ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Hydraulic excitation experiment on frequency characteristic of simulated feed system after pump in a rocket engine
Received date: 2022-05-12
Revised date: 2022-06-27
Accepted date: 2022-10-13
Online published: 2022-10-26
Supported by
Foundation of Key Laboratory of Science and Technology on Liquid Rocket Engine(6142704210102)
To master the frequency characteristics of the feed system after pump in a liquid rocket engine and further understand the stability problems in the development of rocket engines， a test study is carried out on the frequency response of the hydraulic excitation system of the simulated structure after pump. The hard acoustic reflection boundary of the pump and the pulsating signal source formed by combustion of the gas generator are simulated by using the acoustic closed-end device and the turntable exciter， respectively， and the frequency response characteristics of the hydraulic excitation system under forced oscillation are obtained by sweeping the frequency. The results show that in the frequency range of 30-230 Hz， the excitation source can generate artificial pressure pulsation signals with a frequency division amplitude of 0.3-1.07 MPa. There is no difference between linear and stepped frequency sweeps in identifying frequencies， but the identification amplitude of linear frequency sweeps above 100 Hz is smaller than the real amplitude at the stepped frequency sweep platform. The acoustic closed-end device has obvious frequency selectivity. In the test system where the acoustic closed-end device is installed， the frequency band with better closed-end effect accounts for 82.5% of the research frequency range and the closed-end device makes this frequency range increase by 67%， demonstrating a relatively ideal closed-end boundary of the test system. With the increase of steady-state flow， the pulsation amplitude increases， and the main circuit shows more obviously the multi-order resonance frequency characteristics of the whole system， where the first three frequencies are 36， 65 and 101 Hz. In the local subsystem with strong boundary divided by large impedance components， the frequency characteristics under this boundary are highlighted. For a purely forced excitation system， the phase lags along the excitation propagation direction in turn； the phase difference changes greatly near the resonance point， and the pulsating pressure forms a large phase difference before and after the throttle plate and the tee with a long branch.
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 . DOI: 10.7527/S1000-6893.2022.27419
| 1 | CULICK F E C. Unsteady motions in combustion chambers for propulsion systems： RTO-AG-AVT-039［R］. 2006. |
| 2 | LEONARDI M， DI MATTEO F， STEELANT J， et al. Nonlinear analysis of low-frequency combustion instabilities in liquid rocket engines［M］∥Progress in Propulsion Physics–Volume 11. Les Ulis： EDP Sciences， 2019： 295-316. |
| 3 | 陈文， 邢理想， 徐浩海， 等. 深度节流补燃循环发动机系统稳定性研究［J］. 火箭推进， 2020， 46（3）： 41-48. |
| CHEN W， XING L X， XU H H， et al. Study on system stability of deep-throttling staged combustion cycled engine［J］. Journal of Rocket Propulsion， 2020， 46（3）： 41-48 （in Chinese）. | |
| 4 | 刘上， 刘红军， 陈建华， 等. 富氧燃气发生器-供应系统耦合稳定性研究［J］. 推进技术， 2013， 34（11）： 1448-1458. |
| LIU S， LIU H J， CHEN J H， et al. Investigation on oxidizer-rich preburner feed system coupled stability［J］. Journal of Propulsion Technology， 2013， 34（11）： 1448-1458 （in Chinese）. | |
| 5 | CASIANO M J. Extensions to the time lag models for practical application to rocket engine stability design［D］. State College： The Pennsylvania State University， 2010： 120-127. |
| 6 | KLEM M， PIEPER J， WALKER R. Combustor design and analysis using the ROCket Combustor Interactive Design （ROCCID） methodology： AIAA-1990-2240［R］. Reston： AIAA， 1990. |
