| タイトル | Water cooling system for an air-breathing hypersonic test vehicle |
| 著者（英） | Dziedzic, William M.; Petley, Dennis H. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1993-06-01 |
| 言語 | eng |
| 内容記述 | This study provides concepts for hypersonic experimental scramjet test vehicles which have low cost and low risk. Cryogenic hydrogen is used as the fuel and coolant. Secondary water cooling systems were designed. Three concepts are shown: an all hydrogen cooling system, a secondary open loop water cooled system, and a secondary closed loop water cooled system. The open loop concept uses high pressure helium (15,000 psi) to drive water through the cooling system while maintaining the pressure in the water tank. The water flows through the turbine side of the turbopump to pump hydrogen fuel. The water is then allowed to vent. In the closed loop concept high pressure, room temperature, compressed liquid water is circulated. In flight water pressure is limited to 6000 psi by venting some of the water. Water is circulated through cooling channels via an ejector which uses high pressure gas to drive a water jet. The cooling systems are presented along with finite difference steady-state and transient analysis results. The results from this study indicate that water used as a secondary coolant can be designed to increase experimental test time, produce minimum venting of fluid and reduce overall development cost. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 93A49831
AIAA PAPER 93-1984 |
| 権利 | Copyright |
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