Design concept and aerodynamic characteristics of XTER TBCC inlet

CAI Zejun; HU Zhancang; YU Lianchen; HONG Tangbao; ZHU Chengxiang; YOU Yancheng

doi:10.7638/kqdlxxb-2021.0393

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Design concept and aerodynamic characteristics of XTER TBCC inlet

更新时间：2026-05-28

- Design concept and aerodynamic characteristics of XTER TBCC inlet
- Vol. 40, Issue 1, Pages: 218-231(2022)
- 作者机构：
  
  厦门大学航空航天学院,厦门,361000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0393
  CLC： V236
- Published：2022
- 稿件说明：
移动端阅览
蔡泽君, 胡占仓, 余联郴, 等. XTER内收缩组合进气道设计理念及气动特性[J]. 空气动力学学报, 2022, 40(1): 218−231.

CAI Zejun, HU Zhancang, YU Lianchen, et al. Design concept and aerodynamic characteristics of XTER TBCC inlet[J]. 2022, 40(1): 218-231.
蔡泽君, 胡占仓, 余联郴, 等. XTER内收缩组合进气道设计理念及气动特性[J]. 空气动力学学报, 2022, 40(1): 218−231. DOI： 10.7638/kqdlxxb-2021.0393

CAI Zejun, HU Zhancang, YU Lianchen, et al. Design concept and aerodynamic characteristics of XTER TBCC inlet[J]. 2022, 40(1): 218-231. DOI： 10.7638/kqdlxxb-2021.0393.

摘要

组合循环发动机的进气道特性是决定整体方案可行性的关键因素之一。本文针对XTER（Xiamen Turbine Ejector Ramjet）组合动力总体需求，详细梳理了XTER内收缩组合进气道的设计理念及设计要素，在此基础上重点分析了该组合进气道的流动结构及特性规律。结果表明，XTER组合进气道各设计要素及设计约束相互耦合，分流调节机构是组合进气道设计的核心，其设计难度高且使设计要素的相互制约问题更为突出。在全速域马赫数0～6范围内，XTER内收缩组合进气道的流动结构差异显著，但总流量系数均维持在0.75以上，有效保障了组合发动机的流量捕获，且分流调节机构能够实现模态转换过程中流量的平稳过渡。在马赫数2.5涡轮-引射亚燃模态转换过程中，引射亚燃通道及超燃通道总压恢复均稳定上升，在模态转换完成时总压恢复均接近或超过0.85。在区间马赫数3～4.5的引射亚燃-超燃模态转换过程中，进气道总流量系数由0.81提升至0.90，引射亚燃通道在前62.5%的进程中保持较高的总压恢复性能，表明该通道在前半程的模态转换过程中仍具有较强的工作能力。综合来看，XTER内收缩组合进气道的气动特性能够满足动力方案总体需求，全速域范围内流量系数变化缓和，模态转换过程中通道性能过渡平稳，具备宽速域连续正常工作能力。

Abstract

The performance of inlets is critical to combined cycle engines. Aiming at the overall demand of Xiamen Turbine Ejector Ramjet (XTER)

the design concept and design elements of the inward-turning Turbine Based Combined Cycle (TBCC) inlet for XTER are reviewed in detail. On this basis

flow structures and characteristics of the inlet are analyzed. Results show that either design elements or design constraints of the XTER inlet are coupled with each other

and the mass modulation mechanism is the core element

which is

however

difficult to design and makes the mutual restriction among design elements more complicated. Flow structures in the XTER inlet vary significantly with the increase of Mach number from 0 to 6. Nevertheless

the total mass flow rate remaines above 0.75

which meets the mass flow demand. The mass distribution mechanism also helps the flow mass varies smoothly during mode transitions. During the turbine-to-ejector transition at Mach 2.5

the total-pressure recovery coefficients of the ejector and scramjet increase steadily. Once the transition ends

the total-pressure recovery coefficient is close to or above 0.85. As to the ejector-to-scramjet transition at Mach 3-4.5

the mass flow rate of the inlet increases from 0.81 to 0.90. Moreover

the ejector tunnel maintains a high total-pressure recovery coefficient in the first 62.5% process

indicating that this tunnel still performs properly in the first half of mode transition process. Taken together

the XTER inlet it is capable of continuous normal operation in a wide speed range since its aerodynamic characteristics meet the demand of power system

i.e.

the mass flow rate varies moderately in the full speed range and the tunnel performance transits smoothly in the mode transition process.

关键词

Keywords

references

李茜, 崔艷林. 2020年高超声速推进技术发展综述[J]. 航空动力, 2021(2): 20-23.

李思冶, 查柏林, 王金金, 等. 美俄高超声速武器发展研究综述[J]. 飞航导弹, 2021(3): 31-37.

DING F, LIU J, SHEN C B, et al. An overview of waverider design concept in airframe-inlet integration methodology for air-breathing hypersonic vehicles[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(6): 16-26. (in Chinese)

YIN Z Y, YU D K, XU X. Development trend and technical challenge of high Mach number turbine based propulsion system[J]. Aeroengine, 2021, 47(4): 1-7. (in Chinese)

李文杰, 林旭斌. NASA启动高超声速飞机研究[J]. 飞航导弹, 2021(5): 9-12.

MARSHALL A, GUPTA A, LAVELLE T, et al. Critical issues in TBCC modeling[C]//40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Fort Lauderdale, Florida. Reston, Virigina: AIAA, 2004. doi: 10.2514/6.2004-3827

BASE M . Reusable launch vehicles and space operations[R]. Occasional Paper, csat12, 2000.

