Acoustic Characterization of Compact Jet Engine Simulator Units

• Published in: NASA Center for AeroSpace Information (CASI). Conference Proceedings
• Main Authors: Doty, Michael J, Haskin, Henry H
• Format: Conference Proceeding
• Language: English
• Published: Hampton NASA/Langley Research Center 27.05.2013
• Subjects: Acoustic noise; Acoustics; Air conditioners; Air injection; Combustion chambers; Computer simulation; Flow stability; Hybrid vehicles; Jet engines; Noise levels; Nonuniform flow; Nozzles; Screens; Wind tunnels

Two dual-stream, heated jet, Compact Jet Engine Simulator (CJES) units are designed for wind tunnel acoustic experiments involving a Hybrid Wing Body (HWB) vehicle. The newly fabricated CJES units are characterized with a series of acoustic and flowfield investigations to ensure successful operation with minimal rig noise. To limit simulator size, consistent with a 5.8% HWB model, the CJES units adapt Ultra Compact Combustor (UCC) technology developed at the Air Force Research Laboratory. Stable and controllable operation of the combustor is demonstrated using passive swirl air injection and backpressuring of the combustion chamber. Combustion instability tones are eliminated using nonuniform flow conditioners in conjunction with upstream screens. Through proper flow conditioning, rig noise is reduced by more than 20 dB over a broad spectral range, but it is not completely eliminated at high frequencies. The low-noise chevron nozzle concept designed for the HWB test shows expected acoustic benefits when installed on the CJES unit, and consistency between CJES units is shown to be within 0.5 dB OASPL.