WO1994008540B1 - Active gas turbine (jet) engine noise suppression - Google Patents
Active gas turbine (jet) engine noise suppressionInfo
- Publication number
- WO1994008540B1 WO1994008540B1 PCT/US1993/009739 US9309739W WO9408540B1 WO 1994008540 B1 WO1994008540 B1 WO 1994008540B1 US 9309739 W US9309739 W US 9309739W WO 9408540 B1 WO9408540 B1 WO 9408540B1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- jet aircraft
- engine
- acoustic
- actuator
- engines
- Prior art date
Links
- 230000001629 suppression Effects 0.000 title 1
- 230000000694 effects Effects 0.000 claims abstract 2
- 210000003284 Horns Anatomy 0.000 claims 8
- 210000001331 Nose Anatomy 0.000 claims 4
- 230000000051 modifying Effects 0.000 claims 4
- 210000003800 Pharynx Anatomy 0.000 claims 2
- 238000005070 sampling Methods 0.000 claims 2
- 239000003381 stabilizer Substances 0.000 claims 2
- 230000005534 acoustic noise Effects 0.000 claims 1
- 238000007906 compression Methods 0.000 claims 1
- 230000005520 electrodynamics Effects 0.000 claims 1
- 230000002708 enhancing Effects 0.000 claims 1
- 230000003044 adaptive Effects 0.000 abstract 1
- 230000001537 neural Effects 0.000 abstract 1
Abstract
A method and system for reducing the acoustic levels of internal and external sound fields (23 and 24) generated by gas turbine engines (2) has several actuators to generate sound (50, 84, and 115), several sensors to measure the acoustic levels (49 and 69), and one or more controllers (113). The controllers are adaptive self-learning neural networks (112) that control the actuators to generate sound in order to effect the reduction of the internal and external sound field as measured by the sensors.
Claims
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.
2. The system for reducing the acoustic levels of internal and external sound fields generated by gas turbine engines of a jet aircraft of claim 1 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.
3. The system for reducing the acoustic levels of internal and external sound fields generated by gas turbine engines of a jet aircraft of claim 1 wherein said engines have external far and near acoustic radiation fields and said sensor means comprise first error sensors located inside the engine, and second error sensors located in the far and near external acoustic radiation fields of the engine.
4. The system for reducing the acoustic levels of internal and external sound fields generated by gas turbine engines of a jet aircraft of claim 1 wherein said controller means receives signals from a plurality of said sensors and comprises means to control a plurality of actuator means simultaneously to suppress acoustic noise from multiple engines.
5. The system for reducing the acoustic levels of internal and external sound fields generated by gas turbine engines of a jet aircraft of claim 1 wherein said engines provide signals to keyphasor or tachometer means and said controller receives rotational cycle reference signals from the keyphasor or tachometer means, wherein said system learns and adapts in real time to changes in residual acoustic fields.
6. The system for reducing the acoustic levels of internal and external sound fields generated by gas turbine engines of a jet aircraft of claim 5, wherein said engines provide a rotational cycle reference signal and said sensor means provide signals to said controller and said system further comprises means to convert signals from the sensors to digital samples, said means to convert operating at a sampling rate, and rotational speed synchronization means to synchronize the sampling rate to the engines rotational cycle reference signal.
7. A jet aircraft having an active system for reducing the acoustic levels of internal and external sound fields generated by gas turbine engines of the jet aircraft comprising a plurality of actuator means to generate sound, a plurality of sensor means to measure said acoustic levels, said sensor means comprising one or more controller means for controlling said actuators to radiate acoustic energy to cancel acoustic levels measured by said sensor means, said jet engine having a nacelle comprising a cowl, an inlet duct, engine and cowl panels, a bypass duct, an exhaust duct that comprises a tailpipe extension, thrust reverser, and tailpipe, said nacelle having zones containing noise source sensors, internal error sensors, external error sensors, and canceling actuators.
