Research progress on hydrogen gas explosion suppression materials and their suppression mechanisms
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摘要: 氢气在全球清洁能源转型中扮演着关键角色，但其可燃性和高爆炸危害性也使得氢气安全成为研究热点。聚焦氢气抑爆领域的最新研究成果，对不同种类抑爆材料及抑爆机理进行了综合评述。首先，介绍了气体、液体、固体以及多相复合抑爆材料的研究进展，对比分析了抑爆效果、关键参数及其变化规律。其次，探讨了抑爆材料影响氢气爆炸的物理、化学以及物理化学综合的作用过程，以揭示各类材料的抑爆机理。最后，展望了氢气抑爆材料的未来发展趋势，强调对高效能抑爆材料探索和机理研究的深化以及在实际应用中所面临的诸多挑战。Abstract: Hydrogen is crucial in the global shift towards clean energy and is gaining significance in the energy industry, while its high flammability and explosive hazard make its safety a research hotspot. It is crucial to thoroughly investigate and assess the safety of hydrogen as it progresses toward commercialization in the energy sector. This article reviews the latest advancements in hydrogen explosion suppression conducted by researchers around the world, aiming at offering a scientific foundation and technical approach to efficiently manage and reduce the damaging impacts of hydrogen explosion incidents. The article focuses on the study of hydrogen explosion suppression materials and their suppression mechanisms, so as to provide scientific understanding and technical support for the safe application of hydrogen. Firstly, it systematically introduces the research progress in hydrogen explosion suppression by discussing four significant categories, i.e., gas, liquid, solid, and multiphase composite explosion suppression materials. By comparing and analyzing the effects, key performance parameters, and the variation rules of these materials, the current research status and effectiveness of various explosion suppression materials are sorted out, helping to deepen the understanding of the explosion suppression effects of these materials. Secondly, focusing on the suppression mechanism, the research delves into the vital role of explosion suppression materials in suppressing hydrogen explosions. Starting from three dimensions, i.e., physical suppression, chemical suppression, and