液酸ターボポンプ・軸シールのシール性能と耐久性

• Material Type: 文書・図像類
• Title: 液酸ターボポンプ・軸シールのシール性能と耐久性
• Author/Editor: 鈴木, 峰男; 上條, 謙二郎; 渡辺, 義明; 森, 雅裕; SUZUKI, Mineo; KAMIJO, Kenjiro; WATANABE, Yoshiaki; MORI, Masahiro
• Author Heading: 鈴木, 峰男; 上條, 謙二郎; 渡辺, 義明; 森, 雅裕; SUZUKI, Mineo; KAMIJO, Kenjiro; WATANABE, Yoshiaki; MORI, Masahiro
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1982-07
• Publication Date (W3CDTF): 1982-07
• Alternative Title: SEAL PERFORMANCE AND DURABILITY OF ROTATING SHAFT SEALS OF LIQUID OXYGEN TURBOPUMP
• Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-717
• No. or year of volume/issue: 717
• Volume: 717
• Pages: 30-
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Target Audience: 一般
• Note (General): The development of a 10-ton thrust liquid oxygen(LOX) and liquid hydrogen(LH2) rocket engine(LE-5) has been conducted by the National Space Development Agency of Japan(NASDA). National Aerospace Labpratory of Japan(NAL) has carried out research and development of the turbopumps for the LE-5 engine in co-operation with NASDA. A study of the LOX turbopump rotating shaft seals has been performed in connection with the reserch and development of the LOX turbopump. This report describes the seal performance and durability of the rotating shaft seals of the LOX turbopump. The shaft seal system of the LOX trubopump 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 3ata and ambient for the helium purge-gas seal, respectively. The performance of the LOX turbopump shaft seal system has been 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. The durability tests of the seals were carried out using a seal tester, in which the structure of the hot gas seal was change to a double seal. The durability-test conditions were the same those for the LOX turbopump tests except the starting and stopping peripds. Through all the test duration of about 7,000 sec., the performance of the seals was satisfactory. The wear depth of the seals was less than 10μm for carbon nose-piece of mechanical face seal and 15μm for the carbon seal rings of segmented circumferential seals, respectively. From these test results, it was confirmed that the seal performance, durability and reliability of the rotating shaft seals satisfied the requirements for application to the LOX turbopump.; 資料番号: NALTR0717000; レポート番号: NAL TR-717
• Access Restrictions: 限定公開
• Data Provider (Database): 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）; https://irdb.nii.ac.jp
• Original Data Provider (Database): 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