| Publication Date |
1982 |
| Personal Author |
Suzuki, M.; Kamijyo, K.; Watanabe, Y.; Mori, M. |
| Page Count |
31 |
| Abstract |
A study of the LOX turbopump rotating shaft seals was performed in connection with the research and development of the LOX turbopump. The seal performance and durability of the rotating shaft seals of the LOX turbopump are described. The shaft seal system of the LOX turbopump consists of a liquid oxygen seal (a face-contact metal bellows mechanical seal), a turbine-drive hot gas seal (a segmented hydrodynamic circumferential seal), and a helium purge-gas seal (a double segmented hydrodynamic circumferential seal). The operating conditions are as follows; rotating speed is 16,500 rpm, and sealed fluid pressures and temperatures are 15 ata and 90 K for the mechanical seal, 3 ata and 700 K for the turbine-drive hot gas seal, and 3 ata and ambient for the helium purge-gas respectively. The performance of the LOX turbopump shaft seal system was satisfactory in a series of LOX turbopump and LOX/LH2 turbopump system tests. The wear amount of the seals after total test time of about 2,000 sec. was acceptable. |
| Keywords |
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| Source Agency |
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| NTIS Subject Category |
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| Corporate Authors |
National Aerospace Lab., Tokyo (Japan).; National Aeronautics and Space Administration, Washington, DC. |
| Supplemental Notes |
In Japanese; English Summary. |
| Document Type |
Technical Report |
| NTIS Issue Number |
198313 |
