EP1347438A2 - Procédé de réduction du bruit produit par un avion à hélice à plusieurs moteurs - Google Patents

Procédé de réduction du bruit produit par un avion à hélice à plusieurs moteurs Download PDF

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Publication number
EP1347438A2
EP1347438A2 EP03001822A EP03001822A EP1347438A2 EP 1347438 A2 EP1347438 A2 EP 1347438A2 EP 03001822 A EP03001822 A EP 03001822A EP 03001822 A EP03001822 A EP 03001822A EP 1347438 A2 EP1347438 A2 EP 1347438A2
Authority
EP
European Patent Office
Prior art keywords
propellers
propeller
aircraft
adjustment
matched
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP03001822A
Other languages
German (de)
English (en)
Other versions
EP1347438A3 (fr
Inventor
Ingo Udo Dr. Borchers
Sigurd Dr. Häusler
Michael Dr. Bauer
Roger Dr. Drobietz
Wolfgang Dr. Gleine
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Airbus Operations GmbH
Original Assignee
Dornier GmbH
EADS Deutschland GmbH
Airbus Operations GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Dornier GmbH, EADS Deutschland GmbH, Airbus Operations GmbH filed Critical Dornier GmbH
Publication of EP1347438A2 publication Critical patent/EP1347438A2/fr
Publication of EP1347438A3 publication Critical patent/EP1347438A3/fr
Withdrawn legal-status Critical Current

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Classifications

    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/175—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using interference effects; Masking sound

Definitions

  • the invention relates to a method for noise reduction indoors and outdoors of multi-engine propeller aircraft.
  • the propellers are a major source of noise for indoor and outdoor Outside noise level represents.
  • the noise emission of a propeller is due to the periodic processes very tonal.
  • the frequency of the fundamental tone is determined generally from the product of the number of blades and the speed of a propeller. at Today's propeller aircraft has a very low fundamental frequency. A reduction the interior noise therefore requires z.
  • B. the use of a high mass Increase the sound insulation of the fuselage structure of the aircraft. This high mass would be detrimental to the performance of the aircraft. Also increase high Level on the outer skin of the fuselage the mechanical / dynamic loading of the structure.
  • the object of the invention is therefore to create a method with which can significantly reduce the noise emissions of the propellers, and wherein at the same time z. B. the mass required for sound insulation is reduced.
  • the noise emission of the inner and outer propeller are adjusted so that at least that Sound field of the fundamental tone in amplitude and phase of the inner propeller with the Sound field of the fundamental tone in amplitude and phase of the outer propeller in the area overlay the nearest critical fuselage surface of the aircraft so that they weaken significantly there through interference or ideally even completely extinguish.
  • the outer propeller Since the outer propeller is farther away from the surface of the fuselage, must have its sound radiation in the fundamental tone compared to that of the inner propeller to be taller. This can e.g. can be achieved in that the number of sheets of the outer Propellers compared to that of the inner propeller is reduced. In parallel the speed of the outer propeller versus the speed of the inner propeller increased so that the products from blade count and speed for the inner propeller and the outer propeller are the same size. This also ensures that the Propellers have the same fundamental frequency.
  • the necessary phase positions of the sound fields can in the case considered here (Product of speed and number of blades for the propellers constant, i.e. constant Sheet repetition frequency), by fine adjustment of the current sheet position angle of the Propellers are adjusted to each other (e.g. adjustment of the blade phase angle or the phase differences in the blade sequence of the propellers), so that the sound fields like Above mentioned, phase-shifted by about 180 ° in the area of the critical fuselage surface be overlaid. These settings can be actively controlled and controlled become.
  • the inventive method is also taking into account several propeller tones (Fundamental and harmonic) applicable.
  • FIG Propeller plane The method according to the invention for a four-engine is illustrated with the aid of a FIG Propeller plane with two propellers closer to each of the two wings explained. It shows the view from above and in a schematic representation Fuselage outer skin 1 of the aircraft and the position of the inner 5 and the outer 6 propellers on one of the wings. The sound field of the inner propeller 10 and the sound field 11 of the outer propeller are also shown.
  • the two engines 5, 6 are coordinated with one another in such a way that that is at the critical point PK, the closest area to the outer skin of the fuselage 1, overlay the two sound fields so that they weaken as much as possible.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
EP03001822A 2002-03-19 2003-01-29 Procédé de réduction du bruit produit par un avion à hélice à plusieurs moteurs Withdrawn EP1347438A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10212036 2002-03-19
DE10212036A DE10212036B4 (de) 2002-03-19 2002-03-19 Verfahren zur Geräuschreduktion für mehrmotorige Propellerflugzeuge

