中国航天科技集团公司 西安航天动力研究所,西安,710100
纸质出版:2016
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张忠利, 李斌, 张蒙正, 周立新. 吸热型碳氢燃料与高温合金相容性研究[J]. 航空动力学报, 2016, 31(2): 451-458.
doi: 10.13224/j.cnki.jasp.2016.02.025
张忠利, 李斌, 张蒙正, 周立新. 吸热型碳氢燃料与高温合金相容性研究[J]. 航空动力学报, 2016, 31(2): 451-458. DOI: 10.13224/j.cnki.jasp.2016.02.025.
doi: 10.13224/j.cnki.jasp.2016.02.025 DOI:
论证了吸热型碳氢燃料与高温合金相容性研究过程
设计了燃油与高温合金联合加热装置
测试了非钝化和钝化状态的GH625试件和GH3128试件在壁温为500~850℃时、经过燃油压力为3.5MPa、燃油温度为450~500℃、流速为1~5m/s浸渍后的力学性能和金相组织.试验结果表明:在燃料温度为500℃、试件温度为850℃时
GH3128试件结焦量少于GH625试件
GH3128试件的塑性应力下降40%、GH625试件的塑性应力下降60%.燃油浸渍时高温合金钝化后结焦量明显减少.
The course of consistent capacity research was demonstrated from endothermic hydrocarbon fuels and nickel-base-alloy
and the co-heating device was designed for the fuels and alloy. The mechanical capacity and metallographic diagram were gained
whenever the passivated test-slices of GH625 and GH3128 were put under wall temperature about 500-850℃
pressure about 3.5MPa
fuel temperature about 450-500℃
and velocity about 1-5m/s fuels. The experiment results showed that
under the fuel temperature about 500℃ and test-slice temperature about 850℃
the coking capacity of GH3128 was less than GH625
and the plastic stress declined about 40% for GH3128 and 60% for GH625. After the test-slice of alloy was passivated
the coking capacity was obviously cut down.
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