Regenerative cooling technology is one of the key technologies to thermally protect scramjet chamber.

再生冷卻技術是超燃沖壓發(fā)動機燃燒室熱防護的關鍵技術。

In this paper, the conjugative heat transfer in a regenerative cooling structure is investigated numerically by using the FEM and CFD software.

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Regenerative cooling is the most widely used method of cooling a combustion chamber and is accomplished by flowing high-velocity coolant over the back side of the chamber hot gas wall to convectively cool the hot gas liner.

再生冷卻是最廣泛使用的方法冷卻燃燒室和是通過流動的高冷卻速度超過回到會議廳一側的熱氣體墻convectively冷卻熱氣體班輪淫秽啪啪啪黄色免费观看网站。

In the first chapter ,the thermal environment of scramjet and the inevitablility of regeneratively cooled scramjet,the history and state of art of the studies on regeneratively cooled scramjet and regenerative cooling technology were described comprehensively.

本文第一章介紹了超燃沖壓發(fā)動機燃燒室熱環(huán)境和對發(fā)動機燃燒室采取再生冷卻的必要性，研究了超燃沖壓發(fā)動機再生冷卻技術的發(fā)展和現(xiàn)狀一级毛片和暴力，并介紹了本文的研究內容人妻少妇一区二区三区在线。

Through the studies on the regeneratively cooled scramjet structure of tomorrow's advanced propulsion system of this paper, one thermal evaluation tool was developed. This dissertation provided the necessary means for the design of regenerative cooling channels of the scramjet.

通過本文圍繞未來先進推進系統(tǒng)——超燃沖壓發(fā)動機燃燒室再生冷卻結構的研究，發(fā)展了熱分析計算方法国内精品久久久久久不卡影院，初步建立了冷卻通道的設計方法和工具强力打造免费在线。

The internal regenerative cooling is a new cooling technique of the thrust chamber.

一、內部再生冷卻的物理描述內部再生冷卻是一種新的推力室冷卻技術色哟哟天天操。

For a regenerative cooling system, the coolant supply pressure must be sufficient to flow the coolant through the narrow cooling passages at high velocities.

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As the chamber pressure increases, the only cooling methods that can satisfy the requirements are regenerative cooling only or regenerative cooling combined with film cooling.

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Dump cooling , which is similar to regenerative cooling because the coolant flows through small passages over the back side of the combustion chamber wall.

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The study shows that regenerative cooling can meet the airframe/engine integrated cooling requirements in the range of flight Mach numbers from 6 to 12, as fuel injection concept (injector locations and injection fuel mass flow) is set properly, and hydrogen temperature at the exit of cooling passage is allowed to be a relative higher value.

研究表明日本AAAA三级片，在馬赫數(shù)6～12的范圍內，通過適當配置燃料噴射方案和提高冷卻通道出口冷卻劑的溫度免费日韩h视频，采用再生冷卻方式能夠滿足機體／發(fā)動機一體化高超聲速飛行器的冷卻需求一级黄色视频女人射精。