Publications (2)

Publication Number Publication Date
EP1347438A2 true EP1347438A2 (fr) 2003-09-24
EP1347438A3 EP1347438A3 (fr) 2006-10-18

Family

ID=27771413

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03001822A Withdrawn EP1347438A3 (fr) 2002-03-19 2003-01-29 Procédé de réduction du bruit produit par un avion à hélice à plusieurs moteurs

Country Status (5)

Country Link
US (1) US6896219B2 (fr)
EP (1) EP1347438A3 (fr)
BR (1) BR0300683A (fr)
CA (1) CA2422441C (fr)
DE (1) DE10212036B4 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008127696A1 (fr) * 2007-04-11 2008-10-23 Bell Helicopter Textron Inc. Procédé destiné à supprimer les vibrations dans un aéronef à rotors basculants
US8961140B2 (en) * 2009-10-14 2015-02-24 Lord Corporation Aircraft propeller balancing system
US8564217B2 (en) 2010-06-24 2013-10-22 General Electric Company Apparatus and method for reducing acoustical noise in synthetic jets
US8622334B2 (en) 2011-05-19 2014-01-07 Aurora Flight Sciences Corporation System and method for reducing the noise of pusher type aircraft propellers
US10435148B2 (en) * 2017-05-08 2019-10-08 Aurora Flight Sciences Corporation Systems and methods for acoustic radiation control
CN108944749B (zh) * 2017-05-19 2022-03-18 比亚迪股份有限公司 车辆降噪装置及方法
FR3069850B1 (fr) * 2017-08-01 2019-11-22 Safran Aircraft Engines Systeme actif generant des interferences acoustiques destructives pour moteur d'aeronef a plusieurs corps de soufflante
US11312478B2 (en) * 2017-11-27 2022-04-26 United States Of America As Represented By The Administrator Of Nasa Adaptive phase control architecture for reduction of community noise from distributed propulsion vehicles
EP3626628B1 (fr) 2018-09-18 2021-09-01 Bombardier Inc. Système et procédé de synchronisation par phase de moteurs d'aéronefs

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH677844A5 (en) 1989-01-06 1991-06-28 Werner Eichenberger Aircraft propeller noise reduction system - uses cancellation effect of sound waves produced by 2 coaxial propellers
US5453943A (en) 1994-02-18 1995-09-26 United Technologies Corporation Adaptive synchrophaser for reducing aircraft cabin noise and vibration
US5715162A (en) 1992-10-13 1998-02-03 United Technologies Corporation Correlative filter for a synchrophaser

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8615315D0 (en) * 1986-06-23 1986-07-30 Secr Defence Aircraft cabin noise control apparatus
GB2211635B (en) * 1987-10-28 1992-02-05 Fokker Aircraft Control system for synchrophasing aircraft propellers
US5551649A (en) * 1989-10-20 1996-09-03 Fokker Aircraft B.V. Propeller blade position controller
GB2237415A (en) * 1989-10-20 1991-05-01 Fokker Bv Propeller blade synchrophasing
US5789678A (en) * 1996-10-22 1998-08-04 General Electric Company Method for reducing noise and/or vibration from multiple rotating machines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH677844A5 (en) 1989-01-06 1991-06-28 Werner Eichenberger Aircraft propeller noise reduction system - uses cancellation effect of sound waves produced by 2 coaxial propellers
US5715162A (en) 1992-10-13 1998-02-03 United Technologies Corporation Correlative filter for a synchrophaser
US5453943A (en) 1994-02-18 1995-09-26 United Technologies Corporation Adaptive synchrophaser for reducing aircraft cabin noise and vibration

Also Published As

Publication number Publication date
US20040018086A1 (en) 2004-01-29
EP1347438A3 (fr) 2006-10-18
CA2422441A1 (fr) 2003-09-19
BR0300683A (pt) 2004-08-10
DE10212036B4 (de) 2009-01-02
DE10212036A1 (de) 2003-10-16
CA2422441C (fr) 2011-08-02
US6896219B2 (en) 2005-05-24

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