轻质钛合金喷管在氢氧发动机上的应用研究

Application of lightweight titanium alloy nozzle in LOX-LH_2 rocket engine

为降低发动机质量,提高其推重比,将轻质高温钛合金TA15用于液氢液氧发动机推力室喷管,模拟了全尺寸再生冷却钛合金喷管的工作特性,设计了TA15钛合金铣槽式再生冷却缩尺喷管,采用扩散焊工艺生产了缩尺喷管试验件,成功进行了热试验。试验结果表明钛合金氢再生冷却缩尺喷管在高温富氢燃气环境下能够短时间安全稳定工作,传热可靠,最高气壁温达1 017 K,冷却通道流阻及氢温升实测值与计算结果基本一致。最后简要介绍了钛合金的氢脆特性。

To reduce the mass and increase the thrust mass ratio of LOX-LH2 rocket engine, the lightweight titanium alloy TA15 was researched for the thrust chamber nozzle of the engine. In the research process, the working characteristics of full-size hydrogen regeneration cooling nozzle of titanium alloy was simulated, the reduced scale TA 15 regeneration cooling nozzle with milling groove was designed, and then the diffusion welding technology was adopted to produce a reduced scale nozzle specimen. The fire test of the specimen was successful. The test results show that the titanium alloy hydrogen regenerative cooling reduced scale nozzle can work safely and reliably in the high temperature environment with hydrogen-rich gas in short time, whose maximum gas wall temperature can reach 1 017 K. The measured values and the calculated values of flow resistance and hydrogen temperature rise in the cooling channel are in agreement. At the end of the paper, the embrittlement characteristics of titanium alloy in hydrogen are introduced.