|Table of Contents|

Drag characteristics of ramjet chanel of combined cycle engine at low speeds(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2022年06期
Page:
44-51
Research Field:
目次
Publishing date:

Info

Title:
Drag characteristics of ramjet chanel of combined cycle engine at low speeds
Author(s):
DENG Shiyu;  JIN Zhiguang;  KE Yuxiang
(College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
Keywords:
combined cycle engine low Mach number drag characteristics analysis variable geometry numerical simulation drag reduction
PACS:
V431-34
DOI:
-
Abstract:
The effect of excess flow on drag characteristics of turbine based combined cycle engine was studied at low speeds, when the working conditions of the turbine channel were not affected.Both momentum theorem and wall force integral method were adopted to analyze the overall forces of an engine.By comparing the schemes of opening and closing ramjet channel, a drag reduction approach by adjusting the ramjet nozzle throat area in cold state was presented.The study indicates that the two analytical methods have consistent results, evaluating the force of engine accurately.The spillage drag is lower when the ramjet channel keeps open than closed.The drag will be further reduced when the high-speed surplus air was decelerated passing through ramjet channel, and the drag disparity between two schemes becomes greater when the incoming Mach number decreases.In addition, there are also significant drag reduction effect by controlling the downstream nozzle throat area and slowing down theair speed in ramjet channel.A maximum drag reduction of 54 was achieved at freestream Mach number 0.8 and 1.0.

References:

[1] 梅东牧,林鹏,王战.吸气式空天飞机对TBCC动力的需求分析[J].燃气涡轮试验与研究,2013,26(6):12-14.
[2] CHOJNACKI K,HAWK C.An assessment of the rocket-based combined cycle propulsion system for earth-to-orbit transportation[C]//29th Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,1993.
[3] 吕翔,何国强,刘佩进.RBCC飞行器爬升段轨迹设计方法[J].航空学报,2010,31(7):1331-1337.
[4] VARVILL R,BOND A.A comparison of propulsion con-cepts for SSTO reusable launchers[J].Journal of the British Interplanetary Society,2003,56:108-117.
[5] OIKE M,KAMIJO K,TANAKA D,et al.LACE for rocket-based combined-cycle[C]//37th Aerospace Sciences Meeting and Exhibit.Reston,Virigina:AIAA,1999.
[6] VARVILL R, BOND A.The SKYLON spaceplane:Progress to realisation[J].JBIS,2008,61:412-418.
[7] 张韬.预冷压缩吸气式发动机系统方案设计与分析[D].长沙:国防科技大学,2017.
[8] TANATUSGU N,SATO T,NARUO Y,et al.Development study on ATREX engine[J].Acta Astronautica,1997,40(2/3/4/5/6/7/8):165-170.
[9] 张蒙正,南向谊,刘典多.预冷空气涡轮火箭组合动力系统原理与实现途径[J].火箭推进,2016,42(1):6-12.
ZHANG M Z,NAN X Y,LIU D D.Principles and realizing ways of combined power system for pre-cooling air turbo rocket[J].Journal of Rocket Propulsion,2016,42(1):6-12.
[10] 张蒙正,刘典多,马海波,等.PATR发动机关键技术与性能提升途径初探[J].推进技术,2018,39(9):1921-1927.
[11] 朱岩,马元,张蒙正.预冷空气涡轮火箭发动机氦循环系统的参数特性[J].航空动力学报,2018,33(8):2016-2024.
[12] SNYDER L,ESCHER D,DEFRANCESCO R,et al.Turbine based combination cycle(TBCC)propulsion subsystem integration[C]//40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2004.
[13] 姚源,陈萱.美国发布SR-72高超声速飞机概念[J].中国航天,2013(12):39-41.
[14] MAMPLATA C,TANG M.Technical approach to turbine-based combined cycle:Facet[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virginia:AIAA,2009.
[15] 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.Reston,Virginia:AIAA,1998.
[16] WEIR L,REDDY D R,RUPP G.Mach 5 inlet CFD and experimental results[C]//25th Joint Propulsion Conference.Reston,Virginia:AIAA,1989.
[17] 全福旭.TBCC组合发动机仿真模型的结构化建模及性能分析[D].哈尔滨:哈尔滨工业大学,2020.
[18] SANDERS B W,WEIR L J.Aerodynamic design of a dual-flow Mach 7 hypersonic inlet system for a turbine-based combined-cycle hypersonic propulsion system[R].2008-215214.
[19] FAN X Q,LI H,JIA D,et al.Experimental investigation on forced boundary-layer transition of axisymmetric inlet and numerical verification[J].Journal of Aircraft,2006,43(5):1544-1549.
[20] 李建平,宋文艳,郑亚明,等.超燃冲压发动机一体化设计及数值模拟[J].航空动力学报,2009,24(4):911-917.
[21] NICOLAI L,CARICHNER G E.Fundamentals of aircraft and airship design(volume I):aircraft design[Z].2010.

Memo

Memo:
-
Last Update: 1900-01-01