液体火箭发动机高频燃烧不稳定问题综述

doi:10.7527/S1000-6893.2023.29450

Abstract

Abstract:

High-frequency combustion instability remains a key challenge in the development of high-performance liquid rocket engines. The physical processes involved have significant characteristics such as cross scale， nonlinearity， and multi-field coupling. Improving the overall understanding of such problems is helpful for systematic research work. This article briefly describes the main characteristics， key physical mechanisms， and research ideas of high-frequency combustion instability in liquid rocket engines， focusing on the research progress in sub-process response mechanisms both domestically and internationally in recent decades. It points out the important significance of studying response mechanisms for different engine combustion rate control processes， summarizes the progress made by different analysis methods， challenges faced， and subsequent development directions， providing reference for engineering management of such issues.

Key words: liquid rocket engine, high frequency combustion instability, combustion response, rate control process, combustion heat release distribution control

CLC Number:

V434.4

Guangxu WANG, Bin LI, Yonghua TAN, Yushan GAO. High frequency combustion instability in liquid rocket engines: Review[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529450-529450.

Figures/Tables 16

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

References 152

1	SUTTON G P. History of liquid propellant rocket engines［M］. Reston： AIAA， 2006.
2	HUZEL D K， HUANG D H， ARBIT H. Modern engineering for design of liquid-propellant rocket engines［M］. Reston： AIAA， 1992.
3	张贵田. 高压补燃液氧煤油发动机［M］. 北京：国防工业出版社， 2005.
	ZHANG G T. High pressure staged combustion LOX/kerosene rocket engine ［M］. Beijing： National Defense Industry Press， 2005 （in Chinese）.
4	李斌，陈晖，马冬英，等. 500 tf级液氧煤油高压补燃发动机研制进展［J］. 火箭推进， 2022， 48（2）： 1-10.
	LI B， CHEN H， MA D Y， et al. Development of 500 tf class high pressure stage combustion LOX/kerosene rocket engine［J］. Journal of Rocket Propulsion， 2022， 48（2）： 1-10 （in Chinese）.
5	孙纪国，郑孟伟，龚杰峰，等. 220 tf补燃循环氢氧发动机研制进展［J］. 火箭推进， 2022， 48（2）： 11-20.
	SUN J G， ZHENG M W， GONG J F， et al. Development of staged combustion cycle LH₂/LOX engine with 220 tf thrust［J］. Journal of Rocket Propulsion， 2022， 48（2）： 11-20 （in Chinese）.
6	HARRJE D T， REARDON F H. Liquid propellant rocket combustion instability ［M］. Washington， D.C.： NASA， 1972.
7	YANG V， ANDERSON W E. Liquid rocket engine combustion instability［M］. Reston： AIAA， 1995.
8	CROCCO L， CHENG S I. Theory of combustion instability in liquid propellant rocket motors ［M］. London： Butterworths Publications Ltd， 1956.
9	庄逢辰. 液体火箭发动机喷雾燃烧的理论、模型及应用［M］. 长沙：国防科技大学出版社， 1995.
	ZHUANG F C. Theory， model and application of spray combustion of liquid rocket engine［M］. Changsha： National University of Defense Technology Press， 1995 （in Chinese）.
10	DRANOVSKY M L， YANG V， CULICK F， et al. Combustion instabilities in liquid rocket engines： Testing and development practices in Russia［M］. Reston： AIAA， 2007.
11	NATANZON M S. Combustion instability［M］. Reston： AIAA， 2008.
12	CULICK F E. Unsteady motions in combustion chambers for propulsion systems： AGARDograph AG-AVT-039-2006 ［R］. Brussels： NATO， 2006.
13	SIRIGNANO W A. Driving mechanisms for combustion instability［J］. Combustion Science and Technology， 2015， 187（1-2）： 162-205.
14	聂万胜，丰松江. 液体火箭发动机燃烧动力学模型与数值计算［M］. 北京：国防工业出版社， 2011： 70.
	NIE W S， FENG S J. Combustion dynamics model and numerical calculation of liquid rocket engine［M］. Beijing： National Defense Industry Press， 2011： 70 （in Chinese）.
15	王振国. 液体火箭发动机燃烧过程建模与数值仿真［M］. 北京：国防工业出版社， 2012.
	WANG Z G. Modeling and numerical simulations of internal combustion process of liquid rocket engines［M］. Beijing： National Defense Industry Press， 2012 （in Chinese）.
16	杨立军，富庆飞. 液体火箭发动机推力室设计［M］. 北京：北京航空航天大学出版社， 2013.
	YANG L J， FU Q F. Design of thrust chamber of liquid rocket engine［M］. Beijing： Beijing University of Aeronautics & Astronautics Press， 2013 （in Chinese）.
17	KOBAYASHI K， DAIMON Y， IIZUKA N， et al. Studies on combustion instability for liquid propellant rocket engines： AIAA-2011-6028 ［R］. Reston： AIAA， 2011.
