ファンエンジンFJR710による吸入消音ダクト及びファン排気消音ダクトの地上実機試験

Material type: 文書・図像類

Author: 渡辺, 実ほか

Publisher: 航空宇宙技術研究所

Publication date: 1980-01

Material Format: Digital

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Note (General)：: Inlet and fan exhaust noise suppressors for a high by-pass ratio turbofan engine (FJR710) were ground tested.The inlet and fan exhaust duct walls were...

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Material Type: 文書・図像類
Title: ファンエンジンFJR710による吸入消音ダクト及びファン排気消音ダクトの地上実機試験
Author/Editor: 渡辺, 実
鳥崎, 忠雄
武田, 克己
小林, 紘
関根, 静雄
中山, 普
吉田, 晃
越沼, 威
松田, 幸雄
WATANABE, Minoru
TORISAKI, Tadao
TAKEDA, Katsumi
KOBAYASHI, Hiroshi
SEKINE, Shizuo
NAKAYAMA, SUSUMU
YOSHIDA, Akira
KOSHINUMA, Takeshi
MATSUDA, Yukio
Author Heading: 渡辺, 実
鳥崎, 忠雄
武田, 克己
小林, 紘
関根, 静雄
中山, 普
吉田, 晃
越沼, 威
松田, 幸雄
WATANABE, Minoru
TORISAKI, Tadao
TAKEDA, Katsumi
KOBAYASHI, Hiroshi
SEKINE, Shizuo
NAKAYAMA, SUSUMU
YOSHIDA, Akira
KOSHINUMA, Takeshi
MATSUDA, Yukio
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1980-01
Publication Date (W3CDTF): 1980-01
Alternative Title: Static Test of Noise Suppressors for FJR710 Turbofan Engine
Periodical title: 航空宇宙技術研究所資料 = Technical Memorandum of National Aerospace Laboratory
No. or year of volume/issue: 401
Volume: 401
Pages: 29-
ISSN (Periodical Title): ISSN : 0452-2982
Text Language Code: jpn
Target Audience: 一般
Note (General): Inlet and fan exhaust noise suppressors for a high by-pass ratio turbofan engine (FJR710) were ground tested.The inlet and fan exhaust duct walls were lined with perforated-plate-on-honeycomb absorbers.Acoustically treated splitter rings could be inserted into the inlet duct for a greater noise attenuation.The inner and outer walls of the annular fan exhaust duct were lined with different depth absorbers for a broader band noise attenuation.Sound power attenuation spectra were obtained by an insertion loss technique using far field measurements.Noise from each treated duct was compared with noise from a hard wall duct without splitters.A maximum perceived noise level attenuation due to the suppressors of 16 PNdB was obtained at 95％ fan speed.Degradations of engine performance caused by the fully equipped suppressors with splitter rings were about 3％ of the engine thrust.No detectable thrust loss was measured in other experimental cases without splitter rings.
資料番号: NALTM0401000
レポート番号: NAL TM-401
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43984&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43984&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