Abstract
Mixer ejector nozzle devices in scale have been developed for the target to reduce the noise level equivalent to ICAO Annex 16 Chapter 3 regulation with minimum thrust losses. On this paper, a parametric study of mixer ejector nozzle configurations with acoustic liner has been conducted acoustically assuming at static to flight speed. Then upstream nozzle conditions of the mixer with velocity profile and temperature profile were simulated to the uniform flow. For high temperature (HOOK) jet core condition, acoustic liner performance tuned at inner surface of ejector were very important to reduce jet mixing noise generated by mixer lobes inside the ejector especially. Mixer ejector configurations were changed by focusing the mixer shape and mixer lobes number and lobes numbers were important not only enhance of mixing but also attenuation by acoustic liner. Also heat resistive material which was made by porous CMC (ceramic matrix composites) was applied to the acoustic liner and the noise attenuation were ranked with the other existing liner. The mixer ejector noise suppression device including porous ceramic acoustic liner has been defined for the HYPR90-TURBO sub-scale (1/2.6) demonstrator engine which is planned to be tested for noise in the summer of 1997.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
