improve the aerodynamic performance and reduce the weight of the nozzle. On this basis， the adjustment programme for changing geometry of the turbojet flowpath is achieved by using the rotating ramp rotation around the ramp endpoint to complete the design of the exhaust system. Subsequently， the wall pressure distribution and schlieren image of the exhaust system are obtained through cold flow experiments， and the detailed flow field characteristics and performance parameters are obtained through numerical simulations. The results show that the schlieren image and pressure distributions of the wall under each operating condition are in good agreement with the numerical simulation results； when the turbojet works alone， the structure of the exhaust jet is relatively simple， and there will be a shock train structure under the low Nozzle Pressure Ratio （NPR）. In parallel operation， the two flowpath interfere with each other； in separate operation of ramjet， the airflow expands smoothly in the three-dimensional flow path. The thrust performance of the exhaust system deteriorates slightly in the turbine and ramjet co-operating condition， but the thrust coefficient is above 0.924 in the whole working envelope， and the thrust performance changes smoothly. This study provides a new effective solution for the TBCC exhaust system.
Haipeng DING , Zheng LYU , Ke TIAN , Tao YE , Kuangshi CHEN , Jinglei XU . Design and performance analysis of a three-dimensional TBCC exhaust system[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(15) : 131104 -131104 . DOI: 10.7527/S1000-6893.2024.31104
| [1] | 徐惊雷. 超燃冲压及TBCC组合循环发动机尾喷管设计方法研究进展［J］. 推进技术， 2018， 39（10）： 2236-2251. |
| XU J L. Research progress of nozzle design method for scramjet and turbine based combined cycle［J］. Journal of Propulsion Technology， 2018， 39（10）： 2236-2251 （in Chinese）. | |
| [2] | 左林玄， 张辰琳， 王霄， 等. 高超声速飞机动力需求探讨［J］. 航空学报， 2021， 42（8）： 525798. |
| ZUO L X， ZHANG C L， WANG X， et al. Requirement of hypersonic aircraft power［J］. Acta Aeronautica et Astronautica Sinica， 2021， 42（8）： 525798 （in Chinese）. | |
| [3] | 林鹏， 庄福建， 曲林锋， 等. 高超声速飞机尾喷管设计-制造与验证技术发展综述［J］. 航空学报， 2022， 43（6）： 526160. |
| LIN P， ZHUANG F J， QU L F， et al. Technological development in hypersonic nozzle design， manufacture and validation： A review［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（6）： 526160 （in Chinese）. | |
| [4] | 马松， 林鹏， 左林玄， 等. 并联TBCC动力对高超声速飞行器性能的影响［J］. 国防科技大学学报， 2019， 41（2）： 1-7. |
| MA S， LIN P， ZUO L X， et al. Influence of over-under TBCC on the performance of hypersonic aircraft［J］. Journal of National University of Defense Technology， 2019， 41（2）： 1-7 （in Chinese）. | |
| [5] | SIEBENHAAR A， BOGAR T. Integration and vehicle performance assessment of the aerojet “TriJet” combined-cycle engine?［C］?∥16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. Reston： AIAA， 2009. |
| [6] | 莫建伟. TBCC排气系统设计方法及流场特性研究［D］. 南京： 南京航空航天大学， 2015： 107-131. |
| MO JIANWEI. Research on design method and flow characteristics of TBCC exhaust system?［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2015： 107-131 （in Chinese）. | |
