大直径液氧煤油发动机燃烧室结构和隔板型式对声学特性的影响

doi:10.13675/j.cnki. tjjs. 200407

推进技术 ›› 2021, Vol. 42 ›› Issue (7): 1581-1592.DOI: 10.13675/j.cnki. tjjs. 200407

• Combustion, Heat and Mass Transfer • 上一篇下一篇

大直径液氧煤油发动机燃烧室结构和隔板型式对声学特性的影响

曹晨¹，谭永华²，陈建华¹，李龙飞¹

1.西安航天动力研究所液体火箭发动机技术重点实验室，陕西西安 710100;2.航天推进技术研究院，陕西西安 710100

出版日期:2021-07-15 发布日期:2021-08-15
作者简介:曹　晨，博士生，研究领域为液体火箭发动机技术。E-mail：18681840502@163.com

Effects of Structural Parameters and Baffle Patterns on Acoustic Characteristics of Combustion Chamber for Large Diameter LOX/Kerosene Engine

1.Science and Technology on Liquid Rocket Engine Laboratory，Xi’an Aerospace Propulsion Institute，Xi’an 710100，China;2.Academy of Aerospace Propulsion Technology，Xi’an 710100，China

Online:2021-07-15 Published:2021-08-15

摘要/Abstract

摘要： 随着火箭发射任务轨道高度和载荷质量的提高，发动机推力和燃烧室直径增大，使燃烧室固有声学振型越发复杂。燃烧室收敛段、抗脉动隔板及其结构型式会显著影响燃烧室的声学特性，进而改变发动机的燃烧不稳定性裕度。为了研究燃烧室结构和隔板型式对声学特性的影响，建立了燃烧室声学有限元模型，并通过单喷嘴声学实验验证了仿真模型的准确性。研究了燃烧室收敛段和一周六径隔板对燃烧室声学特性的影响，重点分析了RD-170和F-1发动机不同隔板型式下燃烧室的声学特性，从声压分布的角度分析了其隔板设计的合理性。结果表明：添加收敛段后，燃烧室的1L和1T1L振型的频率分别提高了14%和17%。RD-170发动机的周向隔板位于2R振型速度波腹位置；F-1发动机所采用的两周八径13分区隔板不仅减小了2R振型速度波腹的半径，而且使切向振型的声压极值面积最小。双十字隔板使F-1发动机燃烧室中出现径向振型切向化的趋势。

关键词: 大直径燃烧室;液氧煤油发动机;收敛段;声学特性;隔板型式

Abstract: Due to the increase of orbit height and load quality of launch mission， the engine’s thrust and diameter of combustion chamber increased， which makes its acoustic oscillation modes more and more complicated. Convergent section of combustion chamber， anti-pulsating baffle and its structural patterns could not only significantly affect the chamber’s acoustic characteristics， but also indirectly impact the combustion instability margin. In order to study the effects of structural parameters and baffle patterns on acoustic characteristics， a finite element simulation model of the combustion chamber is established. Firstly， the accuracy of the finite element model is verified by a single nozzle acoustic experiment. On this basis， the influence rules of convergent section of combustion chamber and one hub and six radial baffle are analyzed. The design rationality of baffle patterns for RD-170 and F-1 engine is emphatically investigated in terms of sound pressure distribution. The results show the frequency of 1L and 1T1L mode increases by 14% and 17% ， respectively， when convergent section of combustion chamber is considered. For RD-170 engine， the hub baffle locates at the position of 2R mode acoustic velocity anti-node. For F-1 engine， the 13-compartment baffle could not only reduce the radius of 2R mode acoustic velocity anti-node， but also minimize the area of pressure amplitude in tangential modes. The trend of radial vibration mode changing to tangential vibration mode is observed in F-1 engine’s combustion chamber with double cross baffle.

Key words: Large diameter combustion chamber;LOX/kerosene rocket engine;Convergent section;Acoustic characteristics;Baffle pattern

曹晨,谭永华,陈建华,李龙飞. 大直径液氧煤油发动机燃烧室结构和隔板型式对声学特性的影响[J]. 推进技术, 2021, 42(7): 1581-1592.

