| Citation: | HOU Ruifeng, LI Longfei, CHEN Jianhua, et al. Adaptability of cooling structure schemes of liquid propellant rocket engine thrust chamber under different pressures[J]. Journal of Aerospace Power, 2022, 37（12）：2797-2806 doi: 10.13224/j.cnki.jasp.20220378
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In order to accurately evaluate the effect of different cooling schemes on the heat transfer characteristics of thrust chamber of high-pressure liquid oxygen and hydrocarbon rocket engine, a complete model combining regenerative channel, liquid film shield, thermal barrier coating and radiation heat transfer was established. The Ievlev semi-empirical model was adopted for calculation of convection on gas wall. The Shruvik safety margin evaluation criterion was used in analysis. The radial direction multi-layer temperature and heat flux of the thrust chamber were calculated. Based on a large thrust liquid oxygen and kerosene rocket engine, the upper limit of heat transfer capacity of different cooling schemes was studied, and the influence of different thrust chamber pressures on cooling design was analyzed. Results showed that, thrust chamber can mainly rely on regenerative cooling technology to meet the cooling requirements at 12 MPa or below; film cooling slots should be further used at 16 MPa or below; thermal barrier coating should be further installed at 18 MPa or below; several intensive cooling measures must be adopted at 20 MPa or higher.
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