US3613827A - Device for attenuating noise emitted by the jet of a jet engine - Google Patents

Device for attenuating noise emitted by the jet of a jet engine Download PDF

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Publication number
US3613827A
US3613827A US53224A US3613827DA US3613827A US 3613827 A US3613827 A US 3613827A US 53224 A US53224 A US 53224A US 3613827D A US3613827D A US 3613827DA US 3613827 A US3613827 A US 3613827A
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US
United States
Prior art keywords
jet
blading
nozzle
lift
trailing edge
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.)
Expired - Lifetime
Application number
US53224A
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English (en)
Inventor
Andre Labussiere
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.)
Dassault Aviation SA
Original Assignee
Dassault Aviation SA
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 Dassault Aviation SA filed Critical Dassault Aviation SA
Application granted granted Critical
Publication of US3613827A publication Critical patent/US3613827A/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/62—Reversing jet main flow by blocking the rearward discharge by means of flaps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing

Definitions

  • the object of the invention is an improved silencer device which promotes mixing between the internal and external flows and introduces substantial improvements compared with the known devices both as far as the attenuation of the noise level is concerned and as far as concerns the jet engine performance.
  • a blading system with a lift profile designed by virtue of the lift effect to produce a series of marginal vortices at the level of and at the periphery of the blading.
  • the blading in question is constituted by a series of radial blades distributed around a central body, although other arrangements can equally well be adopted, for example a louvre arrangement.
  • FIG. I is a schematic perspective view of a jet engine nozzle equipped with the silencer in accordance with the invention.
  • FIGS. 2, 3, and 4 are diagrams illustrating a variant embodiment with a reverse thrust system, FIGS. 3 and 4 respectively providing views in axial section and elevation (in the latter case on tee rear of the nozzle).
  • the jet engine nozzle 1 contains a central body 2 from which extend radial blades 3 which advantageously project to the rear of the exit plane of the nozzle.
  • These blades are not assembled on simple symmetrical profiled arms designed in order to reduce drag; in other words, they are true blades or aerofoils which have a top camber and bottom camber and give rise to an aerodynamic lift Rz due to the jet flow. It is this lift which in fact produces, as with an aerofoil, marginal or tip vortices illustrated schematically by the arrows 4 and extending through vortex zones 5.
  • This kind of silencer has an obvious advantage because of its simplicity and robustness. It can easily be designed to be wholly or partially retracted in cruising flight.
  • the blades have a variable camber.
  • Each blade is made up on the one hand by a fixed front element 3a at the leading edge and situated in the body of the jet, the direction of which latter is indicated by the arrow F, and on the other hand by a movable trailing edge flap 3b articulated about a radial axis 6.
  • FIG. 3 illustrates a reverse thrust system of conventional kind in which a grid of deflector blades 7 is located in a lateral duct 8 which can be closed off during nonnal operation and uncovered on landing when it is desired to produce reverse thrust for braking, by forward deflection of the jet.
  • the trailing edge flaps 3b are deployed through about in relation to the fixed part 3a, into the position C shown in full line in FIG. 2, and virtually close off the exit section of the nozzle 1, as shown in FIG. 4.
  • the hot gases are then forced to escape through the lateral duct 8 (FIG. 3) and are deflected forward by the blade grid 7.
  • a device for attenuating the noise emitted by the jet comprising a blading fitted in said exit section and having blades shaped with a lift-producing profile and designed, by virtue of said lift, to create a series of tip vortices level with and at the periphery of the blading.
  • a device as claimed in claim-1 in which the blading is constituted by a series of radial blades distributed about a central body.
  • a device as claimed in claim I in which the blading projects towards the rear of the exit plane of the nozzle.
  • each blade comprising on the one hand a fixed leading edge element and on the other hand a movable flap at the trailing edge.
  • trailing edge flap can be disposed in projection of the fixed leading edge element, the assembly then being located in the body of the jet and the blade lift being virtually zero, the silencing effect being produced by deploying the trailing edge flap through a given angle in relation to the fixed part of the blade.
  • trailing edge flaps can be deployed through approximately 90 in relation to the leading edge element in order to close off the exit section of the jet engine nozzle at least to a substantial extent.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Exhaust Silencers (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US53224A 1969-07-16 1970-07-08 Device for attenuating noise emitted by the jet of a jet engine Expired - Lifetime US3613827A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6924196A FR2053736A5 (zh) 1969-07-16 1969-07-16

Publications (1)

Publication Number Publication Date
US3613827A true US3613827A (en) 1971-10-19

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Family Applications (1)