CAO Chen¹,TAN Yong-hua²,CHEN Jian-hua¹,LI Long-fei¹. Effects of Structural Parameters and Baffle Patterns on Acoustic Characteristics of Combustion Chamber for Large Diameter LOX/Kerosene Engine[J]. Journal of Propulsion Technology, 2021, 42(7): 1581-1592.

参考文献

[1] Harrje D T ， Reardon F H . Liquid Propellant Rocket Combustion Instability［R］. NASA SP-194， 1972.
[2] Culick F E C . Stability of High-frequency Pressure Oscillations in Rocket Combustion Chambers［J］. AIAA Journal， 2011， 1（5）： 1097-1104.
[3] Culick F E C ， Yang V . Overview of Combustion Instabilities in Liquid Propellant Rocket Engines［M］. Reston： American Institute of Aeronautics and Astronautics， 1995.
[4] Warren D ， Langer C . History in the Making-The Mighty F-1 Rocket Engine［R］. AIAA 89-2387.
[5] Bostwick L C . Development of LOX/RP-1 Engines for Saturn/Apollo Launch Vehicles［R］. AIAA 68-569.
[6] Oefelin J C ， Yang V . Comprehensive Review of Liquid-Propellant Combustion Instabilities in F-1 Engines［J］. Journal of Propulsion and Power， 2015， 31（5）： 657-677.
[7] You D ， Ku D D ， Yang V . Acoustic Waves in Baffled Combustion Chamber with Radial and Circumferential Blades［J］. Journal of Propulsion and Power， 2013， 29（6）： 1453-1467.
[8] Rubinsky V R . Instability Phenomenology and Case Studies： Combustion Instability in the RD-0110 Engine［M］. Reston： American Institute of Aeronautics and Astronautics， 1995.
[9] Hansen J ， Connolly P ， Larkin J ， et al . Incorporation of RD-180 Failure Response Features in the Atlas V Booster Emergency Detection System［R］. AIAA 2011-7120.
[10] Li D ， Xu X . Numerical Simulation of Combustion Flow Field in RD-170 Chamber［R］. AIAA 2009-4959.
[11] Li D L ， Tian Y ， Sun J G . Effects of Baffle on Combustion Acoustic Characteristics of Liquid Rocket Engine［J］. Journal of Aerospace Power， 2012， 27（3）： 715-720.
[12] Kim H J ， Lee K J ， Choi H S ， et al . An Experimental Study on Acoustic Damping Enhancement by the Gap of Baffled Injectors［R］. AIAA 2005-4446.
[13] Quinlan J M ， Kirkpatrick A T ， Milano D ， et al . Analytical and Numerical Development of a Baffled Liquid Rocket Combustion Stability Code［J］. Journal of Propulsion and Power， 2012， 28（1）： 122-131.
[14] You D ， Yang V . Linear Stability Analysis of Baffled Combustion Chamber with Radial and Circumferential Blades［R］. AIAA 2005-930.
[15] Eversman W ， Roy I . The Effect of a Baffle on Acoustic Radiation Directivity［R］. AIAA 98-2250.
[16] Quinlan J ， Bibik O ， Zinn B . Experimental and Numerical Combustion Instability Modes in Asymmetric Baffled Chambers［R］. AIAA 2010-6802.
[17] Li Xiang-ning ， Liu Yu . Basic Parameters Analysis of First Stage Engine System for Heavy Lift Vehicle［J］. Journal of Aerospace Power， 2010， 25（1）： 180-186.
[18] Li Long-fei ， Chen Jian-hua ， Liu Zhan-guo . Control Techniques of High Frequency Combustion Instability for High Thrust LOX/Kerosene Staged Combustion Cycle Engine［J］. Missiles and Space Vehicles， 2011（3）： 16-19.
[19] CAO Chen ， TAN Yong-hua ， Chen Jian-hua . Effects of Gas Nozzle and Resonators on Acoustic Characteristics of Combustion Chamber［J］. Journal of Aerospace Power， 2019， 34（8）： 1836-1846.

大直径液氧煤油发动机燃烧室结构和隔板型式对声学特性的影响

Effects of Structural Parameters and Baffle Patterns on Acoustic Characteristics of Combustion Chamber for Large Diameter LOX/Kerosene Engine

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