US3550721A - Silencing assembly for jet engines - Google Patents

Silencing assembly for jet engines Download PDF

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Publication number
US3550721A
US3550721A US718565A US3550721DA US3550721A US 3550721 A US3550721 A US 3550721A US 718565 A US718565 A US 718565A US 3550721D A US3550721D A US 3550721DA US 3550721 A US3550721 A US 3550721A
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US
United States
Prior art keywords
ring
nozzle
silencer
channels
jet engines
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
US718565A
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English (en)
Inventor
Georges Bruner
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.)
Breguet Aviation SA
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Breguet Aviation SA
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Filing date
Publication date
Application filed by Breguet Aviation SA filed Critical Breguet Aviation SA
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Anticipated expiration legal-status Critical
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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
    • F02K1/38—Introducing air inside the jet
    • F02K1/383—Introducing air inside the jet with retractable elements

Definitions

  • a silencer assembly for a jet aeroplane comprises an annular structure immediately in front of the nozzle exit, the annular structure defining a plurality of angularly spaced channels through which air is drawn to the jet stream.
  • PATENTEU neczs 19m sum 1 or 5 PATENIEU 05132 91970 SHEET 2 of 5 SILENCING ASSEMBLY FOR JET ENGINES
  • a disadvantage of jet-engined aircraft is that at takeoff they make considerable noise, something which greatly disturbs people living near airports.
  • the present invention provides a silencer which can be cut out during cruising flight.
  • the silencer is based on the principle of diluting the gases by sucking in air from outside through an aspirator.
  • takeoff aspirated air is introduced into the jet stream in a number of channels disposed at the nozzle end.
  • the channels are advantageously adapted to fold laterally into one another around the entire periphery of the jet stream so as to form in cruising flight a smooth annular nozzle for the jet stream.
  • the shapes of the channels will be such that the exhaust gas exit cross section is substantially the same, and appropriate for engine operation conditions, whether or not the silencer is in operation.
  • a ring forming the aspirator may be positioned to extend completely around the nozzle exit, whereas during cruising flight such ring is retracted.
  • the invention provides several forms of retraction.
  • FIG. 1 to 4 shows an improved silencer in accordance with the invention in position for takeoff and in position for cruising flight, the silencer including a slidable aspirator ring;
  • FIGS. to 7 show the silencer with the aspirator ring opening in a rearward position
  • FIGS. 8 to 11 show a silencer having an extensible ring which during cruising flight folds behind the silencer
  • FIG. 12 is a perspective view of an embodiment of the invention.
  • folding channels 1 which are open to atmosphere at the rear have air-guiding vanes 2 which also serve to stiffen the channel walls.
  • One wall of each channel is articulated along a rib 3, folding occurring around the axis formed by the rib 3 until each channel touches the adjacent channel (see for example FIG. 4).
  • walls 4 of each channel may be part-cylindrical.
  • the channels are foldable between a silencing position (see FIGS. 1 and 2) and a cruising position (see FIGS. 3 and 4).
  • the folding movement of the channels 1 is produced by torsion tubes 5 which are embedded in the channel structure in extension of the rib 3 which constitutes the folding axis.
  • the end of each tube 5 is mounted in a bearing 6 forming part of a partition 7.
  • Each tube 5 carries a lever 8 which, depending upon available space, extends either outwards, as in FIGS. 1, 3 and 12, or inwards, as in FIGS. 8 and 10.
  • the lever ends are interconnected by a number of rods 9 visible in FIG. 12 and the system is operated through the agency of a ram 10 disposed somewhere on the periphery of this actuating facility.
  • FIGS. 1 and 2 show a unitary ring 11 whose throat 12 is positioned, when the silencer is in operation as shown in FIG. it, slightly aft of an exhaust gas exit 13.
  • the ring 11 is carried by two or more rails 14 with the interposition of sliding shoes 15; the rails 14 form part of the stationary structure of the system, as can be seen in FIG. 4.
  • ring 11 In cruising flight the ring 11 is advanced into the position ll shown in FIG. 3 so as to restore the outer shape of the engine fairing.
  • a circular slot 16, visible in FIG. 3 can be left in front of the leading edge of the ring 11 so that the ring 17 formed by the folded channels can be supplied with external air and thus obviate possible extra baffle drag.
  • aspirator efficiency can be improved, more particularly as regards possible extra thrust at takeoff, if the rear part of the ring 11 forms a diffuser- -i.e., can open conically as it approaches its retracted position.
  • the ring 11 is subdivided into a number of sections 11a, 11b, 11c, etc. as can be seen in FIG. 6, each section having two pairs of shoes 15.
  • each rail 14 bends outwards from a place 18.
  • the ring elements can then pivot around the place 18, with a simultaneous increase in throat diameter Dc.
  • the resulting diffuser is at an angle to the nozzle axis.
  • Each section of the ring 11 has a member 19 which engages in the adjacent section.
  • FIG. 7 shows an embodiment using a pair of rails 12 and supports 15 comprising rollers 20.
  • FIGS. 8 and 9 show an extensible ring 11 comprising a number of main sections lie and intermediate sections 11f which are engaged in the main sections 112.
  • Each main sec tion is connected to the stationary structure of the silencer by four rods 21 -24 forming two parallelograms.
  • the ring takes up a position behind the zone 17 occupied by the folded channels and thus gives the nozzle exit a satisfactory shape, as can be seen in FIG. 10.
  • Movement is transmitted by a rod 25 connected at a place 26 to the rod 22.
  • a rod 25 connected at a place 26 to the rod 22.
  • the movements can be synchronized and only a single actuator needs to be used.
  • a silencer assembly for jet engines comprising in combination:
  • a jet ejection nozzle provided with a plurality of longitudinal air intake apertures regularly arranged around its axis in a portion adjacent its outlet end;

