Date of Award

Summer 2016

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Committee Director

Arthur Taylor

Committee Member

Robert Ash

Committee Member

Michael Doty

Abstract

Two Compact Jet Engine Simulator (CJES) units were designed for integrated wind tunnel acoustic experiments involving a Hybrid Wing Body (HWB) vehicle. To meet the 5.8% scale of the HWB model, Ultra Compact Combustor technology from the Air Force Research Laboratory was used. The CJES units were built and integrated with a control system in the NASA Langley Low Speed Aero acoustic Wind Tunnel. The combustor liners, plug—vane and flow conditioner components were built in-house at Langley Research Center. The operation of the CJES units was mapped and fixes found for combustor instability tones and rig flow noise. The original concept remained true, but the internal hardware evolved throughout the process. The CJES unit successfully completed the HWB validation test and can be used for acoustic testing or propulsion integration studies that require jet engines.

ISBN

9781369170948

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