18	KOBAYASHI K， NUNOME Y， TOMITA T， et al. Stability index for injection-coupled instability in full-scale firing tests［J］. Journal of Propulsion and Power， 2017， 33（6）： 1489-1503.
19	FLANDRO G， JACOB E. Finite amplitude nonlinear waves in liquid rocket combustion chambers： AIAA-2008 -1003 ［R］. Reston： AIAA， 2008.
20	FLANDRO G， FISCHBACH S. Effects of parallel wave incidence on combustion instability driving mechanisms： AIAA-2007-5807 ［R］. Reston： AIAA， 2007.
21	FISHER S C， DODD F E， JENSEN R J， et al. Scaling techniques for liquid rocket combustion stability testing ［J］. Progress in Asronautics and Aeronautics， 1995， 169（1995）： 545-564.
22	DEXTER C E， FISHER M F， HULKA J R， et al. Scaling techniques for design， development， and test in liquid rocket thrust chambers：Aspects of modeling ［J］. Progress in Asronautics and Aeronautics， 2004， 200 （2004）： 553-600.
23	SOHN C H， SEOL W S， SHIBANOV A A， et al. On the method for hot-fire modeling of high-frequency combustion instability in liquid rocket engines［J］. KSME International Journal， 2004， 18（6）： 1010-1018.
24	SOHN C H， SEOL W S， SHIBANOV A A， et al. Combustion stability boundaries of the subscale rocket chamber with impinging jet injectors［J］. Journal of Propulsion and Power， 2007， 23（1）： 131-139.
25	张蒙正. 燃烧不稳定性模拟实验技术［M］. 西安：西北工业大学出版社， 2017.
	ZHANG M Z. Simulation experiment technology of combustion instability［M］. Xi’an： Northwestern Polytechnical University Press， 2017 （in Chinese）.
26	张蒙正，张志涛，李鳌，等. 高频燃烧不稳定性单喷注器燃烧室模拟实验的研究［J］. 实验技术与管理， 2008， 25（3）： 28-32.
	ZHANG M Z， ZHANG Z T， LI A， et al. Simulation test of high-frequency combustion instabilities of chamber with single injector［J］. Experimental Technology and Management， 2008， 25（3）： 28-32 （in Chinese）.
27	张育林，刘昆，程谋森. 液体火箭发动机动力学理论与应用［M］. 北京：科学出版社， 2005.
	ZHANG Y L， LIU K， CHENG M S. Dynamic theory and application of liquid rocket engine［M］. Beijing： Science Press， 2005 （in Chinese）.
28	MCCORMACK P D. A driving mechanism for high frequency combustion instability in liquid fuel rocket engines［J］. The Journal of the Royal Aeronautical Society， 1964， 68（645）： 633-637.
29	FENWICH J R， BUGLER G J. Oscillatory flame front flow rate amplification through propellant injection ballistics ［C］∥ Third ICRPG Combustion Conference. Cape Kennedy： CPIA Publication， 1967.
30	YANG A L， YANG S R， XU Y F， et al. Periodic atomization characteristics of simplex swirl injector induced by klystron effect ［J］. Chinese Journal of Aeronautics， 2018， 31（5）： 1066-1074.
31	ANON. 4400Hz Vibration investigation final report. Rockwell International ［R］. East Hartford： Pratt and Whitney Aircraft， 1971.
32	ANON. Summary report on an investigation of combustion instability for liquid oxygen and liquid and cold gas hydrogen propellants ［R］. East Hartford： Pratt and Whitney Aircraft， 1964.
33	CONRAD E， PARISH H， WANHAINEN J P. Effect of propellant injection velocity on screech in 20， 000-pound hydrogen-oxygen rocket engine： NASA TN D-3373［R］. Washington， D.C.： NASA， 1966.
34	ARMBRUSTER W， HARDI J S， SUSLOV D， et al. Experimental investigation of self-excited combustion instabilities with injection coupling in a cryogenic rocket combustor［J］. Acta Astronautica， 2018， 151： 655-667.
35	BAZAROV V. Self-pulsations in coaxial injectors with central swirl liquid stage： AIAA-1995-2358 ［R］. Reston： AIAA， 1995.
36	BAZAROV V G， YANG V. Liquid-propellant rocket engine injector dynamics［J］. Journal of Propulsion and Power， 1998， 14（5）： 797-806.
37	STRASSER W. Towards the optimization of a pulsatile three-stream coaxial airblast injector［J］. International Journal of Multiphase Flow， 2011， 37（7）： 831-844.
38	BAI X， CHENG P， SHENG L Y， et al. Effects of backpressure on self-pulsation characteristics of liquid-centered swirl coaxial injectors［J］. International Journal of Multiphase Flow， 2019， 116： 239-249.
39	BAI X， SHENG L Y， LI Q L， et al. Effects of annulus width and post thickness on self-pulsation characteristics for liquid-centered swirl coaxial injectors［J］. International Journal of Multiphase Flow， 2020， 122： 103140.
40	REN Y J， GUO K K， ZHAO J F， et al. Numerical investigation of spray self-pulsation characteristics of liquid-centered swirl coaxial injector with different recess lengths［J］. International Journal of Multiphase Flow， 2021， 138： 103592.
