US3685612A - Gas ejection device with a silencer feature - Google Patents

Gas ejection device with a silencer feature Download PDF

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Publication number
US3685612A
US3685612A US139402A US3685612DA US3685612A US 3685612 A US3685612 A US 3685612A US 139402 A US139402 A US 139402A US 3685612D A US3685612D A US 3685612DA US 3685612 A US3685612 A US 3685612A
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US
United States
Prior art keywords
elementary
fairing
nozzle
ducts
subdivided
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
US139402A
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English (en)
Inventor
Jean Henri Bertin
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.)
Bertin Technologies SAS
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Bertin et Cie SA
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Filing date
Publication date
Application filed by Bertin et Cie SA filed Critical Bertin et Cie SA
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
    • F01N13/20—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00 having flared outlets, e.g. of fish-tail shape
    • 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
    • F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
    • 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
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet

Definitions

  • ABSTRACT U-S An ejection System Comprises a flat nozzle 181/33HD 239/265 opening into a flat fairing open at both ends to form [51] Int Cl B64! 33/66 o 1/12 F01 n & therewith a static pump or ejector.
  • the nozzle is sub- [58] Fie'ld 181760 72 43 51 33 HQ divided into a succession of elementary nozzles 181/33 50 5 7 producing a laminar jet of hot gases, and the fairing is likewise subdivided into as many separate juxtaposed elementary ducts as there are elementary nozzles.
  • Each such elementary nozzle is associated with a [56] References Clted respective elementary duct to form therewith an ele- UNITED STATES PATENTS memary Static P p- 1,357,079 10/1920 Patch ..l8l/43 9 Chain, 6 Drawing Figures 8 9 7 S ,1, i 1 a 31 7 2 a, 4 Y MH EJ- PATENTEU ⁇ 972 3.685.612
  • This invention relates to a flat fishtail-shaped nozzle for exhausting hot gases such as the hot exhaust gases of a turbojet or other jet engine.
  • Fishtail nozzles are familiar and are described in French Pat. Nos. 1,164,692 and 1,207,634 and in Guienne et al. US. Pat. No. 3,212,700; these disclosures also indicate that such nozzles can, with advantage, be combined with a flat fairing open at both ends to form a static pump and that the nozzles have a silencer effect.
  • the fishtail nozzle which in association with a flat fairing has a static pump effect is subdivided into a sequence of elementary nozzles producing a laminar stream of hot gases, and the fairing is subdivided into as many separate juxtaposed elementary ducts as there are elementary nozzles, each elementary nozzle being associated with an elementary duct to form an elementary static pump.
  • the elementary nozzles are cruciform and the elementary ducts are of rectangular cross-section, to improve the static-pump and silencer effects.
  • the flat fairing is divided into compartments by sound-damping partitions which serve to bound the elementary ducts.
  • Flaps for controlling the fairing exit cross-section can be fitted very readily and efiectively to a construction of this kind which is subdivided into juxtaposed elementary static pump; the flaps, which are adjustable, are articulated transversely of the spread of the jet or stream and can be short lengthwise of the flow.
  • the device according to this invention is of use not only in aircraft propulsion but also in surface vehicle propulsion, e.g. ground effect machines; it also has possibilities in other fields, e.g. fog dispersal, snowand frost-clearing aerosolizing.
  • FIG. 1 is a view in side elevation of a jet engine having an ejection device according to this invention, the fuselage and the staticpump fairing being assumed to be transparent to clarify the drawing;
  • FIG. 2 is a plan view in similar conditions
  • FIGS. 3 and 4 are perspective views to a larger scale, and with parts broken away, of the rear terminal part, and
  • FIGS. 5 and 6 are views similar to FIGS. 3 and 4 of two constructional variants.
  • a turbojet engine 1 has an air inlet 2 which intakes air through a sound-insulated tube 3 which has a front inlet 4 and forms a forward extension of a pod 5.
  • An exhaust nozzle 6 for the hot gases has a flat fishtail shape and terminates in an outlet portion 7 opening into fairing 9 which is in shape substantially oblong and which comprises a solid sheetmetal outer casing 10 and an inner sheet-metal perforate casing or wall 11 which serves to bound a convergent-divergent duct, the nozzle outlet plane 7 being disposed at the throat of the convergent-divergent duct.
  • the space between the casings or walls 10 and 11 can be either filled with a sound insulant, such as mineral wool, or left empty, in which event the space acts as a resonator, the diameter of the apertures in the wall 11 being determined in dependence upon the predominant frequency of the exhaust gas noise.
  • a sound insulant such as mineral wool
  • the nozzle outlet crosssection 7 takes the form of a sequence of cruciform elements 8 from which the hot gases issue in the form of thin lamina at right angles to one another.
  • Fairing 9 is subdivided into compartments by sound-insulated longitudinal partitions 20 so that each cruciform element 8 is disposed separately in a substantially rectangular cross-section elementary duct 12.
  • the ducts 12 make up a group of ejectors or static pumps whose leading edge, represented by a line A-A, is a series of fresh air inlets 15 positioned upstream of the outlet planes of the cruciform elements 8, the fresh air being intaken as indicated by arrows f.
  • the leading edge A-A can either be straight or have a pattern such as shown by way of example in FIGS. 2 and 3.
  • the shaded zone represents the volume affected by the hot engine exhaust gases; the total delivery through the ducts 12 is the result of the exhaust gases mixing with the fresh air f and is represented by arrows F.
  • flaps l3l3 are disposed at the trailing edge of the fairing 9 and can pivot about transverse pivots orspindles l414.
  • the flaps 1313 which are paired, are in this embodiment disposed in extension of the fairing top and bottom surfaces.
  • the fiaps13 which are stiffened and balanced by elements 16, are disposed downstream of the partitions 20 and can be operated to pivot around their pivot 14 so as to control the thrust vector direction of the engine 1.
  • the fresh-air inlet line A-A is perpendicular to the engine axis so that the front cross-section is annular, the elementary fresh-air inlets 15 being disposed in the same plane as one another in a ring around the nozzle 6.
  • Two series of individual flaps 17 are disposed in the rear portion of the fairing 9, between the insulated partitions 20 and in the prolongation of the fairing top and bottom surfaces.
  • An ejection device comprising a source of hot gases, a flat fishtail nozzle supplied with hot gas from said source and subdivided into a succession of elementary nozzles designed to produce a laminar hot gaseous jet, and a flat fairing open at both ends and accommodating therein said fishtail nozzle, said fairing being likewise to said fishtail nozzle subdivided into as many separate juxtaposed elementary ducts as there are elementary nozzles, each elementary nozzle and respective elementary duct forming together an elementary static pump.
  • a device wherein the elementary nozzles are cruciform and eject the hot gases in thin lamina at right angles to one another.
  • a device according to claim 1 wherein the elementary ducts are of rectangular cross-section.
  • a device according to claim 1 wherein the fairing is divided into compartments by sound-damping partitions which serve to bound the elementary ducts.
  • the fairing is double-walled and comprises a continuous outer wall and a perforate inner wall bounding a convergentdivergent channel, the fishtail nozzle extending to the throat of the channel.
  • a device according to claim 5 wherein the space between the two fairing walls is filled with sound-damping material.
  • a device wherein the space between the two fairing walls is empty and acts as a resonator, the diameter of the apertures in the perforate wall being determined in dependence upon the predominant frequency of exhaust gas noise.
  • a device according to claim 1 further comprising control flaps fitted at the exit of the fairing and articulated transversely of the spread of the stream.
  • a device wherein the flaps are subdivided into elementary flaps each associated with one of the elementary ducts of the fairing.