physicochemical comprehensive suppression, it elucidates the mechanisms of action of explosion suppression materials in the suppression process, contributing to a deeper understanding of the role of explosion suppression materials in suppressing or mitigating hydrogen explosions. Finally, the article looks forward to the future development directions of hydrogen explosion suppression materials, especially emphasizing the importance of further studies on the high-efficiency explosion suppression materials and the challenges faced in practical applications. This review is aimed to provide scientific reference and inspiration for the research, development, and application of new hydrogen explosion suppression materials.
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随着近年来对新型反装甲灵巧弹药的研制, 爆炸成形弹丸(explosively formed projectiles, EFP)战斗部受到越来越广泛的重视和研究。目前正在开发或生产的灵巧弹药多是基于EFP战斗部的末敏弹。这种EFP战斗部的终点弹道能力要求达到1000倍装药口径炸距以上仍可有效打击装甲目标的顶甲或侧甲。在实施远距离攻击时, 为保证弹丸经过一个较长的空气弹道阶段后仍能以足够小的攻角准确毁伤目标, 要求该类战斗部能够成型具有良好空气动力学特性的EFP。由于EFP是作战实时起爆成型, 其部件制造和装配过程中的不对称性以及偏心起爆的位置偏置都会对EFP成型造成影响, 使实际成型的弹丸总是或多或少存在不对称性。这些不对称性将直接影响EFP外弹道飞行稳定性及着靶精度等:曹兵等[1]通过实验研究了偏心起爆对EFP成型的影响, 得到了起爆偏心量与EFP头部横向剩余速度之间的关系; K.Jach等[2]通过数值编码对药型罩施加偏心载荷, 获得尾翼偏置的EFP; D.J.Brandeis等[3]通过结构设计研究了各种不对称形状对爆炸成形弹丸空气动力性能的影响; C.Berner等[4]研究了尾裙高度、数量及其非对称性对EFP空气动力特性及飞行性能的影响, 并且用参数表示了在翻转运动缓慢时非对称性外形结构的的优点; P.Rouge等[5]通过实验和数值计算研究了装药端面中心点起爆以及偏心起爆条件下爆轰产物以及成型弹丸内部压力、速度及变形分布特点。但是, 对于由偏心起爆引起EFP外形不对称而对弹丸在飞行弹道(从EFP飞行到命中目标这段距离)运动规律及终点弹道散布水平的影响, 尚未见有系统的研究。
本文中基于60 mm弧锥结合罩EFP装药, 通过EFP飞行弹道实验研究不同偏心起爆方式下成型EFP外弹道运动规律特性及终点毁伤效应, 利用数值模拟分析不同起爆偏心量下成型EFP的空气动力学特性, 研究结果为EFP战斗部起爆参数设置提供有益参考。
1. 实验设计
EFP战斗部以自行优化设计的⌀60 mm变壁厚弧锥结合型紫铜罩战斗部为基础, 药型罩口径为56 mm, 曲率半径为46 mm, 罩顶部壁厚为3.5 mm。装药为圆柱形装药, 装药高度为60 mm, 战斗部装药结构如图 1所示。
实验中采用相同装药结构的EFP战斗部:无偏心量时, 采用装药端面中心点起爆方式, 起爆点为图 2所示起爆点1;偏心起爆时, 在距离装药端面中心点2、4 mm处分别设置偏心起爆点2和3, 起爆点分别为图 2所示起爆点2和3。采用偏心量δ与装药直径d的量纲一比值K表示偏心量相对于装药直径的大小, 即
, 则3种偏心起爆方案的相对偏心量分别为0、3.3%和6.7%, 图 2即为3种不同相对起爆偏心量的设计方案示意图。