41	SAHOO S K， GADGIL H. Dynamics of self-pulsation in gas-centered swirl coaxial injector： An experimental study［J］. Journal of Propulsion and Power， 2021， 37（3）： 450-462.
42	EBERHART C J， FREDERICK R A Jr. Details on the mechanism of high-frequency swirl coaxial self-pulsation［J］. Journal of Propulsion and Power， 2017， 33（6）： 1418-1427.
43	HUANG Y H， ZHOU J， HU X P， et al. Acoustic model for the self-oscillation of coaxial swirl injector： AIAA-1997-3328 ［R］. Reston： AIAA， 1997.
44	黄玉辉，周进，胡小平，等. 气液同轴式喷嘴自激振荡的试验现象和声学模型及对火箭发动机不稳定燃烧的影响［J］. 声学学报， 1998， 23（5）： 459-465.
	HUANG Y H， ZHOU J， HU X P， et al. Experiment and acoustic model for the self-oscillation of coaxial swirl injector and its influence to combustion of liquid rocket engine［J］. Acta Acustica， 1998， 23（5）： 459-465 （in Chinese）.
45	KIM B D， HEISTER S. Effect of chamber pressure variation on high-frequency hydrodynamic instability of shear coaxial injector： AIAA-2004-3522 ［R］. Reston： AIAA， 2004.
46	IM J H， YOON Y. The effects of the ambient pressure on self-pulsation characteristics of a gas/liquid swirl coaxial injector： AIAA-2008-4850［R］. Reston： AIAA， 2008.
47	KANG Z T， LI Q L， CHENG P， et al. Effects of recess on the self-pulsation characteristics of liquid-centered swirl coaxial injectors［J］. Journal of Propulsion and Power， 2016， 32（5）： 1124-1132.
48	SASAKI M， SAKAMOTO H， TAKAHASHI M， et al. Comparative study of recessed and non-recessed swirl coaxial injectors： AIAA-1997-2907 ［R］. Reston： AIAA， 1997.
49	IM J H， KIM D， YOON Y， et al. Self-pulsation characteristics of a swirl coaxial injector with various injection and geometric conditions： AIAA-2005-3749 ［R］. Reston： AIAA， 2005.
50	IM J H， CHO S， YOON Y， et al. Comparative study of spray characteristics of gas-centered and liquid-centered swirl coaxial injectors［J］. Journal of Propulsion and Power， 2010， 26（6）： 1196-1204.
51	康忠涛，张新桥，成鹏，等. 气核尺寸对气液同轴离心式喷嘴自激振荡的影响［J］. 航空学报， 2014， 35（12）： 3283-3292.
	KANG Z T， ZHANG X Q， CHENG P， et al. Influence of gas core dimension on self-pulsation of gas-liquid swirl coaxial injector［J］. Acta Aeronautica et Astronautica Sinica， 2014， 35（12）： 3283-3292 （in Chinese）.
52	康忠涛，王振国，李清廉，等. 压力振荡对气液同轴离心式喷嘴自激振荡的影响［J］. 航空学报， 2018， 39（6）： 121988.
	KANG Z T， WANG Z G， LI Q L， et al. Influence of pressure oscillation on self-pulsation of gas-liquid swirl coaxial injector［J］. Acta Aeronautica et Astronautica Sinica， 2018， 39（6）： 121988 （in Chinese）.
53	NUNOME Y， SAKAMOTO H， TAMURA H， et al. An experimental study of super-pulsating flow on a shear coaxial injector with a recessed inner post： AIAA-2007-5560 ［R］. Reston： AIAA， 2007.
54	NUNOME Y， TAMURA H， ONODERA T， et al. Effect of liquid disintegration on flow instability in a recessed region of a shear coaxial injector： AIAA-2009-5389 ［R］. Reston： AIAA， 2009.
55	YOON J， CHUNG J M， YOON Y. Study on self-pulsation characteristics of gas centered shear coaxial injector for supercavitating underwater propulsion system［J］. International Journal of Naval Architecture and Ocean Engineering， 2011， 3（4）： 286-292.
56	YOON J， CHUNG J M， YOON Y. Study on self-pulsation characteristics of gas/liquid shear coaxial injector with annular liquid sheets： AIAA-2012-3859 ［R］. Reston： AIAA， 2012.
57	CHUNG J M， YOON J， YOON Y. Effect of recess length on instability in a gas-centered liquid annular jet［J］. Atomization and Sprays， 2015， 25（1）： 1-21.
58	IM J H， YOON Y， BAZAROV V G. Experiment study on self-pulsation of a gas/liquid swirl coaxial injector in high pressure environment ［C］∥ 60th International Astronautical Congress. Paris： IAF， 2009： 6708-6716.
59	BAI X， CHENG P， LI Q L， et al. Effects of self-pulsation on combustion instability in a liquid rocket engine［J］. Experimental Thermal and Fluid Science， 2020， 114： 110038.
60	GONZALEZ-FLESCA M， SCHMITT T， DUCRUIX S， et al. Large eddy simulations of a transcritical round jet submitted to transverse acoustic modulation［J］. Physics of Fluids， 2016， 28（5）： 055106.
61	ZHANG P Y， WANG B. Effects of elevated ambient pressure on the disintegration of impinged sheets［J］. Physics of Fluids， 2017， 29（4）： 042102.
