LIQUID HYDROGEN TRANSFER TEST REPORT,
Abstract
The feasibility of transferring liquid hydrogen at high flow rates was verified. The transfer rate for this test was in the range of 2500-3000 G.P.M. into an ambient (temperature) pipe line and missile tank. Pipe line bow did not exceed six (6) inches at the beginning of transfer and returned to approximately the original position shortly afterwards. This bow compares favorably with our previous experience flowing liquid oxygen at rates up to 1500 GPM where the maximum bowing reached zero (0) to two (2) inches on the same type transfer system. Missile tank top pressure reached a peak of 24 PSIG approximately 6.5 seconds after transfer was initiated. It decayed thereafter to a minimum of 1 PSIG at termination of flow. The integrity of the WS-315A designed seals and joints were verified at liquid hydrogen temperatures and nominal pressures (not exceeding 40 PSIG). The standard ASA raised face (Serrated) flanges using Kel-F gaskets proved adequate as a sealing means on the pipe line configuration. The flexatallic seals used on the vent valves, emergency drain valve and the main lox tank exit cone all provided satisfactory sealing at liquid hydrogen temperatures. The applicability of cryogenic design practices in relation to valves was demonstrated.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 07, 1960
- Accession Number
- AD0608908
Entities
People
- D. R. Brincka
Organizations
- Douglas