Effects of Equivalence Ratio of Afterburner and Temperature Distribution on Jet Noise from Rectangular Plug Nozzle

平成22年度宇宙輸送シンポジウム(2011年1月20-21日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県
Space Transportation FY2010 (January 20-21, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan
Jet noise characteristics radiated from a rectangular plug nozzle of a pre-cooled turbojet engine are investigated, experimentally. In the present study, the nozzle scale (1.0 %, 2.4 %), total temperature (T(sub t) = 290 K-1720 K), afterburner (AB on or AB off), and hydrogen equivalence ratio (phi = 0.14 - 4.20) are varied. Temperature measurement was carried out using temperature measurement section. By use of A(U(sub j ))(exp n) law, normalized jet noise spectra are obtained. Normalized jet noise spectra with afterburner are lower than that for without afterburner. Combustion afterburner. Combustion afterburner. Combustion which takes place out of nozzle are dominant in a hydrogen rich burn afterburner. It is supposed that diffusion combustion of such an afterburner is dominant, and that the velocity index n=4 is more suitable, which corresponds to "monopole" sound source.
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形態: CD-ROM1枚
Physical characteristics: Original contains color illustrations
Note: One CD-ROM
資料番号: AA0065073008