62	RUTARD N， DOREY L H， LE TOUZE C， et al. Large-eddy simulation of an air-assisted liquid jet under a high-frequency transverse acoustic forcing［J］. International Journal of Multiphase Flow， 2020， 122： 103144.
63	HEIDMANN M F， WIEBER P R. Analysis of n-heptane vaporization in unstable combustor with travelling transverse oscillations： NASA-TN-D-3424-1965 ［R］. Washington， D. C.： NASA， 1965.
64	MIESSE C C. The effect of ambient pressure oscillations on the disintegration and dispersion of a liquid jet［J］. Journal of Jet Propulsion， 1955， 25（10）： 525-530.
65	SRINIVASAN V， SALAZAR A J， SAITO K. Modeling the disintegration of modulated liquid jets using volume-of-fluid （VOF） methodology［J］. Applied Mathematical Modelling， 2011， 35（8）： 3710-3730.
66	YANG X C， TURAN A L. Simulation of liquid jet atomization coupled with forced perturbation［J］. Physics of Fluids， 2017， 29（2）： 022103.
67	HEISTER S D， RUTZ M W， HILBING J H. Effect of acoustic perturbations on liquid jet atomization［J］. Journal of Propulsion and Power， 1997， 13（1）： 82-88.
68	李佳楠，雷凡培，杨岸龙，等. 强迫扰动下的射流撞击雾化特性［J］. 航空学报， 2020， 41（12）： 124027.
	LI J N， LEI F P， YANG A L， et al. Atomization characteristics of impinging liquid jets coupled with forced perturbation［J］. Acta Aeronautica et Astronautica Sinica， 2020， 41（12）： 124027 （in Chinese）.
69	HARVAZINSKI M E， ANDERSON W E， MERKLE C L. Analysis of self-excited combustion instabilities using two- and three-dimensional simulations［J］. Journal of Propulsion and Power， 2013， 29（2）： 396-409.
70	HARVAZINSKI M E， HUANG C， SANKARAN V， et al. Coupling between hydrodynamics， acoustics， and heat release in a self-excited unstable combustor［J］. Physics of Fluids， 2015， 27（4）： 045102.
71	HARVAZINSKI M E， HUANG C， SANKARAN V， et al. Combustion instability mechanisms in a pressure-coupled gas-gas coaxial rocket injector： AIAA-2013-3990 ［R］. Reston： AIAA， 2013.
72	HARVAZINSKI M， ANDERSON W， MERKLE C. Combustion instability diagnostics using the Rayleigh index： AIAA-2011-5548 ［R］. Reston： AIAA， 2011.
73	GRAHAM W R， PERAIRE J， TANG K Y. Optimal control of vortex shedding using low-order models. Part I？open-loop model development［J］. International Journal for Numerical Methods in Engineering， 1999， 44（7）： 945-972.
74	GRAHAM J， LEYVA I， RODRIGUEZ J， et al. On the effect of a transverse acoustic field on a flush shear coaxial injector： AIAA-2009-5142 ［R］. Reston： AIAA， 2009.
75	SCHMITT T， RODRIGUEZ J， LEYVA I A， et al. Experiments and numerical simulation of mixing under supercritical conditions［J］. Physics of Fluids， 2012， 24（5）： 055-104.
76	WEGENER J L， FORLITI D J， LEYVA I A， et al. Receptivity of a cryogenic coaxial gas-liquid jet to acoustic disturbances： AIAA-2014-3487 ［R］. Reston： AIAA， 2014.
77	HAKIM L， SCHMITT T， DUCRUIX S， et al. Dynamics of a transcritical coaxial flame under a high-frequency transverse acoustic forcing： influence of the modulation frequency on the flame response［J］. Combustion and Flame， 2015， 162（10）： 3482-3502.
78	RUIZ A， SCHMITT T， SELLE L， et al. Effects of the recess length of a coaxial injector on a transcritical LO2/H2 jet flame［C］∥ 23rd International Colloquium on the Dynamics of Explosions and Reactive Systems. Berlin： Springer， 2011： 1-7.
79	URBANO A， DOUASBIN Q， SELLE L， et al. Study of flame response to transverse acoustic modes from the LES of a 42-injector rocket engine［J］. Proceedings of the Combustion Institute， 2017， 36（2）： 2633-2639.
80	URBANO A， SELLE L， STAFFELBACH G， et al. Exploration of combustion instability triggering using large eddy simulation of a multiple injector liquid rocket engine［J］. Combustion and Flame， 2016， 169： 129-140.
81	MASQUELET M， MENON S. Large-eddy simulation of flame-turbulence interactions in a shear coaxial injector［J］. Journal of Propulsion and Power， 2010， 26（5）： 924-935.
82	MASQUELET M， MENON S， JIN Y， et al. Simulation of unsteady combustion in a LOX-GH2 fueled rocket engine［J］. Aerospace Science and Technology， 2009， 13（8）： 466-474.
83	WANG X J， HUO H F， WANG Y X， et al. Comprehensive study of cryogenic fluid dynamics of swirl injectors at supercritical conditions［J］. AIAA Journal， 2017， 55（9）： 3109-3119.
84	WANG X J， WANG Y X， YANG V. Geometric effects on liquid oxygen/kerosene Bi-swirl injector flow dynamics at supercritical conditions［J］. AIAA Journal， 2017， 55（10）： 3467-3475.
