1) regenerative cooling channel
再生冷却通道
1.
Effect of aspect ratio on heat transfer and fluid flow in regenerative cooling channel of liquid rocket engine thrust chamber;
保持再生冷却通道个数及冷却工质进口流量不变,通过改变通道肋壁厚度来改变冷却通道深宽比,研究不同深宽比对推力室壁面再生冷却效果的影响规律。
2) regenerative cooling
再生冷却
1.
Numerical study on coupled heat transfer of thrust chamber with regenerative cooling;
再生冷却推力室耦合传热数值模拟
2.
The failure of regenerative cooling due to propellant coking in a liquid rocket engine was investigated by numerically analyzing the flow and heat transfer in a mini cooling channel with artificial roughness.
针对液体火箭发动机再生冷却中的结焦问题,对含粗糙元微小冷却通道内的流动和换热进行数值研究。
3.
To understand and compare different heat transfer characteristics of regenerative cooling in axi-symmetrical nozzle and round to square nozzle(RS nozzle),computational models of axi-symmetrical nozzle(thrust chamber) and RS nozzle(thrust chamber) were established.
为了解和比较轴对称喷管与圆转方喷管不同的再生冷却换热特性,分别对轴对称喷管(推力室)与圆转方喷管(推力室)建立计算模型,通过数值模拟的方法重点研究和比较了轴对称喷管与圆转方喷管的流场、壁面热流密度和温度分布、冷却剂温升和冷却通道压降等换热特性。
3) cooling passage
冷却通道
1.
Based on the RSM,the optimization of the blade cooling passage is implemented to minimize the maximum temperature of the blade,the facet average temperature of the blade surface and the total pressure loss.
以冷却通道肋的位置为设计变量,采用拉丁超立方抽样在变量设计空间里选取样本点,根据样本点建立叶片计算模型,采用流-热耦合分析方法得到叶片气动与传热性能参数,拟合得到叶片壁面最高温度、平均温度和总压损失关于设计变量的四阶响应面近似模型。
4) regenerative cooling
再生冷却<火>
5) blanket cooling
再生区冷却
6) Cooling-channel
冷却液通道
补充资料：部分型房室共同通道
部分型房室共同通道
partial atrioventricular canal
见“部分型原发孔型房间隔缺损”。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条