ロケットターボポンプ用タービンの翼損失に関するパラメータスタディ

Material type: 文書・図像類

Author: 瀧田, 純也ほか

Publisher: 宇宙航空研究開発機構(JAXA)

Publication date: 2013-01-31

Material Format: Digital

Capacity, size, etc.: -

NDC: -

View All

Notes on use

Note (General)：: Due to its special specification, rocket turbopump turbine blades have higher loading and its aspect ratio is extremely low. In such a situation, it i...

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 Institutional Repositories DataBase(IRDB)(Institutional Repository) is linked at the site of Institutional Repositories DataBase(IRDB)(Institutional Repository).
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: ロケットターボポンプ用タービンの翼損失に関するパラメータスタディ
Author/Editor: 瀧田, 純也
福田, 太郎
宇山, 遼一
船﨑, 健一
内海, 政春
Takida, Junya
Fukuda, Taro
Uyama, Ryoichi
Funazaki, Kenichi
Uchiumi, Masaharu
Author Heading: 瀧田, 純也
福田, 太郎
宇山, 遼一
船﨑, 健一
内海, 政春
Takida, Junya
Fukuda, Taro
Uyama, Ryoichi
Funazaki, Kenichi
Uchiumi, Masaharu
Publication, Distribution, etc.: 宇宙航空研究開発機構(JAXA)
Publication Date: 2013-01-31
Publication Date (W3CDTF): 2013-01-31
Alternative Title: Parameter Study on Blade Losses of a Rocket Turbopump Turbine
Periodical title: 宇宙航空研究開発機構研究開発資料 = JAXA Research and Development Memorandum
No. or year of volume/issue: JAXA-RM-12-008
Volume: JAXA-RM-12-008
Pages: 1-9
ISSN (Periodical Title): ISSN : 1349-1121
Text Language Code: jpn
Subject Heading: AMDC+KO Loss Model
Blade Aspect Ratio
Craig & Cox Loss Model
Zweifel factor
Target Audience: 一般
Note (General): Due to its special specification, rocket turbopump turbine blades have higher loading and its aspect ratio is extremely low. In such a situation, it is difficult to predict turbine efficiency accurately in system design phase of rocket engine. The purpose of the present work is to evaluate the accuracy of existing one dimensional loss model. By using the steady three dimensional CFD analyses, parametric studies against the major design variables such as tip clearance, blade loading, blade aspcet ratio, were carried out. These simulation results were compared with the results that were also obtained by using the existing one dimensional loss models. The results clarified the cause of the reduction of accuracy of one-dimensional prediction of turbine efficiency. The one-dimensional loss model was found to underestimate the loss under the condition of a blade with a low aspect ratio. From comparison between the existing one-dimensional loss models, it was also found that the "Craig & Cox model" could reproduce the tendency for blade loading correctly.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA0065515000
レポート番号: JAXA-RM-12-008
Access Restrictions: 限定公開
Periodical Title (NCID): AA11983593
https://ci.nii.ac.jp/ncid/AA11983593
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