85	WANG X J， LI Y X， WANG Y X， et al. Near-field flame dynamics of liquid oxygen/kerosene bi-swirl injectors at supercritical conditions［J］. Combustion and Flame， 2018， 190： 1-11.
86	WANG X J， YEH S T， CHANG Y H， et al. A high-fidelity design methodology using LES-based simulation and POD-based emulation： A case study of swirl injectors［J］. Chinese Journal of Aeronautics， 2018， 31（9）： 1855-1869.
87	PRIEM R J， GUENTERT D C. Combustion instability limits determined by a nonlinear theory and a one dimensional model： NASA-TN-D-1409-1962 ［R］.Washington， D.C.： NASA， 1962.
88	PRIEM R J. Theoretical and experimental models for unstable rocket combustor［J］. Symposium （International） on Combustion， 1963， 9（1）： 982-992.
89	HEIDMANN M F， WIEBER P R. Analysis of frequency response characteristics of propellant vaporization： NASA-TM-X-52195-1966 ［R］. Washington， D. C.： NASA， 1966.
90	TONG A Y， SIRIGNANO W A. Oscillatory vaporization of fuel droplets in an unstable combustor［J］. Journal of Propulsion and Power， 1989， 5（3）： 257-261.
91	DUVVUR A. Numerical solution of convective droplet vaporization in an oscillatory gas flow： Application to liquid propellant longitudinal mode combustion instability ［D］. Irvine： University of California， 1992.
92	DUVVUR A， CHIANG C H， SIRIGNANO W A. Oscillatory fuel droplet vaporization： Driving mechanism for combustion instability［J］. Journal of Propulsion and Power， 1996， 12（2）： 358-365.
93	LEE G Y， YOON W S. Controlling factors of pressure-coupled combustion responses in a high pressure combustion chamber： AIAA-2004-3519 ［R］. Reston： AIAA， 2004.
94	LEE G Y， KIM S Y， YOON W S. Oscillatory vaporization and acoustic response of droplet at high pressure［J］. International Communications in Heat and Mass Transfer， 2008， 35（10）： 1302-1306.
95	YOON W S， KIM S Y. Responses of droplet evaporation to high-pressure oscillations： AIAA-2004-1161［R］. Reston： AIAA， 2004.
96	尹婷，吴高杨，聂万胜. 压力振荡环境下液滴蒸发动态响应特性研究［J］. 火箭推进， 2015， 41（4）： 19-28.
	YIN T， WU G Y， NIE W S. Study on dynamic response characteristics of droplet evaporation in pressure oscillation environment［J］. Journal of Rocket Propulsion， 2015， 41（4）： 19-28 （in Chinese）.
97	TIEN J S， SIRIGNANO W A. Unsteady thermal response of the condensed-phase fuel adjacent to a reacting gaseous boundary layer［J］. Symposium （International） on Combustion， 1971， 13（1）： 529-539.
98	PRIEM R J， HEIDMANN M F. Propellant vaporization as a design criterion for rocket-engine combustion chambers： NASA-TR-R-67-l960 ［R］. Washington， D. C.： NASA， 1960.
99	BHATIA R， SIRIGNANO W A. One-dimensional analysis of liquid-fueled combustion instability［J］. Journal of Propulsion and Power， 1991， 7（6）： 953-961.
100	REARDON F H， An investigation on transverse mode combustion instability in liquid propellant rocket motors ［D］. New Jersey： Princeton University， 1961.
101	REARDON F H， CROCCO L， HARRJE D T. Velocity effects in transverse mode liquid propellant rocket combustion instability［J］. AIAA Journal， 1964， 2（9）： 1631-1641.
102	庄逢辰，聂万胜，周进，等. 应用隔板抑制液体火箭发动机不稳定燃烧的数值模拟［J］. 指挥技术学院学报， 1997， 8（1）： 1-12.
	ZHUANG F C， NIE W S， ZHOU J， et al. Numerical simulation of applicating baffles to suppression of combustion instabilities in liquid rocket engine［J］. Journal of Equipment Academy， 1997， 8（1）： 1-12 （in Chinese）.
103	LEVINE R S. Development problems in large liquid rocket engines ［C］∥ Third AGARD. Brussels： NATO， 1958.
104	LEVINE R S. Experimental status of high frequency liquid rocket combustion instability［J］. Symposium （International） on Combustion， 1965， 10（1）： 1083-1099.
105	INGARD U， ISING H. Acoustic nonlinearity of an orifice［J］. The Journal of the Acoustical Society of America， 1967， 42（1）： 6-17.
106	SIRIGNANO W A. A theoretical study of nonlinear combustion instability： longitudinal mode ［D］. New Jersey： Princeton University， 1964.
107	ZINN B T. A theoretical study of nonlinear transverse combustion instability in liquid propellant rocket motors ［D］. New Jersey： Princeton University， 1966.
108	ZINN B T. A theoretical study of non-linear damping by Helmholtz resonators［J］. Journal of Sound and Vibration， 1970， 13（3）： 347-356.
