Pressure Measurement of Flow through Cascade Using the Suction-Type Shock Tunne
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- NAGAYAMA Takehiko
- 三菱重工業(株)技術本部長崎研究所
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- KURAMOTO Yasuo
- 三菱重工業(株)技術本部長崎研究所
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- IMAIZUMI Masamichi
- 三菱重工業(株)技術本部長崎研究所
Bibliographic Information
- Other Title
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- 大気吸込式衝撃風胴を使用した翼列流れの圧力計測
- タイキ スイコミシキ ショウゲキ フウドウ オ シヨウシタ ヨクレツ ナガレ
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Abstract
This paper describes a pressure measurement method of the transonic flow through the turbine cascade by means of the suction-type shock tunnel.<BR>The present method which uses silicon oil containing tubes is characterized by an improvement in the response of the pressure-time. It is shown that the values of the static pressures on the blade surfaces measured by the present method almost agree with those by the optical method. The experimental results using a Pitot tube are also shown as an example of this method in order to obtain the total pressures downstream of the cascade.
Journal
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- Aeronautical and Space Sciences Japan
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Aeronautical and Space Sciences Japan 28 (320), 450-455, 1980
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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Details 詳細情報について
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- CRID
- 1390001204477102336
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- NII Article ID
- 130003782491
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- NII Book ID
- AN00189072
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- ISSN
- 24241369
- 00214663
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- NDL BIB ID
- 2193055
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- Text Lang
- ja
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- Data Source
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- Abstract License Flag
- Disallowed