Application Number Title Priority Date Filing Date
US53224A Expired - Lifetime US3613827A (en) 1969-07-16 1970-07-08 Device for attenuating noise emitted by the jet of a jet engine

Country Status (5)

Country Link
US (1) US3613827A (zh)
DE (1) DE2035403C3 (zh)
FR (1) FR2053736A5 (zh)
GB (1) GB1307867A (zh)
NL (1) NL7010373A (zh)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3830431A (en) * 1973-03-23 1974-08-20 Nasa Abating exhaust noises in jet engines
US4175640A (en) * 1975-03-31 1979-11-27 Boeing Commercial Airplane Company Vortex generators for internal mixing in a turbofan engine
US4298089A (en) * 1976-12-23 1981-11-03 The Boeing Company Vortex generators for internal mixing in a turbofan engine
US5197855A (en) * 1991-07-01 1993-03-30 United Technologies Corporation Engine exhaust/blade interaction noise suppression
US5203164A (en) * 1990-06-06 1993-04-20 Paulson Allen E Method and apparatus for quieting a turbojet engine
US5517865A (en) * 1991-06-13 1996-05-21 General Electric Company Vortex suppression for an eductor
US6606854B1 (en) * 1999-01-04 2003-08-19 Allison Advanced Development Company Exhaust mixer and apparatus using same
US20040031258A1 (en) * 2002-03-20 2004-02-19 Dimitri Papamoschou Jet engine noise suppressor
US11105297B2 (en) * 2019-01-24 2021-08-31 Airbus Operations Sas Turbofan comprising a set of rotatable blades for blocking off the bypass flow duct

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4439104A (en) * 1981-06-15 1984-03-27 The Garrett Corporation Compressor inlet guide vane and vortex-disturbing member assembly
US4844695A (en) * 1988-07-05 1989-07-04 Pratt & Whitney Canada Inc. Variable flow radial compressor inlet flow fences
US5373691A (en) * 1993-06-23 1994-12-20 Allied-Signal Inc. Inlet guide vane dewhistler
US7926256B2 (en) * 2008-10-27 2011-04-19 General Electric Company Inlet system for an EGR system

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2934889A (en) * 1956-02-14 1960-05-03 United Aircraft Corp Noise abatement means
US2944623A (en) * 1955-09-02 1960-07-12 Jr Albert G Bodine Jet engine noise reducer
GB885093A (en) * 1959-05-01 1961-12-20 Alec David Young Improvements in or relating to jet propulsion nozzles
US3153319A (en) * 1952-07-25 1964-10-20 Young Alec David Jet noise suppression means

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3153319A (en) * 1952-07-25 1964-10-20 Young Alec David Jet noise suppression means
US2944623A (en) * 1955-09-02 1960-07-12 Jr Albert G Bodine Jet engine noise reducer
US2934889A (en) * 1956-02-14 1960-05-03 United Aircraft Corp Noise abatement means
GB885093A (en) * 1959-05-01 1961-12-20 Alec David Young Improvements in or relating to jet propulsion nozzles

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3830431A (en) * 1973-03-23 1974-08-20 Nasa Abating exhaust noises in jet engines
US4175640A (en) * 1975-03-31 1979-11-27 Boeing Commercial Airplane Company Vortex generators for internal mixing in a turbofan engine
US4298089A (en) * 1976-12-23 1981-11-03 The Boeing Company Vortex generators for internal mixing in a turbofan engine
US5203164A (en) * 1990-06-06 1993-04-20 Paulson Allen E Method and apparatus for quieting a turbojet engine
US5517865A (en) * 1991-06-13 1996-05-21 General Electric Company Vortex suppression for an eductor
US5197855A (en) * 1991-07-01 1993-03-30 United Technologies Corporation Engine exhaust/blade interaction noise suppression
US6606854B1 (en) * 1999-01-04 2003-08-19 Allison Advanced Development Company Exhaust mixer and apparatus using same
US20040031258A1 (en) * 2002-03-20 2004-02-19 Dimitri Papamoschou Jet engine noise suppressor
US7293401B2 (en) * 2002-03-20 2007-11-13 The Regents Of The University Of California Jet engine noise suppressor
US11105297B2 (en) * 2019-01-24 2021-08-31 Airbus Operations Sas Turbofan comprising a set of rotatable blades for blocking off the bypass flow duct

Also Published As

Publication number Publication date
FR2053736A5 (zh) 1971-04-16
GB1307867A (en) 1973-02-21
DE2035403A1 (de) 1971-02-04
NL7010373A (zh) 1971-01-19
DE2035403B2 (de) 1979-10-25
DE2035403C3 (de) 1980-07-17

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