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

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

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G10K-011/16
출원번호	US-0964604 (1992-10-21)
발명자 / 주소	Burdisso Ricardo (Blacksburg VA) Fuller Chris R. (Blacksburg VA) O\Brien Walter F. (Blacksburg VA) Thomas Russell H. (Blacksburg VA) Dungan Mary E. (Malden SC)
출원인 / 주소	The Center for Innovative Technology (Herndon VA 02) Virginia Polytechnic Institute & State University (Blacksburg VA 02) Virginia Tech Intellectual Properties, Inc. (Blacksburg VA 02)
인용정보	피인용 횟수 : 32 인용 특허 : 0

초록 ▼

An 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.

대표청구항 ▼

An active noise control system for reducing aircraft engine noise which means emanates from an aircraft engine inlet of a gas turbine engine, said gas turbine engine having a fan and compressor the revolution of which generates a primary sound field, said active noise control system comprising: blade passage sensor means mounted within said turbine engine adjacent to said fan for generating a reference acoustic signal, said blade passage sensor means comprises an eddy current sensor to sense a fan blade passage frequency which is correlated with radiated sound; distributed error sensor means positioned to be responsive to said primary sound field for generating an error acoustic signal; acoustic driver means comprised of piezoelectric driven panels mounted circumferentially flush about an interior surface of said inlet preceding said fan; and controller means responsive to said reference acoustic signal and said error acoustic signal for driving said acoustic driver means to generate a secondary sound field having an approximately equal amplitude but opposite phase as said primary sound field to thereby effectively reduce said engine noise. A compact acoustic driver for generating a controlled sound field for canceling noise comprising: a curved panel tuned to have a fundamental frequency near a tone in said noise to be canceled, and having an interior radius of curvature and an exterior radius of curvature, said curved panel having an exterior surface defined by said exterior radius of curvature; surface strain actuator means mounted only on said exterior surface of said curved panel, said surface strain actuator means being mechanically coupled to said curved panel to impart mechanical motion thereto; and electrical generator means connected to said surface strain actuator means for driving said actuator means and imparting mechanical motion to said curved panel at said fundamental frequency to generate said controlled sound field for canceling said tone in said noise.

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연합인증

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

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