图 3所示为偏心起爆条件下EFP飞行弹道实验现场布置:EFP战斗部水平设置, 距离地面1.5 m, 沿EFP飞行弹道15 m处开始, 按照5 m间隔共设置15块网靶, 用来捕捉EFP飞行过程中弹形和飞行姿态变化。在离战斗部15 m处和85 m处分别设置2组铝箔靶测定EFP飞行中的速度及速度降。距战斗部中心96 m处设置1 m×1 m×25 mm的45钢方形靶, 从而获得偏心起爆对EFP的立靶密集度以及侵彻威力的影响。实验之前将战斗部置于特制的木支架上, 利用瞄准仪瞄准目标、水平测量仪调整靶板姿态, 保证战斗部中心、网靶中心和钢靶中心处在同一水平面上。
2. 偏心起爆影响EFP飞行特性和弹道散布实验
EFP飞行弹道实验中预先在网靶上竖直做一条直线, 设置网靶时用铅垂线校正将其作为处理EFP飞行姿态的基准, 每发弹丸连续穿过15个网靶。弹丸穿过网靶时, 部分网靶破裂, 未统计破裂靶纸信息。实验中无偏心时, 回收有效靶纸12张; 偏心量为3.3%时回收到有效靶纸12张; 起爆相对偏心量为6.7%时回收到有效靶纸13张。图 4所示为3发EFP在飞行弹道不同距离上部分网靶穿孔照片。
由图 4可以看出网靶较好的记录了EFP飞行过程中姿态的变化情况。实验表明, 无偏心量时, 弹丸在网靶上的穿孔几乎接近圆形, 说明弹丸运行稳定; 当相对偏心量为3.3%时, 弹丸开始有小幅度波动变化, 但是很快弹丸的运动就趋向于稳定, 网靶穿孔逐渐接近圆形; 当相对偏心量为6.7%时, 弹丸在网靶上留下的穿孔接近EFP纵向截面形状, 扭曲变形的尾翼在网靶上得到了体现, 说明成型EFP不具有对称性, 弹丸在飞行过程中发生剧烈运动, 外弹道运行稳定性较差。从EFP穿孔形状还可以发现EFP弹轴不仅与网靶法线之间的夹角θ(攻角)改变, 而且靶纸上弹孔长轴与铅垂线之间夹角γ(摆动角)也不断发生变化。由此可以判断EFP在飞行过程中姿态变化很复杂, 在攻角变化的同时还以弹道方向为轴发生摆动。
图 4 实验所得EFP在飞行弹道不同距离上网靶穿孔照片Figure 4. Experimental net target perforation photo of EFP at different distances on flight trajectoryEFP在网靶上穿孔的形状由EFP的形状和着靶姿态决定, 竖直布置的网靶可以捕捉EFP的外形和运动特点。通过网靶上的穿孔形状, 尺寸及穿孔分布可以测定EFP飞行过程中运动学参数的变化情况[6]。图 5~6所示为EFP飞行攻角和摆动角随飞行距离变化曲线图, 图中设弹丸头部穿孔向上攻角为正, 弹丸头部穿孔向下攻角为负, 弹轴偏向铅垂线左侧摆动角为正, 弹轴偏向铅垂线右侧摆动角为负。
图 5 攻角随EFP飞行距离变化曲线Figure 5. Attack angle varied with different distance on flight trajectory
图 6 摆动角随EFP飞行距离变化曲线Figure 6. Swinging angle varied with different distance on flight trajectory从图 5~6中可以看出, EFP飞行过程中必然伴随着攻角和摆动角的变化, EFP在网靶上穿孔是弹丸在该网靶处攻角和摆动角的合成角度。完整EFP在飞行过程中攻角呈现非线性周期摆动, 摆动幅度随弹丸运行距离增加有明显减小的趋势。当炸高大于50 m后, 相对偏心量小于3.3%时弹丸攻角基本保持在10°以内, 弹丸飞行稳定, 即EFP进入攻角小幅波动的稳定飞行阶段; 相对偏心量为6.7%时, EFP的攻角和摆动角摆动幅值较大而且摆动收敛速度较小, 弹丸在空气中发生非周期性摆动。弹丸运行周期保持在10-2s量级。
EFP偏心起爆的弹道实验中, 3种偏心起爆成型的EFP均有效击穿距战斗部中心96 m处厚25 mm的方形45钢靶。图 7所示为以瞄准靶心为原点建立坐标系, 3发EFP分别在钢靶上穿孔位置分布。从图 7中可以看出0偏心量时, 由于重力, 风速等自然因素导致弹着点偏离靶心, EFP飞行96 m时偏离靶心的绝对距离为0.08 m。随着相对偏心量的增大, 弹着点偏离靶心的位置逐渐增大, 相对偏心量达到6.7%时弹丸偏离靶心的绝对距离为0.44 m, EFP着靶精度明显降低。3发弹丸击穿钢靶后在靶板上留下的穿孔都接近圆形。弹体穿过钢靶时, 对靶板造成冲塞式破坏, 从靶板坑壁可明显观察到紫铜材质EFP挤凿靶板留下的痕迹, 在靶板背面还观察到由于层裂引起靶板背面破片崩落产生的环形区域。
3. 偏心起爆对EFP成型及飞行特性的数值计算
为从理论上更深刻认识偏心起爆对EFP飞行特性及终点弹道散布的影响, 采用ANSYS/LS-DYNA有限元软件对前述实验中偏心起爆条件下EFP成型过程进行数值模拟, 并通过计算流体力学软件CFX对成型EFP的外流场特性进行数值模拟分析。