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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)
US718565A 1967-04-07 1968-04-03 Silencing assembly for jet engines Expired - Lifetime US3550721A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR101852A FR1525355A (fr) 1967-04-07 1967-04-07 Silencieux débrayable pour avion à réaction

Publications (1)

Publication Number Publication Date
US3550721A true US3550721A (en) 1970-12-29

Family

ID=8628358

Family Applications (1)

Application Number Title Priority Date Filing Date
US718565A Expired - Lifetime US3550721A (en) 1967-04-07 1968-04-03 Silencing assembly for jet engines

Country Status (6)

Country Link
US (1) US3550721A (en:Method)
BE (1) BE713074A (en:Method)
DE (1) DE1751079A1 (en:Method)
FR (1) FR1525355A (en:Method)
GB (1) GB1218631A (en:Method)
NL (1) NL6804667A (en:Method)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3647020A (en) * 1970-02-02 1972-03-07 Rohr Corp Jet propulsion apparatus and operating method
US3695387A (en) * 1970-09-08 1972-10-03 Rohr Corp Sound suppression system for fan jet engines
US3815360A (en) * 1971-04-16 1974-06-11 Rohr Industries Inc Combined infrared and sound suppressor for aircraft jet engine
US3830431A (en) * 1973-03-23 1974-08-20 Nasa Abating exhaust noises in jet engines
US4196585A (en) * 1976-10-04 1980-04-08 Chuiko Viktor M Ejector-type engine thrust augmentor
US5771681A (en) * 1996-09-17 1998-06-30 The Boeing Company Aircraft turbofan engine mixing apparatus
US5779150A (en) * 1996-10-01 1998-07-14 The Boeing Company Aircraft engine ejector nozzle
US5794434A (en) * 1996-10-09 1998-08-18 The Boeing Company Aircraft thrust reverser system with linearly translating inner and outer doors
US5826794A (en) * 1997-02-28 1998-10-27 The Boeing Company Aircraft scoop ejector nozzle
US5884843A (en) * 1996-11-04 1999-03-23 The Boeing Company Engine noise suppression ejector nozzle
US5908159A (en) * 1997-02-24 1999-06-01 The Boeing Company Aircraft chute ejector nozzle
US5910094A (en) * 1996-09-10 1999-06-08 The Boeing Company Aircraft labyrinth fire seal
US5941065A (en) * 1996-11-04 1999-08-24 The Boeing Company Stowable mixer ejection nozzle
US6010329A (en) * 1996-11-08 2000-01-04 Shrinkfast Corporation Heat gun with high performance jet pump and quick change attachments
US6227846B1 (en) 1996-11-08 2001-05-08 Shrinkfast Corporation Heat gun with high performance jet pump and quick change attachments
JP2007187161A (ja) * 2006-01-13 2007-07-26 Snecma 超音速航空機のターボファンジェットエンジン用の、可変領域を有するコア排気ミキサ
JP2008196484A (ja) * 2007-01-26 2008-08-28 Snecma 超音速機用複流ターボジェットの可変断面フローミキサ
WO2015040323A1 (fr) * 2013-09-23 2015-03-26 Snecma Tuyere a flux confluents de turbomachine comprenant un capot primaire a volets se chevauchant
US20160017815A1 (en) * 2013-03-12 2016-01-21 United Technologies Corporation Expanding shell flow control device
US10566097B2 (en) 2017-03-27 2020-02-18 Ge-Hitachi Nuclear Energy Americas Llc Intermixing feedwater sparger nozzles and methods for using the same in nuclear reactors