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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)
US139402A 1970-05-04 1971-05-03 Gas ejection device with a silencer feature Expired - Lifetime US3685612A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7016227A FR2087076A5 (fr) 1970-05-04 1970-05-04

Publications (1)

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US3685612A true US3685612A (en) 1972-08-22

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US139402A Expired - Lifetime US3685612A (en) 1970-05-04 1971-05-03 Gas ejection device with a silencer feature

Country Status (5)

Country Link
US (1) US3685612A (fr)
CA (1) CA927614A (fr)
DE (1) DE2121485A1 (fr)
FR (1) FR2087076A5 (fr)
GB (1) GB1345786A (fr)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4128769A (en) * 1976-09-27 1978-12-05 The Garrett Corporation Eductor muffler
US5699965A (en) * 1989-06-30 1997-12-23 Sikorsky Aircraft Corporation Infrared suppressor for a gas turbine engine
US5717172A (en) * 1996-10-18 1998-02-10 Northrop Grumman Corporation Sound suppressor exhaust structure
US5992140A (en) * 1997-06-24 1999-11-30 Sikorsky Aircraft Corporation Exhaust nozzle for suppressing infrared radiation
US6016651A (en) * 1997-06-24 2000-01-25 Sikorsky Aircraft Corporation Multi-stage mixer/ejector for suppressing infrared radiation
US6055804A (en) * 1997-07-23 2000-05-02 Sikorsky Aircraft Corporation Turning vane arrangement for IR suppressors
US6122907A (en) * 1998-05-11 2000-09-26 Sikorsky Aircraft Corporation IR suppressor
US6354538B1 (en) * 1999-10-25 2002-03-12 Rohr, Inc. Passive control of hot air injection for swirling rotational type anti-icing system
US20070186556A1 (en) * 2006-02-13 2007-08-16 General Electric Company Methods and apparatus for operating a pulse detonation engine
US20090000304A1 (en) * 2007-06-28 2009-01-01 Honeywell International, Inc. Integrated support and mixer for turbo machinery
US20100224348A1 (en) * 2009-03-03 2010-09-09 Rolls-Royce Deutschland Ltd & Co Kg Method for the manufacture of an ejector nozzle tube
US20130327417A1 (en) * 2012-06-07 2013-12-12 Jeffrey L. Gardner Self aligning venturi pipe assembly
US10150438B2 (en) * 2017-05-03 2018-12-11 Nissan North America, Inc. Rear exhaust finisher assembly
US20230112668A1 (en) * 2021-10-11 2023-04-13 Boom Technology, Inc. Dissimilarly shaped aircraft nozzles with tandem mixing devices, and associated systems and methods