8. The jet aircraft of claim 7 having forward and rearward ends, wherein said nacelle has an inlet end and comprises a nose cowl having an inlet duct at the inlet end of said nacelle, an engine and cowl panel having a bypass duct immediately behind said nose cowl, a tailpipe extension behind said engine and cowl panel, said tailpipe extension having an exhaust duct and a thrust reverser and tail pipe behind said tailpipe extension, wherein said zones comprising noise source sensors comprise a first noise source sensor zone in the forward end of said engine and cowl panel, a second noise source sensor zone in the forward end of said tailpipe extension, and wherein said zones comprising error sensors comprise a first error sensor zone in the forward end of said nose cowl, a second error sensor zone in the rearward end of said engine and cowl panel, and a third error sensor zone in said thrust reverser and tailpipe, and actuator zones comprising a first actuator zone in the inlet duct of said nose cowl aft of said first error sensor zone, a second actuator zone in the bypass duct of said engine and cowl panel between said first noise source sensor zone and said second error sensor zone, and a third actuator zone located in the exhaust duct of said tailpipe extension located aft of said second noise source sensor zone.
9. The jet aircraft of claim 8 wherein the actuators located in one or more of said first, second and third actuator zones comprise air stream modulators.
10. The jet aircraft of claim 8 wherein the actuators located in one or more of said first, second and third actuator zones comprise piezoceramic actuators.
11. The jet aircraft of claim 9 wherein one or more of said air stream modulators comprises an air modulator actuator horn having a mouth opening into an ambient bypass air flow, said horn comprising throat means to provide impedance loading to enhance performance, and horn section means to match the impedance of the ambient bypass air flow at the mouth of the horn.
12. The jet aircraft of claim 11 wherein said horn comprises a mouth having a flange attached to an entry hole in an engine bypass duct wall, a plenum, and a pipe manifold attached to a source of air.
13. The jet aircraft of claim 12 wherein said engine comprises compressor stages and bleed ports on the engine's compressor stages, and wherein said pipe manifold is adapted to receive compressed air from said bleed ports.
14. The jet aircraft of claim 13 wherein said throat means of said horn provides an exit from the plenum, and said mouth of said horn provides an entrance back into a bypass duct, each engine having a plurality of air modulator actuators.
15. The jet aircraft of claim 14 wherein said horn comprises driver means.
16. The jet aircraft of claim 15 wherein said driver means comprises a stiffness-controlled, electrodynamic actuator.
17. The jet aircraft of claim 7 wherein said actuator means comprise acoustic loudspeakers located in one or more of the inlet duct, a bypass duct, and the forward end of the tailpipe.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002147183A CA2147183A1 (en) | 1992-10-13 | 1993-10-12 | Active gas turbine (jet) engine noise suppression |
| EP94901158A EP0667757A4 (en) | 1992-10-13 | 1993-10-12 | Active gas turbine (jet) engine noise suppression. |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US07/961,612 | 1992-10-13 | ||
| US07/961,612 US5386689A (en) | 1992-10-13 | 1992-10-13 | Active gas turbine (jet) engine noise suppression |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| WO1994008540A1 WO1994008540A1 (en) | 1994-04-28 |
| WO1994008540B1 true WO1994008540B1 (en) | 1994-06-09 |
Family
ID=25504741
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/US1993/009739 WO1994008540A1 (en) | 1992-10-13 | 1993-10-12 | Active gas turbine (jet) engine noise suppression |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US5386689A (en) |
| EP (1) | EP0667757A4 (en) |
| CA (1) | CA2147183A1 (en) |
| IL (1) | IL107276A0 (en) |
| WO (1) | WO1994008540A1 (en) |
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1992
- 1992-10-13 US US07/961,612 patent/US5386689A/en not_active Expired - Fee Related
-
1993
- 1993-10-12 WO PCT/US1993/009739 patent/WO1994008540A1/en not_active Application Discontinuation
- 1993-10-12 EP EP94901158A patent/EP0667757A4/en not_active Withdrawn
- 1993-10-12 CA CA002147183A patent/CA2147183A1/en not_active Abandoned
- 1993-10-13 IL IL10727693A patent/IL107276A0/en unknown
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