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不同注气成分置驱瓦斯效果数值模拟研究
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作者 徐小马 燕湘湘 黄姝羽 《工矿自动化》 CSCD 北大核心 2024年第4期112-120,共9页
注气促抽瓦斯的注气成分主要有N_(2),CO_(2)和空气,但目前针对不同注入成分的置驱效果对比研究较少。针对该问题,建立了考虑裂隙气体渗流和基质孔隙气体扩散的注气成分置驱瓦斯数学模型,在对该模型验证的基础上,模拟注入气体置驱煤样瓦... 注气促抽瓦斯的注气成分主要有N_(2),CO_(2)和空气,但目前针对不同注入成分的置驱效果对比研究较少。针对该问题,建立了考虑裂隙气体渗流和基质孔隙气体扩散的注气成分置驱瓦斯数学模型,在对该模型验证的基础上,模拟注入气体置驱煤样瓦斯气体过程,并对比研究相同注气压力和煤体渗透率条件下不同注气成分(N_(2),CO_(2)和空气)对瓦斯的置驱效果。结果表明:①相同注气时间下,从注气端到排气端,注入气体的体积分数逐渐降低,在注气端附近注入气体的体积分数最高;瓦斯体积分数逐渐增加,在排气端附近瓦斯体积分数最高;随着注气时间增加,注入气体的体积分数增加区域逐渐向排气端移动直至覆盖整个煤样,瓦斯体积分数降低区域也逐渐向排气端移动直至覆盖整个煤样,表明煤样中的瓦斯逐渐被置换出来,进而被驱替出整个煤样。②在相同注气时间内,从注气端到排气端,N_(2),CO_(2)和空气3种注入气体体积分数和瓦斯体积分数具有相似的变化规律,即从注气端到排气端,注入气体体积分数逐渐降低、瓦斯体积分数逐渐升高,随着注气时间增加,注入气体的体积分数增高区域增加。相同注气时间、煤样相同位置处注入气体的体积分数和瓦斯体积分数互补,即相加为100%。③3种注入气体对瓦斯的置驱效果排序为CO_(2)>空气>N_(2)。④对排气端气体的体积分数分析可知,排气端气体的体积分数随时间变化可分为突破阶段、平衡进行阶段和置驱完成阶段。不同注入气体3个阶段持续时间不同,注入N_(2)突破时间和置驱完成时间分别为30,90 min;注入CO_(2)突破时间和置驱完成时间分别为20,80 min;注入空气突破时间和置驱完成时间分别为28,87 min。⑤在现场应用时,应根据具体煤层的吸附解吸能力、煤层自燃特性等选择合适的注入气体。 展开更多
关键词 瓦斯抽采 抽采 成分 置驱瓦斯 置驱效果 注气端
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Aero-Thermal Performances of Leakage Flows Injection from the Endwall Slot in Linear Cascade of High-Pressure Turbine
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作者 Wan Aizon W Ghopa Zambri Harun +1 位作者 Ken-ichi Funazaki Takemitsu Miura 《Journal of Thermal Science》 SCIE EI CAS CSCD 2015年第1期49-57,共9页
The existence of a gap between combustor and turbine endwall in the real gas turbine induces to the leakages phenomenon. However, the leakages could be used as a coolant to protect the endwaU surfaces from the hot gas... The existence of a gap between combustor and turbine endwall in the real gas turbine induces to the leakages phenomenon. However, the leakages could be used as a coolant to protect the endwaU surfaces from the hot gas since it could not be completely prevented. Thus, present study investigated the potential of leakage flows as a function of film cooling. In present study, the flow field at the downstream of high-pressure turbine blade has been investigated by 5-holes pitot tube. This is to reveal the aerodynamic performances under the influenced of leakage flows while the temperature measurement was conducted by thermoehromic liquid crystal (TLC). Expe- rimental has significantly captured theaerodynamics effect of leakage flows near the blade downstream. Further- more, TLC measurement illustrated that the film cooling effectiveness contours were strongly influenced by the secondary flows behavior on the endwall region. Aero-thermal results were validated by the numerical simulation adopted by commercial sottware, ANSYS CFX 13. Both experimental and numerical simulation indicated almost similar trendinaero and also thermal behavior as the amount of leakage flows increases. 展开更多
关键词 endwall fllmcooling leakage flows secondary flows aerodynamic loss film cooling effectiveness
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