| [7] | MO J W， XU J L， ZHANG L H， et al. The experimental and numerical study of the over-under TBCC exhaust system?［C］?∥17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston： AIAA， 2011： 2234. |
| [8] | 牛彦沣. 并联式 TBCC 排气系统设计方法及性能研究［D］. 南京： 南京航空航天大学， 2016： 15-28. |
| NIU YANFENG. Research on design and performance study of over-under TBCC exhaust system flow structure［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2016： 15-28 （in Chinese）. | |
| [9] | 牛彦沣， 徐惊雷， 许保成， 等. 并联TBCC排气系统流场结构数值模拟及实验研究［J］. 推进技术， 2017， 38（12）： 2686-2691. |
| NIU Y F， XU J L， XU B C， et al. Numerical and experimental study of over-under TBCC exhaust system flow structure［J］. Journal of Propulsion Technology， 2017， 38（12）： 2686-2691 （in Chinese）. | |
| [10] | XU B C， XU J L， WANG X， et al. Flowfield and performance analysis of a three-dimensional TBCC exhaust nozzle［J］. Journal of Engineering for Gas Turbines and Power， 2017， 139（11）： 112602. |
| [11] | 花文达， 徐惊雷. 三维并联式TBCC发动机排气系统设计与实验［J］. 航空动力学报， 2018， 33（9）： 2268-2277. |
| HUA W D， XU J L. Design approach and experiment of three-dimensional over/under TBCC exhaust system［J］. Journal of Aerospace Power， 2018， 33（9）： 2268-2277 （in Chinese）. | |
| [12] | 吕郑. Ma0-6并联式TBCC排气系统的设计及性能研究［D］. 南京： 南京航空航天大学， 2019： 38-149. |
| LVZ. Design and performance study of Ma0-6 parallel TBCC exhaust system［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2019： 38-149 （in Chinese）. | |
| [13] | OGAWA H， BOYCE R R. Nozzle design optimization for axisymmetric scramjets by using surrogate-assisted evolutionary algorithms?［J］. Journal of Propulsion and Power， 2012， 28（6）： 1324-1338. |
| [14] | TANIMIZU K， MEE D J， STALKER R J， et al. Nozzle design study for a quasi-axisymmetric scramjet-powered vehicle at Mach 7.9 flight conditions［J］. Shock Waves， 2013， 23（5）： 453-460. |
| [15] | 魏仁敏， 杜刚， 金捷. 基于Kriging代理模型的单边膨胀喷管尾缘切角优化［J］. 航空动力学报， 2018， 33（4）： 874-881. |
| WEI R M， DU G， JIN J. Optimization of trailing edge angles of single expansion ramp nozzle based on Kriging method［J］. Journal of Aerospace Power， 2018， 33（4）： 874-881 （in Chinese）. | |
| [16] | 卢鑫， 岳连捷， 肖雅彬， 等. 超燃冲压发动机三维变截面尾喷管设计［C］∥第三届高超声速科技学术会议会议文集. 北京： 中国力学学会， 2010： 254-259. |
| LU X， YUE L J， XIAO Y B， et al. Design of three-dimensional section controllable scramjet nozzle?［C］?∥Proceedings of the 3rd International Conference on Hypersonic Technology. Beijing： Chinese Society of Theoretical and Applied Mechanics， 2010： 254-259. | |
| [17] | 卢鑫， 岳连捷， 肖雅彬， 等. 超燃冲压发动机尾喷管流线追踪设计［J］. 推进技术， 2011， 32（1）： 91-96. |
| LU X， YUE L J， XIAO Y B， et al. Design of scramjet nozzle based on streamline tracing technique［J］. Journal of Propulsion Technology， 2011， 32（1）： 91-96 （in Chinese）. | |
| [18] | MO J W， XU J L， GU R， et al. Design of an asymmetric scramjet nozzle with circular to rectangular shape transition［J］. Journal of Propulsion and Power， 2014， 30（3）： 812-819. |
| [19] | MO J W， XU J L， GU R， et al. Design of a circular to rectangular transition scramjet nozzle with streamline tracing technique?［C］?∥18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference. Reston： AIAA， 2012. |
| [20] | LV Z， XU J L， MO J W. Design and analysis on three-dimensional scramjet nozzles with shape transition［J］. Aerospace Science and Technology， 2017， 71： 189-200. |
/
| 〈 |
|
〉 |
CJA