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Analysis of hydrogen/oxygen combustor heat transfer and structural failure

机译:氢/氧燃烧室传热与结构破坏分析

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For all combustion systems with H_2 and O_2 being used as propellants problems concerning proper design and optimization of structures increase when achieving the stoichiometric mixture and higher pressures. Especially challenging are energy technology applications such as the spontaneous generation of steam by H_2/O_2 combustion for spinning reverve prurposes or within gas turbine cycles with typical heat fluxes in the order of 20 MW/m~2 and even more for H_2/O_2 rocket engines where local heat flux maxim may exceed 80 MW/m~2. To overcome these extreme thermal loads with combustion chamber temperatures around 3500 K copper alloys are favored for combustion chamber walls due to their heat transport properties although the maximum wall temperature is limited to about 700 K. The combustion chamber pressures for the applications mentioned above vary between 3 and 10 MPa. Typical wall thicknesses between the hot gas s ide and the coolant are in the order of 1 mm. Thermal strains induced by these large temperature differences yields to plastic deformation and thus many dramatically reduce the life time of the component.
机译:对于使用H_2和O_2作为推进剂的所有燃烧系统,当达到化学计量的混合物和较高的压力时,有关适当设计和结构优化的问题就会增加。能源技术应用尤其具有挑战性,例如通过H_2 / O_2燃烧自发产生蒸汽以达到旋转目的,或在燃气轮机循环内,典型热通量约为20 MW / m〜2,对于H_2 / O_2火箭发动机甚至更高局部热通量最大值可能超过80 MW / m〜2。为了克服燃烧室温度约为3500 K的这些极端热负荷,尽管最大壁温限制在700 K以内,但铜合金因其传热性能而被首选用于燃烧室壁。上述应用中的燃烧室压力在3和10 MPa。热气侧和冷却剂之间的典型壁厚约为1毫米。这些较大的温差引起的热应变会导致塑性变形,因此许多应力会极大地缩短组件的使用寿命。

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