109	FÖRNER K， CÁRDENAS MIRANDA A， POLIFKE W. Mapping the influence of acoustic resonators on rocket engine combustion stability［J］. Journal of Propulsion and Power， 2015， 31（4）： 1159-1166.
110	ZINN B T. Longitudinal mode acoustic losses in short nozzles［J］. Journal of Sound and Vibration， 1972， 22（1）： 93-105.
111	LIOI C， KU D， YANG V. Linear acoustic analysis of the preburner of an oxidizer-rich staged combustion engine［J］. Journal of Propulsion and Power， 2018， 35（2）： 396-402.
112	PIERINGER J， SATTELMAYER T， FASSL F. Simulation of combustion instabilities in liquid rocket engines with acoustic perturbation equations［J］. Journal of Propulsion and Power， 2009， 25（5）： 1020-1031.
113	袁磊. 空气加热器高频燃烧不稳定维持机理研究［D］. 长沙：国防科技大学， 2018.
	YUAN L. Study on self-sustained mechanism of high frequency combustion instability in air heater［D］.Changsha： National University of Defense Technology， 2018 （in Chinese）.
114	NUSCA M J， MATHIS N P， MICHAELS R S. Computational modeling of injection throttling using a new class bipropellants in the army’s impinging stream vortex engine ［C］∥ Proceedings of the 4th JANNAF Liquid Propulsion Subcommittee Meeting. Columbia： JHUERG， 2008.
115	NUSCA M J. MICHAELS R S. Development of a computational model for the impinging stream vortex engine ［C］∥ Proceedings of the 39th JANNAF Combustion Subcommittee Meeting. Columbia： JHUERG， 2003.
116	NUSCA M J. MICHAELS R S. Development of a computational model for the army’s impinging stream vortex engine ［C］∥ Proceedings of the 1st JANNAF Liquid Propulsion Subcommittee Meeting. Columbia： JHUERG， 2004.
117	NUSCA M J. MICHAELS R S. Computational modeling of hypergolic ignition in the army’s impinging stream vortex engine ［C］∥ Proceedings of the 2nd JANNAF Liquid Propulsion Subcommittee Meeting. Columbia： JHUERG， 2005.
118	NUSCA M J， MATHIS N P， MICHAELS R S. Computational modeling of the army’s impinging stream vortex engine with an injection throttling system ［C］∥ Proceedings of the 41st JANNAF Combustion Subcommittee Meeting. Columbia： JHUERG， 2006.
119	NUSCA M， MATHIS N， MICHAELS S. Modeling hypergolic ignition in the army’s impinging stream vortex engine including injection throttling： AIAA-2007-5443 ［R］. Reston： AIAA， 2007.
120	NUSCA M. Modeling combustion instability in small MMH-NTO liquid rocket engines using CFD： Injector-chamber coupling： AIAA-2010-1518 ［R］. Reston： AIAA， 2010.
121	SATTELMAYER T， SCHMID M， SCHULZE M. Interaction of combustion with transverse velocity fluctuations in liquid rocket engines［J］. Journal of Propulsion and Power， 2015， 31（4）： 1137-1147.
122	聂万胜. 自燃推进剂火箭发动机燃烧稳定性研究［D］. 长沙：国防科技大学，1998.
	NIE W S. Study on combustion stability of hypergolic propellant rocket engine ［D］. Changsha： National University of Defense Technology， 1998.（in Chinese）
123	尕永婧. 液氧煤油模型发动机高频燃烧不稳定性研究［D］. 北京：清华大学， 2012.
	GA Y J. Research on the high frequency combustion instability in the model of LOX/kerosene engine［D］.Beijing： Tsinghua University， 2012 （in Chinese）.
124	QIN J X， ZHANG H Q， WANG B. Numerical evaluation of acoustic characteristics and their damping of a thrust chamber using a constant-volume bomb model［J］. Chinese Journal of Aeronautics， 2018， 31（3）： 470-480.
125	ANDERSON W， RYAN H， SANTORO R， et al. Combustion instability mechanisms in liquid rocket engines using impinging jet injectors： AIAA-1995-2357 ［R］. Reston： AIAA， 1995.
126	GARBY R， SELLE L， POINSOT T. Large-Eddy Simulation of combustion instabilities in a variable-length combustor［J］. Comptes Rendus Mecanique， 2013， 341（1-2）： 220-229.
127	SUMMERFIELD M. A theory of unstable combustion in liquid propellant rocket systems［J］. Journal of the American Rocket Society， 1951， 21（5）： 108-114.
128	SZUCH J R， WENZEL L. Analysis of chugging in liquid-bipropellant rocket engines using propellants with different vaporization rates： NASA-TN-D-3080-1965 ［R］. Washington， D. C.： NASA， 1965.
129	SMITH A J， REARSON F H. The sensitive time lag theory and its application to liquid rocket combustion instability problems： AFRPL-TR-67-314［R］. Pasadena： Air Force Rocket Propulsion Laboratory， 1968.
130	HUTT J J， ROCKER M. High-frequency injection-coupled combustion instability ［J］， Progress in Astronautics and Aeronautics， 1995， 169： 345-356.
131	CASIANO M J. Extensions to the time lag models for practical application to rocket engine stability design ［D］. Pennsylvania： The Pennsylvania State University， 2010.
