タイトル(掲載誌)航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-653
一般注記The development of a 10-ton thrust liquid oxygen and liquid hydrogen (LOX and LH2) rocket engine is under way at the National Space Development Agency. In advance of the development of a liquid hydrogen turbopump, the National Aerospace Laboratory carried out study and development of a face-contact, bellows mechanical seal for a liquid hydrogen turbopump in co-operation with the National Space Development Agency. The present report describes the fundamental experiments of the mechanical seal (seal diameter:58.5mm) for liquid nitrogen and liquid hydrogen and the development of the mechanical seal for a liquid hydrogen turbopump (seal diameter:43.2mm). The developed mechanical seal has two features. One is a new type of seal nosepiece, which reduces the sealing face distortion at low temperature and high pressure. It results in a small amount of seal leakage and wear, and a low starting torque. The other feature is a new type vibration damper made of Teflon sheets. Th sheets are fixed in a nosepiece in order to prevent fluttering of the seal nosepiece during the rapid start or stop of a turbopump. Numerous tests were performed to clarify the seal performance. It was confirmed that the developed turbopump mechanical seal satisfied almost all requirements for application to a turbopump: seal leakage, wear life, reliability, starting torqe ,etc.. A long time test of 66 minutes in the condition (fluid pressure: 15 ata, rotating speed: 50,000 rpm, liquid hydrogen coolant flow: 0.4l/sec) was successful. The seal performances of the developed turbopump mechanical seal were as follows: liquid hydrogen leakage in steady state condition was 7.7~19.2cc/min. Wear of seal components after a long time run were 0~8μm in carbon face piece and 0.1μm (maximum) in chromium plate on rotating ring.
資料番号: NALTR0653000
レポート番号: NAL TR-653
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース(IRDB)(機関リポジトリ)
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