Patent Document ID: 5386689
Application ID: 07961612
Patent Flag: 1

Claim One:
1. A system for reducing the acoustic levels of internal and external sound fields generated by gas turbine engines of a jet aircraft having an aircraft fuselage, wings, nacelles, tail, and stabilizer structures, said system comprising a plurality of actuator means to generate sound, a plurality of sensor means to measure said acoustic levels, said sensor means comprising microphone means located in and around the engines, and on a plurality of aircraft structures selected from among the aircraft fuselage, wings, nacelles, tail, and stabilizer structures, one or more controller means to control said actuators to generate sound in order to effect the reduction of the internal and external sound field as measured by the plurality of sensors wherein said actuator means comprises an air modulator-based acoustic source that receives a flow of compressed air derived from compression stages of one or more of said engines.