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A Study of Side Loads in Rocket Nozzles during Startup and Shutdown Transients

Research Project

Project/Area Number 12450075
Research Category

Grant-in-Aid for Scientific Research (B)

Allocation TypeSingle-year Grants
Section一般
Research Field Fluid engineering
Research InstitutionOsaka University

Principal Investigator

TSUJIMOTO Yoshinobu  Osaka University, Graduate School of Engineering Science, Professor, 基礎工学研究科, 教授 (50112024)

Co-Investigator(Kenkyū-buntansha) YOKOTA Kazuhiko  Nagoya Institute of Technology, Mechanical Engineering, Associate Professor, 機械工学部, 助教授 (70260635)
SAKAZUME Norio  National Space Development Agency of Japan, Office of Space Transportation Systems, Senior Engineer, 宇宙輸送システム本部, 主任開発部員
YOSHIDA Yoshiki  Osaka University, Graduate School of Engineering Science, Associate Professor, 基礎工学研究科, 助教授 (80240836)
Project Period (FY) 2000 – 2001
Project Status Completed (Fiscal Year 2001)
Budget Amount *help
¥7,100,000 (Direct Cost: ¥7,100,000)
Fiscal Year 2001: ¥1,600,000 (Direct Cost: ¥1,600,000)
Fiscal Year 2000: ¥5,500,000 (Direct Cost: ¥5,500,000)
KeywordsMach Disk / Cap Shock / Free Shock Separation / Restricted Shock Separation / Trapped Vortex / Small step for film cooling / CTP nozzle / Three dimensional CFD / 2次元ノズル / 数値シミュレーション / 超音速風洞実験 / 流体振動 / 横推力 / キャップショック / FSS / RSS
Research Abstract

Recently, the large side loads is observed in the latest rocket nozzles during start-up and shutdown transient. The objective of this study is to clarify the mechanisms of producing the side loads. In this study, both experimental and numerical studies are performed. In the numerical studies, both the three-dimensional and two-dimensional simulations are performed. The results of three-dimensional simulations show that the simultaneous occurrence of the Free Shock Separation (FSS) and the Restricted Shock Separation (RSS) produces the large side load. In the two-dimensional simulations, the flow field is replaced with a two-dimensional planer field so that it is possible to observe the asymmetric flow patterns. The results show that the small step for film cooling gives great effect on the side load. At the steps, the separation points are trapped in the certain range of pressure ratio, and rapidly shifts to the nozzle exit at the certa(in press)ure ratio. This shift occurs asymmetrically and it produces the large side load. The experimental studies are performed by using the two-dimensional supersonic nozzles. The results show that the asymmetric flow patterns are produced by the instability of shear layer in the downstream of shock wave. But in two-dimensional nozzles, the flow is separated from sides of the test section, and the affects the separation pattern on the nozzle wall.

Report

(3 results)
  • 2001 Annual Research Report   Final Research Report Summary
  • 2000 Annual Research Report
  • Research Products

    (8 results)

All Other

All Publications (8 results)

  • [Publications] 森田良, 米澤宏一, 横田和彦, 辻本良信, 坂爪則夫: "2次元CFDによるロケットノズルに生じる非定常横推力に関する研究"日本機械学会関西支部第76期定時総会講演会講演論文集. 014-1. 13-5-13-6 (2001)

    • Description
      「研究成果報告書概要(和文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] 米澤宏一, 森田良, 横田和彦, 辻本良信, 坂爪則夫: "3次元CFDを用いたロケットノズルに生じる非定常横推力に関する研究"日本機械学会関西支部第76期定時総会講演会講演論文集. 014-1. 13-9-13-10 (2001)

    • Description
      「研究成果報告書概要(和文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] 米澤宏一, 横田和彦, 辻本良信, 坂爪則夫: "ロケットノズルに生じる横推力に関する3次元非定常CFD"第10回スペース・エンジニアリング・コンファレンス講演論文集. 01-68. 35-41 (2002)

    • Description
      「研究成果報告書概要(和文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] 米澤宏一, 横田和彦, 渡邉泰秀, 坂爪則夫, 辻本良信, 安部隆士: "ロケットノズルに生じる横推力"日本機械学会関西支部第77期定時総会講演会講演論文集. 024-1. 10-9-10-10 (2002)

    • Description
      「研究成果報告書概要(和文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] Koichi YONEZAWA, Kazuhiko YOKOTA, Yasuhide WATANABE, Yoshinobu TSUJIMOTO, Takashi ABE: "2-D Numerical simulation of Side Loads in Rocket Nozzles"Proceedings of 23rd International Symposium on Space Technology and Science, ISTS-e-27.

    • Description
      「研究成果報告書概要(和文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] Koichi YONEZAWA, Kazuhiko YOKOTA, Yoshinobu TSUJIMOTO, Norio SAKAZUME, Yasuhide WATANABE: "Three Dimensional Unsteady Flow Simulation of Compressed Truncated Perfect Nozzles"AIAA Paper 2002-1251.

    • Description
      「研究成果報告書概要(和文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] Koichi YONEZAWA, Kazuhiko YOKOTA, Yasuhide WATANABE, Yoshinobu TSUJIMOTO, Takashi ABE: "2-D Numerical simulation of Side Loads in Rocket Nozzles"Proceedings of 23rd International Symposium on Space Technology and Science. ISTS-e-27. (2002)

    • Description
      「研究成果報告書概要(欧文)」より
    • Related Report
      2001 Final Research Report Summary
  • [Publications] Koichi YONEZAWA, Kazuhiko YOKOTA, Yoshinobu TSUJIMOTO, Norio SAKAZUME, Yasuhide WATANABE: "Three Dimensional Unsteady Flow Simulation of Compressed Truncated Perfect Nozzles"AIAA Paper. 2002-1251 (2002)

    • Description
      「研究成果報告書概要(欧文)」より
    • Related Report
      2001 Final Research Report Summary

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Published: 2000-04-01   Modified: 2016-04-21  

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