<論文>液水/液酸ターボポンプの実験 I. ポンプ

概要

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The tests were conducted to assess the performance characteristics of a turbopump for a liquid-hydrogen, liquid-oxygen rocket engine of 7000 kg-thrust level. The general design and the production of turbo-pump had been performed in 1975 and 1976 fiscal year respectively, and then since August of 1977, 10 running tests were carried out in Noshiro Testing Center of ISAS. Data were obtained enough to estimate the performance characteristics of pumps, and then the results almost satisfies the goal intended in design. Although the trubopump presented here is designed as a flight-type, the pumps were tested first to assess their performance characteristics by means that the turbines to drive pumps were driven by nitrogen or hydrogen gas at room temperature in place of combustion gas. Both liquid-hydrogen and liquid-oxygen pumps are a single stage centirfugal-flow type with helical inducer. The report about the turbine is to be published after hot running tests using a combustion gas generator.
宇宙航空研究開発機構の論文