3.1 偏心起爆对EFP成型特性的影响
利用Lagrange网格对EFP战斗部计算模型进行划分。为提高分析效率, 在文中取1/2物理模型进行数值计算, 三维有限元计算模型如图 8所示。
药型罩材料为紫铜, 其本构方程选用Johnson-Cook模型, 状态方程为Mie-Grüneisen方程; 主装药为8701炸药, 炸药本构关系的描述选用HIGHEXPLOSIVE BURN形式, 状态方程选用JWL状态方程; 计算中添加*CONTACT_SLIDING_ONLY_PENALTY关键字定义炸药和金属罩之间接触算法, 药型罩内部采用自动面面接触, 从而可以有效地避免网格之间发生穿透、畸形。计算模型参数取自参考文献[7]。
图 9所示为不同相对偏心量下EFP成型特点。0偏心起爆时, 当炸药起爆200μs后, EFP外形基本稳定, 弹丸的飞行速度维持在1 500 m/s左右。偏心起爆时, 爆轰波形相对于装药轴线产生偏斜, 作用于药型罩后造成药型罩的不对称压垮。随着偏心量增大, 弹丸头部和尾翼分别向相反的方向发生偏转:头部对称轴发生逆时针方向偏转, 偏转角度对偏心量变化不敏感; 尾翼对称轴发生顺时针方向偏转, 偏心量对尾翼对称轴偏转的影响程度较大。相对偏心量控制在1.7%以内时, 弹丸外形基本不发生变化。相对偏心量超过3.3%时, 弹丸头部和尾翼的相对偏转角增大速率明显加快。
图 9 不同相对起爆偏心量影响EFP成型Figure 9. Influence of different relative initiation eccentricity on EFP forming炸药起爆后, 由于偏心量存在, 弹丸获得一个垂直于弹轴的横向速度, 运动方向沿偏心起爆点指向装药中心。随着偏心量增加, 弹丸的横向速度效应越来越明显。图 10所示为不同相对偏心量下弹丸横向速度的变化情况。当相对偏心量小于3.3%时, 弹丸横向速度随偏心量变化程度较小, 当相对偏心量为3.3%时, 弹丸获得横向速度仅为6.1 m/s; 相对偏心量超过5%时弹丸的横向速度增加速率明显加快, 当相对偏心量达到6.7%时, 弹丸的横向速度达到17.3 m/s, 经过百米量级中间弹道飞行后弹丸的射偏量增大, 命中目标的准确性概率降低, 这与实验中3种偏心起爆条件下EFP命中96 m处45#钢靶的规律特点吻合较好。
图 10 不同相对偏心量对弹丸横向速度效应的影响Figure 10. Influence of different relative initiation eccentricity on EFP lateral velocity3.2 偏心起爆对EFP空气动力特性影响
为进一步研究偏心起爆条件下成型EFP的空气动力学特性, 将在LS-DYNA中成型的EFP通过计算流体力学软件CFX对弹丸外流场特性进行数值模拟。数值计算基本方程为三维Navier-Stokes方程, 湍流模型采用SST模型, 采用“双时间步”的二阶隐式格式求解非定常过程。气动力计算条件为标准状态, 即大气密度为ρ=1.25 kg/m3, 大气压力为101 325 Pa, 大气温度288.15 K, 此时声速为340.29 m/s。以EFP稳定成型的外形[8]及气动参数作为气动力学参数分析的初始条件。表 1为气动力初始计算状态及基本参数, 表中S为最大迎风面积, L为EFP长度。
表 1 不同工况气动力初始计算状态及基本参数Table 1. The initial calculation state and basic parameters of different aerodynamic conditionsK/% v/(m·s-1) S/cm2 L/cm 0.0 1 500.08 3.02 4.31 3.3 1 496.89 3.53 4.14 5.0 1 487.00 6.37 3.95 6.7 1 475.08 9.15 3.73 图 11所示为利用计算流体力学软件CFX得到不同起爆偏心量下EFP飞行弹道流场分布情况。由数值计算结果可以看出EFP在空气中超音速飞行, 将会在弹丸头部产生弓形脱体正激波。此时弹丸头部区域压力相当高, 造成弹体阻力增大, 速度衰减加快。弧锥结合形药型罩经过爆炸成型后形成前折式尾翼对流经弹体表面气流起到进一步的阻碍作用, 在尾翼前端形成了气体的滞止回流区。随着偏心量的增大, EFP头部和尾翼相对扭曲程度增大, 弹丸飞行过程中所受气动阻力增加, EFP速度降迅速增大, 弹丸的终点毁伤能力下降。
