The renewing of the test section of the NAL transonic wind tunnel. Part 1: Reconstruction of the 1st corner turning vanes and aerodynamic stress measurement
| Autor: | Koike, Akira, Hosoe, Nobuyuki, Oguni, Yasuo, Suzuki, Koichi, Miwa, Hitoshi |
|---|---|
| Jazyk: | japonština |
| Rok vydání: | 1992 |
| Předmět: |
transonic wind tunnel
変動圧力 風洞改修 crack propagation flow turning vane 高速ディフューザ 応力圧力相関 構造物疲労 structural resonance fluctuating pressure stress pressure correleration 偏流翼 応力測定 structural fatigue high speed diffuser 振動空力荷重 コーナベーン vibrational aerodynamic load 遷音速風洞 亀裂進行 flow induced structural damage 構造物共振 corner vane 流れ誘因構造物損傷 wind tunnel refurbishment stress measurement |
| Zdroj: | 航空宇宙技術研究所資料 = Technical Memorandum of National Aerospace Laboratory. 651:1-24 |
| ISSN: | 0452-2982 |
| Popis: | 航空宇宙技術研究所(NAL)遷音速風洞は1960年に建設され、その老朽化部分の大幅な修理が1985年から開始された。この修理の中で新らしく再製作された偏流翼について記述する。偏流翼の翼厚は初め6mmで、疲労による亀裂の進行を防ぐため1968年に9mmに増加された。しかし亀裂の発生は止まなかったので、今回の改修では翼厚は12mmに増加された。偏流翼に当る流れの空気力や変動圧力により偏流翼内に生ずる応力を計測する試験を製作の前と後に実施した。その結果を、応力と圧力との相関も含めて示す。 National Aerospace Laboratory (NAL) transonic wind tunnel was constructed in 1960, and in-depth repairs of its superannuated parts was begun in 1985. In this paper, the newly reconstructed turning vanes are described. The thickness of the turning vanes was 6 mm at first and it was increased to 9 mm in 1968 to prevent cracks caused by fatigue from developing. Despite of this increase in thickness, cracks were observed again. With the present reconstruction, the thickness was increased to 12 mm. Tests designed to measure the stresses within the vanes by aerodynamic force and pressure fluctuations of incoming flow were conducted before and after reconstruction. Results from the measurements are presented including a correlation analysis between the stress and the pressure fluctuation. 資料番号: AA0004139000 レポート番号: NAL TM-651 |
| Databáze: | OpenAIRE |
| Externí odkaz: |
|