132	汪广旭，谭永华，庄逢辰，等. 自燃推进剂模型燃烧室高频纵向燃烧不稳定性［J］. 航空动力学报， 2020， 35（8）： 1578-1585.
	WANG G X， TAN Y H， ZHUANG F C， et al. High frequency longitudinal combustion instability of modeled hypergolic propellants combustor［J］. Journal of Aerospace Power， 2020， 35（8）： 1578-1585 （in Chinese）.
133	MUSS J A， NGUYEN T V， JOHNSON C W. User’s manual for rocket combustor interactive design （ROCCID） and analysis computer program， Volume I-User’s Manual： NASA-CR -187109-1991 ［R］. Washington， D. C.： NASA， 1991.
134	MUSS J， NGUYEN T V， JOHNSON C W. User’s manual for rocket combustor interactive design （ROCCID） and analysis computer program. Volume Ⅱ： Appendixes A-K： NASA-CR-187110 -1991 ［R］. Washington， D. C.： NASA， 1991.
135	O’HARA L， YU Y， ANDERSON W， et al. A vortex shedding-based combustion response model applied to an unstable liquid rocket combustor： AIAA-2009-5136 ［R］. Reston： AIAA， 2009.
136	TAMANAMPUDI G M R， ANDERSON W E. Development of combustion instability analysis tool by incorporating combustion response models： AIAA-2015-4165 ［R］. Reston： AIAA， 2015.
137	HUANG C， GEJJI R M， ANDERSON W E， et al. Combustion dynamics behavior in a single-element lean direct injection （LDI） gas turbine combustor： AIAA-2014-3433 ［R］. Reston： AIAA， 2014.
138	HUANG C， ANDERSON W， MERKLE C. Multi-fidelity framework explorations for nonlinear Euler equations［C］∥ 53rd AIAA/SAE/ASEE Joint Propulsion Confer-ence. Reston： AIAA， 2017.
139	ALESSANDRO S， FREZZOTTI M L， FAVINI B， et al. A multi-dimensional approach for low order modeling of combustion instability in a rocket combustor： AIAA-2018-4677［R］. Reston： AIAA， 2018.
140	FREZZOTTI M L， ALESSANDRO S， GALLO G， et al. Low-order modeling of coupling effects between propellant injection and pressure fluctuations in high frequency combustion instability ［C］∥ Proceedings of Space Propulsion， 2018.
141	汪广旭，谭永华，陈建华，等. 考虑喷注流强分布的纵向稳定性建模与分析［J］. 航空学报， 2021， 42（6）： 124510.
	WANG G X， TAN Y H， CHEN J H， et al. Modeling and analysis of longitudinal stability considering injection intensity distribution［J］. Acta Aeronautica et Astronautica Sinica， 2021， 42（6）： 124510 （in Chinese）.
142	KIRCHHOFF G. Vorlesungen über mathematische Physik Mechanik［M］. 1877 （in Chinese）.
143	FLANDRO G. Approximate analysis of nonlinear instability with shock waves： AIAA-1982-1220 ［R］. Reston： AIAA， 1982.
144	FLANDRO G A. Energy balance analysis of nonlinear combustion instability［J］. Journal of Propulsion and Power， 1985， 1（3）： 210-221.
145	汪广旭，谭永华，陈建华，等. 液体火箭发动机非稳态燃烧过程对其稳定性的影响［J］. 航空动力学报， 2019， 34（4）： 929-936.
	WANG G X， TAN Y H， CHEN J H， et al. Effects of unsteady combustion process on combustion instability of liquid rocket engine［J］. Journal of Aerospace Power， 2019， 34（4）： 929-936 （in Chinese）.
146	汪广旭，付秀文，石晓波，等. 燃烧室非线性压力振荡及其产生机理研究［J］. 火箭推进， 2016， 42（2）： 29-34， 58.
	WANG G X， FU X W， SHI X B， et al. Study on nonlinear pressure oscillation and its mechanism in combustion chamber［J］. Journal of Rocket Propulsion， 2016， 42（2）： 29-34， 58 （in Chinese）.
147	FREZZOTTI M L， D’ALESSANDRO S， FAVINI B， et al. Numerical issues in modeling combustion instability by quasi-1D Euler equations［J］. International Journal of Spray and Combustion Dynamics， 2017， 9（4）： 349-366.
148	SUBRAMANIAN P. Dynamical systems approach to the investigation of thermoacoustic instabilities ［D］. Chennai： Indian Institute of Technology Madras， 2011.
149	SUBRAMANIAN P， SUJITH R I， WAHI P. Subcritical bifurcation and bistability in thermoacoustic systems［J］. Journal of Fluid Mechanics， 2013， 715： 210-238.
150	SUJITH R I， JUNIPER M P， SCHMID P J. Non-normality and nonlinearity in thermoacoustic instabilities［J］. International Journal of Spray and Combustion Dynamics， 2016， 8（2）： 119-146.
151	SUJITH R I， UNNIVR. Complex system approach to investigate and mitigate thermoacoustic instability in turbulent combustors［J］. Physics of Fluids， 2020， 32（6）： 061401.
152	汪广旭，谭永华，庄逢辰，等. 喷注流强分布对高频纵向燃烧不稳定性抑制效果［J］. 航空学报， 2022， 43（9）： 126018.
	WANG G X， TAN Y H， ZHUANG F C， et al. Suppression effect of injection intensity distribution on longitudinal combustion instability［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（9）： 126018 （in Chinese）.

