Active control of aircraft engine inlet noise using compact sound sources and distributed error sensors

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dc.contributor.assigneeCenter for Innovative Technologyen
dc.contributor.assigneeVirginia Polytechnic Institute and State Universityen
dc.contributor.assigneeVirginia Tech Intellectual Properties, Inc.en
dc.contributor.inventorBurdisso, Ricardo A.en
dc.contributor.inventorFuller, Chris R.en
dc.contributor.inventorO'Brien, Walter F. Jr.en
dc.contributor.inventorThomas, Russell H.en
dc.contributor.inventorDungan, Mary E.en
dc.date.accessed2016-08-19en
dc.date.accessioned2016-08-24T17:55:40Zen
dc.date.available2016-08-24T17:55:40Zen
dc.date.filed1992-10-21en
dc.date.issued1994-10-11en
dc.description.abstractAn active noise control system using a compact sound source is effective to reduce aircraft engine duct noise. The fan noise from a turbofan engine is controlled using an adaptive filtered-x LMS algorithm. Single multi channel control systems are used to control the fan blade passage frequency (BPF) tone and the BPF tone and the first harmonic of the BPF tone for a plane wave excitation. A multi channel control system is used to control any spinning mode. The multi channel control system to control both fan tones and a high pressure compressor BPF tone simultaneously. In order to make active control of turbofan inlet noise a viable technology, a compact sound source is employed to generate the control field. This control field sound source consists of an array of identical thin, cylindrically curved panels with an inner radius of curvature corresponding to that of the engine inlet. These panels are flush mounted inside the inlet duct and sealed on all edges to prevent leakage around the panel and to minimize the aerodynamic losses created by the addition of the panels. Each panel is driven by one or more piezoelectric force transducers mounted on the surface of the panel. The response of the panel to excitation is maximized when it is driven at its resonance; therefore, the panel is designed such that its fundamental frequency is near the tone to be canceled, typically 2000-4000 Hz.en
dc.format.mimetypeapplication/pdfen
dc.identifier.applicationnumber7964604en
dc.identifier.patentnumber5355417en
dc.identifier.urihttp://hdl.handle.net/10919/72822en
dc.identifier.urlhttp://pimg-fpiw.uspto.gov/fdd/17/554/053/0.pdfen
dc.language.isoen_USen
dc.publisherUnited States Patent and Trademark Officeen
dc.subject.cpcF05B2260/962en
dc.subject.cpcG10K11/1786en
dc.subject.cpcG10K11/1788en
dc.subject.cpcG10K2210/107en
dc.subject.cpcG10K2210/112en
dc.subject.cpcG10K2210/121en
dc.subject.cpcG10K2210/1281en
dc.subject.cpcG10K2210/1291en
dc.subject.cpcG10K2210/3032en
dc.subject.cpcG10K2210/3042en
dc.subject.cpcG10K2210/3045en
dc.subject.cpcG10K2210/3046en
dc.subject.cpcG10K2210/3226en
dc.subject.cpcG10K2210/32271en
dc.subject.cpcG10K2210/3229en
dc.subject.cpcG10K2210/32291en
dc.subject.cpcG10K2210/511en
dc.subject.uspc381/71.7en
dc.subject.uspcother381/190en
dc.subject.uspcother415/119en
dc.titleActive control of aircraft engine inlet noise using compact sound sources and distributed error sensorsen
dc.typePatenten
dc.type.dcmitypeTexten
dc.type.patenttypeutilityen

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