Jet engine fan noise reduction system utilizing electro pneumatic transducers

• US 5,732,547 A
• Filed: 05/24/1996
• Issued: 03/31/1998
• Est. Priority Date: 10/13/1994
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Orzechowski, Jeffrey M., Olsen, Ronald F.
• Primary Examiner(s): Thorpe, Timothy
• Assistant Examiner(s): Kim, Ted
• Application Number:
  US08/653,138
• Time in Patent Office: 676 Days
• Field of Search: 60/204, 60/226.1, 60/725, 60/39.29, 415/119
• US Class Current: 60/204
• CPC Class Codes: F05B 2260/962 by means creating "anti-noise"
• CPC Class Codes: G10K 11/17857 Geometric disposition, e.g. placement of microphones
• CPC Class Codes: G10K 11/17861 using additional means for damping sound, e.g. using sound absorbing panels
• CPC Class Codes: G10K 11/17883 the reference signal being derived from a machine operating condition, e.g. engine RPM or vehicle speed
• CPC Class Codes: G10K 2210/109 Compressors, e.g. fans
• CPC Class Codes: G10K 2210/112 Ducts vehicle exhausts G10K2210/12822
• CPC Class Codes: G10K 2210/121 Rotating machines, e.g. engines, turbines, motors; Periodic or quasi-periodic signals in general
• CPC Class Codes: G10K 2210/1281 Aircraft, e.g. spacecraft, airplane or helicopter
• CPC Class Codes: G10K 2210/3026 Feedback
• CPC Class Codes: G10K 2210/3027 Feedforward
• CPC Class Codes: G10K 2210/3045 Multiple acoustic inputs, single acoustic output
• CPC Class Codes: G10K 2210/3046 Multiple acoustic inputs, multiple acoustic outputs
• CPC Class Codes: G10K 2210/32121 Fluid amplifiers, e.g. modulated gas flow speaker using electrovalves
• CPC Class Codes: G10K 2210/3229 Transducers

Abstract

A jet engine fan noise reduction system. The noise reduction system includes active noise control to suppress fan tone noise of an airplane flyover noise signature. The active noise control includes microphones with acoustic transducers upstream and downstream of the engine fan and fan exit guide vane stage to sense control system errors. Control signals are derived from the fan angular speed or blade passing frequency and the error signals sensed by the acoustic transducers. The control output signals actuate (modulate) air control valves on each side of the fan stage to direct conditioned (pressure and temperature regulated) high pressure primary air flow, thereby producing acoustic canceling of fan tone noise.

Claims

1. In combination in a system for jet engine fan stage noise reduction:

a reference sensor X;

an error microphone E1;

an error microphone E2;

a control unit responsive to said reference sensor X, said error microphone El, and said error microphone E2 for providing control signal Y1, and control signal Y2;

said control signal Y1 controlling said electro pneumatic transducers which modulate conditioned high pressure air to produce a modulated sound source;

said control signal Y2 controlling said electro pneumatic transducers which modulate conditioned high pressure air to produce a modulated sound source;

waveguides for directing sound waves and airflow from said electro pneumatic transducers to a fan blade tip region on each side of the fan stage;

a pressure regulator to condition high pressure air from an engine compressor for said electro pneumatic transducers;

a heat exchanger to condition the high temperature air from the engine compressor for said electro pneumatic transducers;

supply ducts for transporting engine compressor air to the said pressure regulator and said heat exchanger and conditioned compressor air to the said electro pneumatic transducers; and

at least one bleed port located on the engine compressor'"'"'s case for extracting high pressure air to supply electro pneumatic transducers.

2. The combination according to claim 1 further including reference sensor X for providing reference input to synchronize said control unit.

3. The combination according to claim 2 further including acoustic treatment located on flow surfaces ahead of and behind the fan to attenuate fan noise which is not canceled by the modulated conditioned high pressure air leaving the said wave guides.

4. A system for jet engine fan stage noise reduction comprising in combination:

an active noise control system including a plurality of microphones and electro pneumatic transducers upstream and downstream of the fan stage of the jet engine, said microphone sensing control system errors;

said active noise control system further including a reference signal from the fan, and error signals sensed by said microphones for providing control output signals; and

,

said control output signals actuating electro pneumatic transducers located on each side of the fan stage, to modulate conditioned high pressure air flow to each side of the fan stage by way of waveguides; and

said waveguides directing the modulated and conditioned high pressure air flow to a region of a fan tip, thereby producing acoustic canceling of fan noise; and

a system for conditioning high pressure and temperature engine compressor air for said electro pneumatic transducers consisting of;

a pressure regulator to condition the high pressure air from the engine compressor for said electro pneumatic transducers;

a heat exchanger to condition the high temperature air from the engine compressor for said electro pneumatic transducers;

supply ducts for transporting engine compressor air to said pressure regulator and said heat exchanger and conditioned compressor air to the said electro pneumatic transducers.

5. The system according to claim 4 further including said acoustic treatment to reduce fan broadband noise and fan tone noise which is not canceled by the electro pneumatic transducers.

6. In a jet engine having a fan stage, a method for control of jet engine fan noise comprising the steps of:

providing output control signals in response to a signal representative of blade passing frequency; and

,

utilizing said output control signals to actuate electro pneumatic transducers on each side of said fan stage to direct by way of waveguides conditioned and modulated high pressure air flow to a region of the fan blade tip on both the upstream and downstream sides of the fan stage; and

conditioning air from an engine compressor for effective use with said electro pneumatic transducers comprising the steps of;

ducting engine compressor bleed air from at least one port mounted on the engine compressor'"'"'s case through a supply duct to a pressure regulator for the purpose of controlling the supply pressure to said heat exchanger and said electro pneumatic transducers;

ducting the pressure regulated compressor air leaving said pressure regulator through a supply duct to said heat exchanger for reducing and controlling the temperature of the supply air pressure for said electro pneumatic transducers; and

ducting the conditioned high pressure air through a supply duct to said electro pneumatic transducers.