HUI Y, JUN M, MAN Y J, et al. Numerical simulation of variable-geometry inlet for TRRE combined cycle engine[C]// 21st AIAA International Space Planes and Hypersonics Technologies Conference, Xiamen, China. Reston, Virginia: AIAA, 2017 doi: 10.2514/6.2017-2437

凌文辉,侯金丽,韦宝禧,冮强.空天组合动力技术挑战及解决途径的思考[J].推进技术,2018,39(10):2171-2176. doi:10.13675/j.cnki.tjjs.2018.10.002

WEI B X, LING W H, GANG Q, et al. Analysis of key technologies and propulsion performance research of TRRE engine[J]. Journal of Propulsion Technology, 2017, 38(2): 298-305. (in Chinese)

ZHANG M Z, LIU D D, MA H B, et al. Preliminary analysis on critical technology and performance improvement of PATR engine[J]. Journal of Propulsion Technology, 2018, 39(9): 1921-1927. (in Chinese)

HYDE E H. Marquardt's Mach 4.5 supercharged ejector ramjet (SERJ) high-performance aircraft engine project: unfulfilled aspirations ca. 1970[J]. AIAA, 2000.

MERLIN P. Design and development of the blackbird: challenges and lessons learned[C]//47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition, Orlando, Florida. Reston, Virigina: AIAA, 2009. doi: 10.2514/6.2009-1522

MCCLINTON C R, REUBUSH D E, SITZ J, et al. Hyper-X program status[C ] //39th Aerospace Sciences Meeting and Exhibit, Reno, NV, U. S. A. , AIAA 2001-1910, 2001. https://ntrs.nasa.gov/api/citations/20010071335/downloads/20010071335.pdf doi: 10.2514/6.2001-828

FERNANDEZ R, REDDY D, BENSON T, et al. Design issues for turbine-based and rocket-based combined cycle propulsion system inlets[C]//34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, C leveland, OH, USA. Reston, Virigina: AIAA, 1998. AIAA-98-3774. doi: 10.2514/6.1998-3774

WEIR L, REDDY D R, RUPP G. Mach 5 inlet CFD and experimental results[C ] //25th Joint Propulsion Conference, Monterey, CA, USA. Reston, Virigina: AIAA, 1989. AIAA 89-2355. NASA-TM-102317. https://ntrs.nasa.gov/api/citations/19890018299/downloads/19890018299.pdf doi: 10.2514/6.1989-2355

HE M F, LI X K, YIN C, et al. Areodynamic design and analysis of a TBCC inlet based on inward-turning inlet[J]. Aircraft Design, 2021, 41(4): 56-64, 73. (in Chinese)

LIU H X, LIANG C H, SUN M X. Progress and analysis of US supersonic turbine based combined cycle engine[J]. Aeroengine, 2017, 43(4): 96-102. (in Chinese)

SPRAVKA J J, JORRIS T R. Current hypersonic and space vehicle flight test and instrumentation[R]. Defense Technical Information Center, 2015. doi: 10.21236/ada619521

MAGEE T, FUGAL S, FINK L, et al. Boeing N+2 supersonic experimental validation phase II program[C]//32nd AIAA Applied Aerodynamics Conference, Atlanta, GA. Reston, Virginia: AIAA, 2014. doi: 10.2514/6.2014-2137

KOTHARI A, TARPLEY C, MCLAUGHLIN T, et al. Hypersonic vehicle design using inward turning flow fields[C]//32nd Joint Propulsion Conference and Exhibit, Lake Buena Vista, FL. Reston, Virginia: AIAA, 1996 doi: 10.2514/6.1996-2552

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, Bremen, Germany. Reston, Virigina: AIAA, 2009. doi: 10.2514/6.2009-7420

MIN H, SUN B, LI J X, et al. Investigation on interference characteristics among channels of a over-under inward turning inlet[J]. Journal of Propulsion Technology, 2018, 39(12): 2695-2702. (in Chinese)

TIAN F C. Investigation of the unstart state of inward turning hypersonic inlet[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2013 (in Chinese).

张航, 谭慧俊, 邵文清, 等. 不同前缘钝化半径对内转进气道性能特性影响研究[C]//第八届全国高超声速科技学术会议论文集, 哈尔滨, 2015: 25.

邬凤林. 宽范围可调内转进气道设计方法研究[D]. 南京: 南京理工大学, 2017.

ZHU C X, ZHANG H F, HU Z C, et al. Analysis on the low speed performance of an inward-turning multiduct inlet for turbine-based combined cycle engines[J]. International Journal of Aerospace Engineering, 2019, 2019: 1-10. DOI:10.1155/2019/6728387

HU Z C, CAI Z J, WANG T Y, et al. Analysis of effects of mode transition type on performance of mode transition for 3D inward-turning combined inlet[J]. Journal of Propulsion Technology, 2020, 41(12): 2670-2680. (in Chinese)

KONG F. Mass flow distribution design and performance analysis of multi-duct combine cycle inlet[D]. Xiamen: Xiamen University, 2019 (in Chinese).

LI P, CHEN W C, GUO W. “CST” parametric geometry representations for wave riders[C]//2010 Asia-Pacific International Symposium on Aerospace Technology, 2010: 35-38.

REINARTZ B U, HERRMANN C D, BALLMANN J, et al. Aerodynamic performance analysis of a hypersonic inlet isolator using computation and experiment[J]. Journal of Propulsion and Power, 2003, 19(5): 868-875. DOI:10.2514/2.6177

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Analysis of damping and cross dynamic derivative characteristics for a quasi-HyTRV lifting body

Research on the characteristics of water droplets impacting moving superhydrophobic surfaces and its regulation

Noise prediction and reduction methods for LAGOON landing gear based on Lattice Boltzmann method

Installation effects on propeller tone noise

Dynamic ablation morphology measurement of thermal protection materials using structured light vision

Related Author

No data

Related Institution

No data

AI问答

⁰