[1]	Ziguang LI, Peng CHENG, Qinglian LI, Xiao BAI, Pengjin CAO. Influence of backpressure on spray distribution characteristics of a gas-liquid pintle injector element [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(2): 128614-128614.
[2]	Ruida CHEN, Xiachao CHEN, Hongyu CHEN, Hui XU, Xin HONG. Ignition characteristics and exhaust experiment of 120 N engine at simulated high lunar temperature [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529112-529112.
[3]	Yushan GAO, Song YAN, Zhiwei ZHANG. Precise engine displacement testing technique based on stereo vision and circular mark points [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 528826-528826.
[4]	Penggang MU, Binchao LI, Jun WANG, Shaowei SONG, Hanyang SHI. Research progress on structural strength of liquid rocket engine during engineering development phase [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529065-529065.
[5]	Meng DONG, Yonghua TAN, Chuang HE, Lixiang XING, Ruiguo ZHAO. Hydraulic excitation experiment on frequency characteristic of simulated feed system after pump in a rocket engine [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 127419-127419.
[6]	Le XIANG, Kaifu XU, Hui CHEN, Suibo LI, Kai ZHANG, Shixin LIU. Experimental studies on cavitating flow for liquid rocket engine cryogenic turbopump: Review [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(7): 27131-027131.
[7]	Zehao CHEN, Hui CHEN, Yushan GAO, Hang ZHANG. Review and prospect of model-based fault diagnosis technology for liquid rocket engines [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 629016-629016.
[8]	Xiaopu ZHANG, Feng REN, Pengli XU, Zhimin LI, Caihong SU. Selection method of measuring parameters for rocket engine based on fault recognition [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(22): 128522-128522.
[9]	Dahua DU, Bin LI. Key structural dynamic design technologies in liquid rocket engines: Review [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(10): 27554-027554.
[10]	WANG Guangxu, TAN Yonghua, ZHUANG Fengchen, CHEN Jianhua, YANG Bao'e, HONG Liu. Suppression effect of injection intensity distribution on longitudinal combustion instability [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126018-126018.
[11]	LIANG Tao, CUI Peng, CHENG Peng, LI Qinglian, ZHANG Bin, SONG Jie. Influence of pressure ratio on evolution of cavitation dynamic process in Venturi tube [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 125212-125212.
[12]	CUI Peng, SONG Jie, LI Qinglian, CHEN Lanwei, LIANG Tao, SUN Jun. Dynamic modeling and simulation analysis of LOX/RP1 variable thrust engines using motor pump: Part I-single condition analysis [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124884-124884.
[13]	WANG Guangxu, TAN Yonghua, CHEN Jianhua, ZHUANG Fengchen, HONG Liu, CHEN Hongyu, YANG Baoe. Modeling and analysis of longitudinal stability considering injection intensity distribution [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(6): 124510-124510.
[14]	TANG Liang, HU Jinhua, LIU Jiwu, LI Ping, ZHOU Lixin, YANG Baoe. Experimental study on oblique jet wall impingement and geometrical parameter modeling of liquid film [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(12): 124061-124061.
[15]	YANG Baofeng, LI Bin, CHEN Hui, LIU Zhanyi. Matching effect between inducer and impeller in a liquid rocket engine propellant pump [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(5): 122609-122609.

High frequency combustion instability in liquid rocket engines: Review

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 16

References 152

Related Articles 15

Recommended Articles

Metrics

Comments