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3579993A (en) * 1969-08-04 1971-05-25 Rohr Corp Sound suppression system
US3618700A (en) * 1970-06-15 1971-11-09 Boeing Co Retracted noise suppression system
RU2182672C1 (ru) * 2001-01-15 2002-05-20 Акционерное общество открытого типа Авиамоторный научно-технический комплекс "Союз" Выходное двухмерное сопло для воздушно-реактивного двигателя

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3647020A (en) * 1970-02-02 1972-03-07 Rohr Corp Jet propulsion apparatus and operating method
US3695387A (en) * 1970-09-08 1972-10-03 Rohr Corp Sound suppression system for fan jet engines
US3815360A (en) * 1971-04-16 1974-06-11 Rohr Industries Inc Combined infrared and sound suppressor for aircraft jet engine
US3830431A (en) * 1973-03-23 1974-08-20 Nasa Abating exhaust noises in jet engines
US4196585A (en) * 1976-10-04 1980-04-08 Chuiko Viktor M Ejector-type engine thrust augmentor
US5910094A (en) * 1996-09-10 1999-06-08 The Boeing Company Aircraft labyrinth fire seal
US5771681A (en) * 1996-09-17 1998-06-30 The Boeing Company Aircraft turbofan engine mixing apparatus
US5779150A (en) * 1996-10-01 1998-07-14 The Boeing Company Aircraft engine ejector nozzle
US5794434A (en) * 1996-10-09 1998-08-18 The Boeing Company Aircraft thrust reverser system with linearly translating inner and outer doors
US5941065A (en) * 1996-11-04 1999-08-24 The Boeing Company Stowable mixer ejection nozzle
US5884843A (en) * 1996-11-04 1999-03-23 The Boeing Company Engine noise suppression ejector nozzle
US6010329A (en) * 1996-11-08 2000-01-04 Shrinkfast Corporation Heat gun with high performance jet pump and quick change attachments
US6227846B1 (en) 1996-11-08 2001-05-08 Shrinkfast Corporation Heat gun with high performance jet pump and quick change attachments
US5908159A (en) * 1997-02-24 1999-06-01 The Boeing Company Aircraft chute ejector nozzle
US5826794A (en) * 1997-02-28 1998-10-27 The Boeing Company Aircraft scoop ejector nozzle
JP2007187161A (ja) * 2006-01-13 2007-07-26 Snecma 超音速航空機のターボファンジェットエンジン用の、可変領域を有するコア排気ミキサ
JP2008196484A (ja) * 2007-01-26 2008-08-28 Snecma 超音速機用複流ターボジェットの可変断面フローミキサ
US20160017815A1 (en) * 2013-03-12 2016-01-21 United Technologies Corporation Expanding shell flow control device
WO2015040323A1 (fr) * 2013-09-23 2015-03-26 Snecma Tuyere a flux confluents de turbomachine comprenant un capot primaire a volets se chevauchant
FR3011038A1 (fr) * 2013-09-23 2015-03-27 Snecma Capot primaire a volets se chevauchant pour tuyere a flux confluents de turbomachine
GB2534498A (en) * 2013-09-23 2016-07-27 Snecma Confluent-flow nozzle of a turbine engine including a main cowl with overlapping flaps
US10167814B2 (en) 2013-09-23 2019-01-01 Safran Aircraft Engines Turbine engine nozzle having confluent streams and including a core cowl with overlapping flaps
GB2534498B (en) * 2013-09-23 2020-05-20 Snecma A turbine engine nozzle having confluent streams and including a core cowl with overlapping flaps
US10566097B2 (en) 2017-03-27 2020-02-18 Ge-Hitachi Nuclear Energy Americas Llc Intermixing feedwater sparger nozzles and methods for using the same in nuclear reactors

Also Published As

Publication number Publication date
BE713074A (en:Method) 1968-08-16
NL6804667A (en:Method) 1968-10-08
FR1525355A (fr) 1968-05-17
GB1218631A (en) 1971-01-06
DE1751079A1 (de) 1975-06-19

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