深冷涡喷火箭组合循环发动机初步分析

Primary analysis of deep cooled turbojet liquid rocket engine combined cycle

关键词:  运载器  深冷涡喷火箭组合发动机  低温推进剂火箭发动机  发动机性能计算

Key words:  Carrier  Deep cooled turbojet liquid rocket engine  Cryogenic propellant rocket engine  Engine performance calculatio?

摘要:

为了对国外近年来提出的KLIN循环发动机 (深冷涡喷发动机DCTJ +火箭发动机LRE)的可实现性进行分析验证 ,估算了深冷涡喷 /火箭组合循环发动机的特性 ,结合国外文献的研究 ,认为KLIN循环发动机有效载荷系数高、循环效率高、发展风险小、技术上可近期实现 ,极具开发和应用前景。

Abstract:

In order to verify the realization possibility of the combined propulsion known as KLIN cycle,which consist of a thermally integrated deep cooled turbojet and liquid rocket engine,a primary performance assess was performed From the assessed results and the references, it can be concluded that the KLIN cycle provides a high payload capability of the launcher, and it can be realized in the near term without a need for large leaps in technology Furthermore, KLIN cycle technology is full within current industrial capability and can be completely ground tested, thereby minimizing development risk and cost