|Table of Contents|

Research progresses on turbulent mixing and combustion for air-turbo-rocket engine(PDF)

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

Issue:
2011年06期
Page:
14-19
Research Field:
专论与综述
Publishing date:

Info

Title:
Research progresses on turbulent mixing and combustion for air-turbo-rocket engine
Author(s):
LI Wen-long;  LI Ping;  GUO Hai-bo
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
air-turbo-rocket;  turbulent mixing and combustion;  lobed mixer
PACS:
V43-34
DOI:
-
Abstract:
It is absolutely crucial for the performance of air-turbo-rocket engine in which forms an efficient and steady mixing combustion of air and fuel-rich gas in the combustion chamber. The experimental investigations on schemes of turbulent mixing and combustion for air-turbo-rocket engine, which are proceeded by worldwide institutes, are reviewed. Typical applications and various research achievements of aeronautic lobed mixers for enhancing molecular mixing between bypass and core flows are assessed. An essential summary of characteristics and key problems about turbulent mixing and combustion is carried out. Furthermore, the focuses on turbulent mixing and combustion in subsequent researches which should be paid extra attention are analyzed.

References:

[1]BOSSARD J A, CHRISTENSEN K L, FENDUN M H. Return of solid fuel gas generator ATR, AIAA87-1987[R]. USA: AIAA, 1987.
[2]LILLEY J S, HECHT S E, KIRKHAM B G, et al. Experimental evaluation of an air turbo ramjet, AIAA 94-3386[R]. USA: AIAA, 1994.
[3]THOMAS M E, LEONARD A D. Air-Turbo-Rocket com- bustion, AIAA 95-0813[R]. USA: AIAA, 1995.
[4]TANATSUGU Nobuhiro, NARUO Yoshihiro. Test results on ATR for a future space plane, AIAA92-5054[R]. USA: AIAA, 1992.
[5]SATO Tetsuya, TANATSUGU Nobuhiro, HATTA Hiroshi, et al. Development study of the ATREX engine for TSTO space plane, AIAA2001-1839[R]. USA: AIAA, 2001.
[6]HASEGAWA Hiroaki, SHIMADA Yosuke, KASHIKAWA Iwao, et al. Experimental study of compact combustor with double-staged flameholders for ATR engine, AIAA2001-3292[R]. USA: AIAA, 2001.
[7]EDEFUR Henrik. Design of an air-launched tactical missile for three different propulsion system: ATR, rocket and turbojet, GT 2007-27844[R]. [S. l.]: GT, 2007.
[8]POVINELLI L A. Computation of three-dimensional flow in turbofan mixers and comparison with experimental data, AIAA 80-0227[R]. USA: AIAA, 1980.
[9]BLACKMORE W L, THOMPSON C E. Three-dimensional viscous analysis of ducts and flow spliters[J]. Journal of Aircraft, 1983, 20(5): 385-389.
[10]ELLIOTT J K, MANNING T A, QIU Y J, et al. Computational and experimental studies of flow in multi-lobed forced mixers, AIAA 92-3568[R]. USA: AIAA, 1992.
[11]YU S C M， YEO J H，TEH J K L. Velocity measurements downstream of a lobed forced mixer with different trailing edge configurations, AIAA 94-0018[R]. USA: AIAA, 1994.
[12]OBA O Y, KODAMA H, NAKAMURA Y. Large eddy simulationanalysis of a 18-lobe convoluted mixer nozzle, AI-AA 2002-0717[R]. USA: AIAA, 2002.
[13]单勇, 张靖周. 波瓣喷管引射-混合器涡结构的数值研究[J]. 空气动力学报, 2005, 23(3): 355-358.
[14]张靖周, 谢志荣, 李立国. 三维强迫混合波瓣结构流场的数值研究[J]. 推进技术, 2001，22(3): 225-228.
[15]KUCHAR A P, CHAMBERLIN R. Test investigation of exhaust system mixers for energy efficient engine (E3) propulsion system, AIAA 80-0229[R]. USA: AIAA, 1980.
[16]路玉霞, 吴寿生. 速度比对波瓣混合器混合气动性能的影响[J]. 航空动力学报, 2002, 17(1): 53-57.
[17]PATERSON R W. Turbofan mixer nozzle flow Field-A benchmark experimental study[J]. Journal of Engineering for Gas Turbine and Power，1984, 106(3): 692-698.
[18]LI H, KOBAYASHI T, SAGA T, et al. Application of wavelet vector muti-resolution technique to PIV measurements, AIAA 2001-0696[R]. USA: AIAA, 2001.

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