图 11 偏心起爆获得EFP的飞行弹道流场分布Figure 11. The distribution of EFP flow field on flight trajectory从弹丸尾翼流场分布情况可以看出, 随着偏心量增大, 弹丸尾翼不对称性增加:尾翼附近, 气体发生不对称的分离流动, 周围流场分布特点由对称性逐渐发生畸变, 弹体压心向弹体前部偏移; 弹丸上下表面的压强差增大, 产生法向力, 在弹体上形成一垂直弹轴的力矩, 使弹丸在一定攻角范围内做无规则的俯仰运动更加剧烈, 增加了弹体本身的不稳定性, 不利于弹体飞行。弹体尾部由于激波和回流区相互干扰以及尾翼结构的不对称性使弹尾流场分布不规则。当偏心量逐渐增大时, 弹体尾翼流场分布逐渐由圆形向倒三角形变化, 流场分布失去对称性, 弹丸运动不稳定性增加。
尾翼弹丸在空气中运动的稳定性可以用弹丸抵抗外界干扰以保持自身飞行稳定的稳定储备量来衡量。为了定量的认识偏心起爆对EFP飞行稳定性的影响, 引入稳定储备量B来表征不同相对偏心起爆量条件下, EFP在中间弹道飞行阶段的稳定性。稳定储备量B是指弹丸阻力中心与质心位置的相对距离, 即
B=(xpl−xsl)×100%=(Cp−Cs)×100% (1) 式中:
, 其中xp、Cp为弹丸阻力中心到弹丸头部的绝对距离和相对距离(Cp又称弹丸压力中心系数); xs, Cs为弹丸质心到弹丸头部的绝对距离和相对距离; l为弹丸全长; F为弹丸飞行时所受空气阻力; ρ为空气密度; S为最大迎风面积; v为弹丸稳定成型后的飞行速度。其中l、F、ρ、S、v可以有数值计算直接获得, 进而可以求得Cp和B。
对于尾翼弹丸, 要保证其能够在空气中良好的稳定飞行, 其稳定储备量B必须满足:B > 15%[9]。
图 12所示为不同偏心量条件下成型EFP的稳定储备量, 从图中可以看出0偏心量的弹丸具有相当高的的稳定储备量, 为30.29%;当相对偏心量小于5%时, 弹丸的稳定储备量保持在20%以上, 弹丸飞行过程中所受的稳定力矩大于翻转力矩, 即弹丸在飞行过程中抵抗外界干扰能力较强, 能够稳定保持自身飞行稳定。当相对偏心量达到6.7%时, 弹丸稳定储量仅为13.71%, 弹丸飞行过程中的质心和压心距离较小, 飞行过程中抵抗外界干扰能力迅速降低, 弹丸飞行过程中易受外界条件干扰而发生大幅度摆动甚至翻转。EFP在飞行过程中的攻角和摆动角摆动幅值较大而且摆动收敛速度较小, 弹丸攻角长久偏离平衡位置, 速度降增大。
图 12 不同相对偏心量的弹丸的稳定储备量Figure 12. The stabilization storage of projectile with different relative initiation eccentricity综上所述, 一方面偏心起爆使EFP获得垂直于弹轴的横向速度, 影响弹道射偏量的大小, 降低了对目标的打击精度; 另一方面偏心起爆通过影响EFP对称成型, 改变弹丸在飞行过程中流场对称性, 使弹丸在飞行过程中的不稳定性增加, 弹丸速度降增大, 减弱了EFP对终点目标的毁伤效果。
4. 结论
本文中利用数值模拟分析不同起爆偏心量下成型EFP的空气动力学特性, 得出如下结论:
(1) 偏心起爆时, 爆轰波对药型罩的不对称压垮导致EFP头部和尾翼对称轴线相对偏斜, 弹丸获得垂直于弹轴的横向速度。随着偏心量的增大, EFP横向速度效应明显, 弹道射偏量增大, 降低了对目标的打击精度。
(2) EFP飞行弹道实验和数值计算结果表明:相对偏心量小于3.3%时, EFP在网靶穿孔接近圆形, 说明弹丸在此偏心量内产生的不对称变形对EFP飞行稳定基本不发生影响; 相对偏心量位于3.3%~ 6.7%时, 弹丸不对称变形程度增大, 弹体周围流场分布逐渐失去对称性, 当相对偏心量达到6.7%时, EFP在一路网靶上留下的穿孔接近弹丸纵向截面形状, 说明弹丸在飞行过程中发生较大幅值的摆动, 弹丸速度衰减增大, 降低了EFP对目标的终点毁伤能力。因此, EFP起爆的相对偏心量应当控制在3.3%以内。
(3) 利用偏心起爆条件下成型EFP的空气动力学数值计算结果和飞行弹道试验结果有效分析了偏心起爆对EFP飞行弹道稳定性的影响, 为评价EFP飞行弹道的稳定性提供了一种简单有效的方法, 研究结果为EFP战斗部起爆参数设置以及对目标的精确打击提供有益参考。
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表 1 近年氢气泄漏爆炸事故
Table 1. Recent hydrogen gas leak explosion incidents
事故时间 事故地点 事故原因 事故后果 2018年3月12日 中国江西省九江市一石化企业 柴油加氢装置原料缓冲罐超压爆炸着火 2人死亡，1人受伤
直接经济损失约338万元2019年5月23日 韩国江原道江陵市 在水电解氢气试验的过程中，因操作失误而导致爆炸 2人死亡，6人受伤 2019年6月1日 美国加州圣塔克拉拉一化工厂 储氢罐发生泄漏爆炸 无人伤亡，经济损失数万美元，
