| Citation: | ZHENG Shangzhe, CHEN Yuchun, WANG Zhihua, et al. Influence of helium cycle flow ratio on SABRE4 design point hydrogen flow rate[J]. Journal of Aerospace Power, 2024, 39（11）：20220774 doi: 10.13224/j.cnki.jasp.20220774
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The thermodynamic calculation model based on component method for synergistic air-breathing rocket engine (SABRE) design point was established. The minimum hydrogen flow rate required by the engine was analyzed. To save the hydrogen flow rate, two simplified schemes of SABRE4 were proposed by adding two helium branches based on the SABRE3 configuration. Combining two simplified schemes, SABRE4 scheme was proposed. The influences of the helium branches flow ratios on engine design point parameters and hydrogen flow rate were analyzed. The results showed that: the minimum hydrogen flow rate was proportional to the helium flow rate through Heat Exchanger 3. The less helium flow rate through Heat Exchanger 3 indicated the less hydrogen flow rate required. A smaller branch one flow ratio one was conductive to reducing the hydrogen flow rate, meanwhile the required helium compressor pressure ratio was increased. A smaller branch two flow ratio two was conductive to reducing the hydrogen flow rate and the required helium compressor pressure ratio. The decrease of flow ratio one and flow ratio two caused heat exchangers to approach their limits. When the Heat Exchanger 1 inlet helium temperature was lower than 310 K and the pressure ratio of helium compressor was lower than 11.0, the minimum hydrogen flow rate of SABRE4 was 83.3% of SABRE3.
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