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Damage localization effects of the regeneratively-cooled Thrust chamber wall in LOX/methane rocket engines

Chinese Journal of Aeronautics 2018年第8期31卷 1667-1678页

作者： Jiawen SONG Bing SUN School of Astronautics Beihang University

To investigate the damage localization effects of the Thrust chamber wall caused by combustions in LOX/methane rocket engines, a fluid-structural coupling computational methodology with a multi-channel model is developed to obtain 3-demensioanl thermal and structural responses.Heat and mechanical loads are calculated by a validated finite volume fluid-thermal coupling numerical method considering non-premixed combustion processes of propellants. The methodology is subsequently performed on an LOX/methane Thrust chamber under cyclic operation. Results show that the heat loads of the Thrust chamber wall are apparently non-uniform in the circumferential direction. There are noticeable disparities between different cooling channels in terms of temperature and strain distributions at the end of the hot run phase, which in turn leads to different temperature ranges, strain ranges, and residual strains during one cycle. With the work cycle proceeding, the circumferential localization effect of the residual strain would be significantly enhanced. A post-processing damage analysis reveals that the low-cycle fatigue damage accumulated in each cycle is almost unchanged, while the quasi static damage accumulated in a considered cycle declines until stabilized after several cycles. The maximum discrepancy of the predicted lives between different cooling channels is about 30%.

关键词： Cyclic plasticity Damage Heat transfer Regenerative cooling Rocket engine Service life Thrust chamber

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Fault diagnosis of liquid rocket engine Thrust chamber based on improved augmented particle filter

Fault diagnosis of liquid rocket engine thrust chamber based...

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第40届中国控制会议

作者： Yangzhi Zeng Xiaodong Shao Qinglei Hu Haifeng Hu Hao Pan School of Automation Science and Electrical Engineering Beihang University School of Aeronautic Science and Engineering Beihang University Beijing Advanced Innovation Center for Big-Data Based Precision Medicine Beihang University Beijing Aerospace Automatic Control Institute China Academy of Launch Vehicle Technology

The fault diagnosis algorithm proposed in this paper firstly establishes the nonlinear thermodynamic model of the Thrust chamber of the liquid rocket engine under normal mode and four common fault modes.Secondly,the particle filter is designed to estimate the output and residuals of the Thrust chamber and complete the fault detection task by using the generalized likelihood ratio test method.Thirdly,an extended fault estimation particle filter is established by merging the fault estimation vector into the extended state estimation vector to complete the task of fault estimation.Finally,a fault recognition algorithm is designed according to the fault estimation result to complete the fault recognition task in the case of a single fault,at the same time,the recognition result is used to improve the accuracy of the enhanced particle filter.The proposed method is verified to realize real-time and accurate fault diagnosis of Thrust chamber under the influence of uncertain factors such as process and measurement noise.

关键词： Rocket engine Thrust chamber fault diagnosis particle filter

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高压补燃液体火箭发动机推力室冷却技术及结构优化

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Aerospace China 2023年第3期24卷 10-17页

作者： HOU Ruifeng LI Longfei LU Gang CHEN Jianhua Science and Technology on Liquid Rocket Engine Laboratory Xi’an Aerospace Propulsion InstituteXi’an 710100

The LM-5B launch vehicle has successfully completed four missions.Eight high-pressure staged combustion LOX/kerosene engines(YF-100)are equipped in the four boosters of the LM-5B,two in each booster.The YF-100 engine adopts various cooling techniques to ensure cooling,including a metal thermal barrier coating,multiple liquid film cooling slots,spiral milled regenerative cooling channels with high aspect ratio,a non-weld forming Thrust chamber and an optimal cooling flow path design.In addition,the 480-ton LOX/kerosene engine for China’s future heavy-lift launch vehicle LM-9 will be larger in size,which makes it more difficult to be developed and will have more strict requirements in the cooling process.The main differences between the LM-5B and LM-5 are briefly described in this paper and the development process and working characteristics of YF-100 engines are introduced.The advantages and disadvantages of main cooling methods used in the Thrust chambers of high-thrust liquid propellant engines are also described.Finally,the future challenges and countermeasures in cooling technology for China’s high-thrust LOX/kerosene engines and future reusable rocket engines are also presented.

关键词： LM-5B YF-100 staged combustion LOX/kerosene engine Thrust chamber cooling technology

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氢氧火箭发动机助推器结构分析及寿命预测

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Aerospace China 2023年第3期24卷 48-55页

作者： LIU Xiao LI Yongjiang WU Youliang ZHAO Shihong TIAN Yuan SUN Bing Beijing Aerospace Propulsion Institute Beijing 100076 School of Astronautics Beihang UniversityBeijing 100191

After several trial runs,penetrating cracks appeared in the Thrust chamber wall of a hydrogen-oxygen rocket engine,which will affect the service life and performance of the engine.It is necessary to reduce the wall heat flux by injection element mixture ratio biasing or propellant films to prolong the life of the liner wall.In this paper,the deformation of three types of inner walls was calculated under cyclic mechanical loading,and the stress-strain response and the fatigue life of the inner walls were compared.The results show that the bottom midpoint of the gas side channel,with the largest residual strain,is the most prone to failure.In addition,the adoption of injection element mixture ratio biasing or film cooling can greatly increase the life of the inner wall,and the improvement effect of the two measures is similar.

关键词： Thrust chamber cracks heat transfer fatigue life

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