当地氢燃料供应被迫中断2019年6月 挪威桑维卡一合营加氢站 高压储氢罐一特殊插头装配错误 2人受伤
经济损失约2亿欧元2019年12月 威斯康星州沃基工厂 储氢区发生爆炸起火 1人受伤 2020年1月14日 中国珠海长炼石化设备有限公司 重整加氢装置预加单元发生闪爆 无人伤亡
直接经济损失198万元2020年4月 美国北卡州朗维尤一氢燃料工厂 加氢站爆炸 无人伤亡，损失数百美元 2021年8月4日 中国辽宁沈阳经济开发区
一企业院加氢站内卸车柱上软管破裂导致氢气罐爆燃 无人伤亡
直接经济损失1475 万元2021年9月11日 湖南省永兴镇马田镇 个人私自利用液化石油气钢瓶制氢，
导致其制氢罐发生爆炸1人死亡，1人受伤
直接经济损失超93万元2022年4月24日 中国石化齐鲁石化胜利炼油厂 氢气泄漏着火 无人伤亡
直接经济损失180万元
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研究人员 研究对象 实验装置 抑爆剂 结论 刘原一等[21] H2/CO 2 m长不锈钢
管道N2、CO2 CO2对混合气爆燃特性的影响强于N2，主要表现在燃爆下限和压力波传播上 Yan等[22] H2/CO 球形爆炸室 N2、CO2 随着CO2和N2含量的增加，绝热火焰温度、热扩散系数和活性自由基摩尔分数不断降低，
使层流燃烧速度降低。其次，CO2抑制氢气爆炸压力比N2更有效Li等[23] H2 肥皂泡装置 He、Ar、
N2、CO2影响热扩散系数、绝热火焰温度、层流燃烧速度和热膨胀率的降低排序：He>Ar>N2>CO2，且N2不存在第三体效应，第三体效应：CO2>Ar>He，因此，CO2是缓解氢气爆炸较有效的添加物 Wei等[24] H2 定容燃烧弹 Ar、N2、CO2 不活泼气体的稀释减缓了火焰在燃烧室中的传播。抑制作用由小到大依次是Ar、N2、CO2 Wang等[25] H2 7.3 L圆筒
封闭容器Ar、N2、CO2 CO2比热高于N2和Ar，且CO2对能量损失的增加最显著，N2和Ar次之，
因此CO2的抑制效果优于Ar和N2邹颖等[26] H2 20L爆炸球 N2、CO2 CO2在爆炸压力及压力增长率方面的抑制效果优于N2 Wang等[27] H2/LPG 20L爆炸球 N2、CO2 比较了爆炸压力、自由基的摩尔分数和产生速率，得出CO2抑制作用优于N2。
其中N2主要起到了物理抑制作用，而CO2还发挥了化学抑制作用Chang等[28] H2 20 L标准球形
爆炸容器中N2、CO2 N2、CO2气体稀释的抑制作用可以平衡湍流的促进作用。在某些情况下，由于CO2的分子量较大，其对爆炸行为的增强作用比N2射流更明显 Wu等[29] H2 圆柱形停滞室 N2、CO2 从火焰长度减速比的比较可知，CO2与N2的减缓效果非常接近 Zhang等[30] H2 爆炸管道 N2、CO2 比较了爆炸压力、燃烧持续时间和火焰传播等爆炸参数，验证了CO2比N2抑制效果强。
此外，多层爆炸抑制对不同侧缓蚀剂的抑制效果最好
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当量比 绝热火焰温度/K He Ar N2 CO2 0.6 2764.9 2764.9 2222.5 1645.6 0.8 2988.8 2988.8 2566.2 1955.6 1.0 3090.1 3090.1 2760.8 2464.1 1.4 3069.8 3069.8 2705.8 2076.7 2.0 2853.0 2853.0 2478.2 1865.4
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表 4 卤代烃与活化中心化学反应参数对比[77]
Table 4. Comparison of halogenated hydrocarbons and activation center chemical reaction parameters[77]
反应过程 活化能Ea/(kJ∙mol−1) 反应速率常数K/(cm³∙mol−1∙s−1) CHF3+OH·→CF3+H2O 19.10 2.71×10-16 CHClF2+OH·→CClF2+ H2O 12.72 4.60×10-15 CH2FCF3+OH·→CHFCF3+H2O 12.80 4.16×10-15 C2HF5+OH·→C2F5+H2O 13.80 1.90×10-15
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