Numerical investigation of low cycle fatigue life for channel wall nozzles

CHENG Cheng; WANG Yibai; LIU Yu; LIN Qingguo

doi:10.13224/j.cnki.jasp.2018.07.003

Numerical investigation of low cycle fatigue life for channel wall nozzles

doi: 10.13224/j.cnki.jasp.2018.07.003

1.
Research and Development Center,Shanghai Institute of Space Propulsion,Shanghai 201112,China
2.
Shanghai Engineering Research Center of Space Engine,Shanghai 201112
3.
School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing 100191

基金项目: 航空科学基金（2013ZB51014）

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出版历程
- 收稿日期: 2016-12-29
- 刊出日期: 2018-07-28

Preliminary experiment on spontaneous ignition performances of cavity-based strut flameholder

1.
Research and Development Center,Shanghai Institute of Space Propulsion,Shanghai 201112,China
2.
Shanghai Engineering Research Center of Space Engine,Shanghai 201112
3.
School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing 100191

摘要

摘要: The thermal-structural response and low cycle fatigue life of a three-dimensional (3D) channel wall nozzle with regenerative cooling were numerically investigated by coupling the finite volume fluid-thermal method, nonlinear finite element thermal-structural analysis and local strain methods. The nozzle had a high area ratio (nozzle exit area divided by throat area) under cyclic working loads. Parametric studies were carried out to evaluate the effects of channel structural parameters such as channel width, channel height, liner thickness and rib width. Results showed that the integrated effects of three-dimensional channel structure and load distribution caused serious strain, which mainly occurred at the intersectant regions of liner wall on the gas side and the symmetric planes of channel and rib. The cooling effect and channel structural strength were significantly improved as the channel width and height decreased, leading to substantial extension of the nozzle service life. On the other hand, the successive decrease in liner thickness and rib width apparently increased the strain amplitude and residual strain of channel wall nozzle during cyclic work, significantly shortening the service life. The present work is of value for design of the channel wall nozzle to prolong its cyclic service life.
- liquid propellant rocket engine /
- low cycle fatigue /
- channel wall nozzle /
- regenerative cooling /
- nonlinear structural analysis /
- finite element method
Abstract: The spontaneous ignition performances of a cavity-based strut flameholder were preliminarily investigated with spray distances of 5－50mm at atmospheric pressure, the air temperature and oxygen volume fraction were within the range of 750－900℃ and 13.4%－15.8%, Mach number ranged from 0.20－0.28. Results showed that the flameholder could be autoignited when the inlet temperature was above 850℃. As the inlet temperature increased, the performances of spontaneous ignition improved. When the inlet Mach number became larger, the temperature range for successful spontaneous ignition became narrower. With the increase of fuel injection distance, the autoignition performances of the stabilizer were improved. The cavity structure of the stabilizer could stabilize the flame.
- spontaneous combustion /
- ignition /
- strut flameholder /
- bluff body /
- cavity /
- finite element method

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参考文献(24)

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