液体火箭发动机中频耦合振荡初步研究

推进技术 ›› 2013, Vol. 34 ›› Issue (1): 101-108.

液体火箭发动机中频耦合振荡初步研究

刘上,刘红军,孙宏明,陈宏玉

西安航天动力研究所,陕西西安 710100;西安航天动力研究所,陕西西安 710100;西安航天动力研究所,陕西西安 710100;西安航天动力研究所,陕西西安 710100

发布日期:2021-08-15
作者简介:刘上(1984—),男,博士生,研究领域为液体火箭发动机系统动力学。E-mail:liushang020160@yahoo.com.cn

Preliminary Study of Medium Frequency Coupled Oscillation in Liquid Rocket Engine

Xi’an Aerospace Propulsion Institute, Xi’an 710100, China;Xi’an Aerospace Propulsion Institute, Xi’an 710100, China;Xi’an Aerospace Propulsion Institute, Xi’an 710100, China;Xi’an Aerospace Propulsion Institute, Xi’an 710100, China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究常规液体火箭发动机研制中出现的中频流量型耦合振荡问题,对发动机耦合系统中各环节建立了满足声学分析的线性化频域模型。通过比较供应系统和燃烧室的幅频响应,并分析耦合系统的自由振荡复频率,以判断发动机的耦合稳定性。计算结果符合发动机试车规律,能够有效地反映该类型不稳定的特征。进一步讨论了燃烧时滞、喷注压降、管路长度和安装节流圈对系统耦合不稳定的影响规律,并揭示了该类型不稳定的机理。

关键词: 液体火箭发动机;中频耦合振荡;机理分析;节流圈

Abstract: In order to investigate the medium frequency coupled oscillation encountered during the storable liquid propellant rocket engine development, the linear frequency-domain models for every component satisfying acoustics analysis were established. By comparing the response of feed system and chamber, and analyzing the natural oscillation complex frequency of the coupled system, the engine system coupled stability at different conditions was estimated. The calculated results accord with the engine test phenomena, by which the characteristics of this kind instability can be described effectively. Moreover, the influence of combustion time lag, injection pressure drop, feed pipe length and throttle orifice on the system coupled instability was discussed. Thus the mechanism of the instability was identified.

Key words: Liquid rocket engine; Medium frequency coupled oscillation; Mechanism analysis; Throttle orifice

刘上,刘红军,孙宏明,陈宏玉. 液体火箭发动机中频耦合振荡初步研究[J]. 推进技术, 2013, 34(1): 101-108.

参考文献

[1] Bazarov．Design of Injectors for Self-Sustaining of Combustion Chambers Stability[R].AIAA 2006-4722.
[2] 孙宏明.中频燃烧不稳定性[J].火箭推进,1,7(1):20-26.
[3] Harrje D T, Reardon F H.Liquid Propellant Rocket Combustion Instability[R].NASA SP-4,2.
[4] Hutt John J, Rocker Marvin.High Frequency Injector-Coupled Combustion.Liquid Rocket Engine Combustion Instability[M].Washington:AIAA Inc.,1995.
[5] Kesselring R C, Nelson R L, Sprouse K M.Engine Hydraulic Stability[R].NASA CR- 9,7.
[6] Kahn D R, Schuman M D,Hunting J K, et al.Orbital Maneuvering Engine Feed System Coupled Stability Investigation[R].NASA CR-9,5.
[7] Jensen R J, Dodson H, Claflin S E.LOX/ Hydrocarbon Combustion Instability Investigation[R].NASA CR-9,9.
[8] Benedictis M De,Ordonneau G.High Frequency Injection Coupled Combustion Instabilities Study of Combustion Chamber/feed System Coupling[R].AIAA 2006-4721.
[9] Nusca Michael J.Modeling Combustion Instability in Small MMH-NTO Liquid Rocket Engines Using CFD:Injector-Chamber Coupling[R].AIAA 2010-1518.
[10] Aithal Shashi M, Zhining Liu, Jensen Robert J.Nonlinear Injection Transfer Function Simulations for Liquid Propellants[R].AIAA 2008-4742.
[11] Ray-Sing Lin,Bertolotti Fabio P, Eckett Christopher A.A Study of the Application of a Finite Element Model to the Predictions of the Injection-Coupled Response of a LOX Post[R].AIAA 2010-6563.
[12] Yu Y C,Sisco J C, Anderson W E.Examination of Spatial Mode Shapes and Resonant Frequencies Using Linearized Euler Solutions[R].AIAA 2007-3999.
[13] Sisco J C, Smith R J, Sankaran V, et al.Examination of Mode Shapes in an Unstable Model Rocket Combustor[R].AIAA 2006-4525.
[14] Wylie E B, Streeter V L.Fluid Transients [M].New York:McGraw-Hill International Book Co., 1978.
[15] 格列克曼.液体火箭发动机自动调节[M]．顾明初(译)．北京:宇航出版社,1995.
[16] Natanzon M S.Combustion Instability [M].Washington:AIAA, Inc., 1996.
[17] Bazarov, Vigor Yang.Liquid-Propellant Rocket Engine Injector Dynamics [J].Journal of Propulsion and Power, 8,4(5):797-806.
[18] Culick F E C.Unsteady Motions in Combustion Chambers for Propulsion Systems[R].AG-AVT-9,6.