ロケット用液体酸素ポンプの過渡特性に関する実験的研究(第1報)

Material type: 文書・図像類

Author: 志村, 隆ほか

Publisher: 航空宇宙技術研究所

Publication date: 1979-04

Material Format: Digital

Capacity, size, etc.: -

NDC: -

View All

Notes on use

Note (General)：: Liquid rocket engine thrust buildup follows turbopump speed buildup, which occurs in 1～3 seconds after the engine starts. In this rapid start conditio...

Search by Bookstore

Holdings of Libraries in Japan

This page shows libraries in Japan other than the National Diet Library that hold the material.

List of Cooperating Institutions and Databases

Please contact your local library for information on how to use materials or whether it is possible to request materials from the holding libraries.

other

JAXA Repository
Digital
You can check the holdings of institutions and databases with which 学術機関リポジトリデータベース（IRDB）（機関リポジトリ） is linked at the site of 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）.
JAXA Repository

Search by Bookstore

Bibliographic Record

You can check the details of this material, its authority (keywords that refer to materials on the same subject, author's name, etc.), etc.

Digital

Material Type: 文書・図像類
Title: ロケット用液体酸素ポンプの過渡特性に関する実験的研究(第1報)
Author/Editor: 志村, 隆
上條, 謙二郎
橋本, 亮平
渡辺, 光男
渡辺, 義明
長谷川, 敏
SHIMURA, Takashi
KAMIJO, Kenjiro
HASHIMOTO, Ryohei
WATANABE, Mitsuo
WATANABE, Yoshiaki
HASEGAWA, Satoshi
Author Heading: 志村, 隆
上條, 謙二郎
橋本, 亮平
渡辺, 光男
渡辺, 義明
長谷川, 敏
SHIMURA, Takashi
KAMIJO, Kenjiro
HASHIMOTO, Ryohei
WATANABE, Mitsuo
WATANABE, Yoshiaki
HASEGAWA, Satoshi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1979-04
Publication Date (W3CDTF): 1979-04
Alternative Title: Experiments on Transient Characteristics of A Small High Speed Liquid Oxygen Pump(1st Report)
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-570
No. or year of volume/issue: 570
Volume: 570
Pages: 25-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): Liquid rocket engine thrust buildup follows turbopump speed buildup, which occurs in 1～3 seconds after the engine starts. In this rapid start condition, the dynamic characteristics of the turbopumps are thought to deviate considerably from their steady state characteristics. Therefore, it is very important to know the transient characteristics of the turbopumps, in order to make sure that the engine start transient is clear. In the present study, experiments with a small high speed liquid oxygen pump were performed, in order to investigate the pump transient characteristics in the rapid start. The pump tested was designed for 10 ton thrust LOX/LH2 rocket engine. The experiments were made using degassified water and liquid nitrogen, instead of liquid oxygen. Visual observations of cavitation in the pump inducer were performed, using a transparent inducer casing. The following items:transient characteristics of pump head, pump shaft power, accelerating head loss in the pump suction line, pump axial thrust, and pump chilldown, were examined in these experiments. The major results of the present study are as follows: (1)The pump head in the rapid starts tended to be higher than the steady state head. (2)The excess of the head in the rapid starts depended upon the initial flow rate. (3)The pump efficiency in the rapid starts was lower than the steady state efficiency. In addition, we were able to show the relationship between the pump inlet pressure decrease, due to the rapid start, and the cavitation occurrence in the pump inducer.
資料番号: NALTR0570000
レポート番号: NAL TR-570
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44824&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44824&item_no=1&attribute_id=31&file_no=1
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