| 7 | MUSS J， NGUYEN T V， JOHNSON C W. User’s manual for rocket combustor interactive design （ROCCID） and analysis computer program. Volume 1： User’s manual： NASA-CR-187109［R］.Washington，D.C.： NASA， 1991. |
| 8 | 何闯， 邢理想， 徐浩海. 气驱预压涡轮泵对发动机液氧路频率特性影响［J］. 火箭推进， 2021， 47（1）： 76-82. |
| HE C， XING L X， XU H H. Influence of gas drive pre-pressurized turbo-pump on frequency characteristics of liquid oxygen system in rocket engine［J］. Journal of Rocket Propulsion， 2021， 47（1）： 76-82 （in Chinese）. | |
| 9 | 张淼， 李斌， 邢理想. 基于燃气射流冷凝的氧路系统频率特性研究［J］. 航空学报， 2020， 41（2）： 123393. |
| ZHANG M， LI B， XING L X. Study on frequency characteristics of oxygen feed system based on gas jet and condensation［J］. Acta Aeronautica et Astronautica Sinica， 2020， 41（2）： 123393 （in Chinese）. | |
| 10 | 李斌， 杜大华， 张贵田， 等. 液氧/煤油补燃发动机低频频率特性研究［J］. 航空动力学报， 2009， 24（5）： 1187-1191. |
| LI B， DU D H， ZHANG G T， et al. Research on the low frequency characteristics of LOX/kerosene staged combustion cycle engine［J］. Journal of Aerospace Power， 2009， 24（5）： 1187-1191 （in Chinese）. | |
| 11 | BAZAROV V， LEE E， LINEBERRY D， et al. Pulsator designs for liquid rocket injector research： AIAA-2007-5156［R］. Reston： AIAA， 2007. |
| 12 | BALASUBRAMANYAM M， CHEN C P， BAZAROV V G. Numerical studies on frequency response to mass flow rate variations in a hydromechanical pulsator： AIAA-2009-4956［R］. Reston： AIAA， 2009. |
| 13 | CHUNG Y， KIM H， JEONG S， et al. Dynamic characteristics of open-type swirl injector with varying geometry［J］. Journal of Propulsion and Power， 2016， 32（3）： 583-591. |
| 14 | FU Q F， YANG L J， WANG X D. Theoretical and experimental study of the dynamics of a liquid swirl injector［J］. Journal of Propulsion and Power， 2010， 26（1）： 94-101. |
| 15 | FU Q F， YANG L J， QU Y Y， et al. Geometrical effects on the fluid dynamics of an open-end swirl injector［J］. Journal of Propulsion and Power， 2011， 27（5）： 929-936. |
| 16 | 薛帅杰， 刘红军， 洪流， 等. 厚液膜敞口型离心喷嘴动力学特性试验［J］. 航空学报， 2018， 39（12）： 122534. |
| XUE S J， LIU H J， HONG L， et al. Experimental on dynamic characteristics of an open-end swirl injector with thick liquid film［J］. Acta Aeronautica et Astronautica Sinica， 2018， 39（12）： 122534 （in Chinese）. | |
| 17 | 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）. | |
| 18 | 刘上， 张兴军， 程晓辉， 等. 火箭发动机泵后供应系统水力激振试验［J］. 航空动力学报， 2018， 33（11）： 2635-2643. |
| LIU S， ZHANG X J， CHENG X H， et al. Hydraulic vibration experiment on a rocket engine feed system after pump［J］. Journal of Aerospace Power， 2018， 33（11）： 2635-2643 （in Chinese）. | |
| 19 | 刘上， 赵瑞国， 付幼明， 等. 宽频高幅值水力激振信号的产生与控制［J］. 航空动力学报， 2018， 33（10）： 2492-2499. |
| LIU S， ZHAO R G， FU Y M， et al. Creation and control of hydraulic vibration signal with wide frequency range and high amplitude［J］. Journal of Aerospace Power， 2018， 33（10）： 2492-2499 （in Chinese）. | |
| 20 | 刘上， 张兴军， 程晓辉， 等. 发动机泵后管路-汽蚀管系统水力激振试验［J］. 航空动力学报， 2018， 33（12）： 3057-3064. |
| LIU S， ZHANG X J， CHENG X H， et al. Experiment for hydraulic vibration on rocket engine feed pipe-Venturi tube system after pump［J］. Journal of Aerospace Power， 2018， 33（12）： 3057-3064 （in Chinese）. | |
| 21 | 刘上， 张兴军， 程晓辉， 等. 一种液流系统声学闭端入口边界条件模拟装置： CN108225726A［P］. 2018-06-29. |
| LIU S， ZHANG X J， CHENG X H， et al. Simulating device for acoustic closed end inlet boundary conditions of fluid flow system： CN108225726A［P］. 2018-06-29 （in Chinese）. | |
| 22 | 李斌， 张小平， 马冬英. 我国新一代载人火箭液氧煤油发动机［J］. 载人航天， 2014， 20（5）： 427-431， 442. |
| LI B， ZHANG X P， MA D Y. The LOX/kerosene rocket engine for Chinese new-generation manned launch vehicle［J］. Manned Spaceflight， 2014， 20（5）： 427-431， 442 （in Chinese）. | |
| 23 | 刘上， 刘红军， 徐浩海， 等. 流量调节器-管路系统频率特性及稳定性［J］. 推进技术， 2012， 33（4）： 631-638. |
| LIU S， LIU H J， XU H H， et al. Frequency characteristics and stability of the flow regulator-pipe system［J］. Journal of Propulsion Technology， 2012， 33（4）： 631-638 （in Chinese）. |
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