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4295332A (en) * 1978-11-13 1981-10-20 General Electric Company Infrared suppressor system
GB2185718B (en) * 1986-01-23 1989-11-01 Rolls Royce Exhaust nozzle for a gas turbine engine
US4835961A (en) * 1986-04-30 1989-06-06 United Technologies Corporation Fluid dynamic pump
GB2240364B (en) * 1990-01-27 1994-09-28 S & C Thermofluids Ltd Combustion engines improvements
GB2249140B (en) * 1990-08-30 1994-12-07 S & C Thermofluids Ltd Aircraft engine noise suppression
FR2740832B1 (fr) * 1995-11-02 1998-01-02 Onera (Off Nat Aerospatiale) Arriere-corps de turboreacteur a double flux
DE102008023816A1 (de) * 2008-05-15 2009-11-19 Mtu Aero Engines Gmbh Mischdüsenaufbau

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1357079A (en) * 1919-06-19 1920-10-26 Harry M Patch Muffler
DE441932C (de) * 1925-09-13 1927-03-16 Hans Erich Koch Vakuum-Auspufftopf und Schalldaempfer fuer Brennkraftmaschinen
FR657569A (fr) * 1927-11-28 1929-05-24 Perfectionnements aux pots d'échappement
FR725510A (fr) * 1931-10-31 1932-05-13 Silencieux particulièrement destiné aux moteurs d'aviation et formant à la fois radiateur et pare-flammes
FR859758A (fr) * 1939-05-27 1940-12-28 Perfectionnements aux pare-flammes
FR865279A (fr) * 1940-04-29 1941-05-17 Perfectionnement aux pare-flammes silencieux
US2396208A (en) * 1943-03-08 1946-03-05 Anemostat Corp Method of and means for treating gases
US3527318A (en) * 1968-07-31 1970-09-08 Bertin & Cie Jet-engine silencer

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1357079A (en) * 1919-06-19 1920-10-26 Harry M Patch Muffler
DE441932C (de) * 1925-09-13 1927-03-16 Hans Erich Koch Vakuum-Auspufftopf und Schalldaempfer fuer Brennkraftmaschinen
FR657569A (fr) * 1927-11-28 1929-05-24 Perfectionnements aux pots d'échappement
FR725510A (fr) * 1931-10-31 1932-05-13 Silencieux particulièrement destiné aux moteurs d'aviation et formant à la fois radiateur et pare-flammes
FR859758A (fr) * 1939-05-27 1940-12-28 Perfectionnements aux pare-flammes
FR865279A (fr) * 1940-04-29 1941-05-17 Perfectionnement aux pare-flammes silencieux
US2396208A (en) * 1943-03-08 1946-03-05 Anemostat Corp Method of and means for treating gases
US3527318A (en) * 1968-07-31 1970-09-08 Bertin & Cie Jet-engine silencer

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4128769A (en) * 1976-09-27 1978-12-05 The Garrett Corporation Eductor muffler
US5699965A (en) * 1989-06-30 1997-12-23 Sikorsky Aircraft Corporation Infrared suppressor for a gas turbine engine
US5717172A (en) * 1996-10-18 1998-02-10 Northrop Grumman Corporation Sound suppressor exhaust structure
WO1998017898A1 (fr) * 1996-10-18 1998-04-30 Northrop Grumman Corporation Structure d'evacuation a silencieux
EP0868596A1 (fr) * 1996-10-18 1998-10-07 Northrop Grumman Corporation Structure d'evacuation a silencieux
EP0868596A4 (fr) * 1996-10-18 2000-04-19 Northrop Grumman Corp Structure d'evacuation a silencieux
US5992140A (en) * 1997-06-24 1999-11-30 Sikorsky Aircraft Corporation Exhaust nozzle for suppressing infrared radiation
US6016651A (en) * 1997-06-24 2000-01-25 Sikorsky Aircraft Corporation Multi-stage mixer/ejector for suppressing infrared radiation
US6055804A (en) * 1997-07-23 2000-05-02 Sikorsky Aircraft Corporation Turning vane arrangement for IR suppressors
US6122907A (en) * 1998-05-11 2000-09-26 Sikorsky Aircraft Corporation IR suppressor
US6354538B1 (en) * 1999-10-25 2002-03-12 Rohr, Inc. Passive control of hot air injection for swirling rotational type anti-icing system
US20070186556A1 (en) * 2006-02-13 2007-08-16 General Electric Company Methods and apparatus for operating a pulse detonation engine
US7836682B2 (en) * 2006-02-13 2010-11-23 General Electric Company Methods and apparatus for operating a pulse detonation engine
US20090000304A1 (en) * 2007-06-28 2009-01-01 Honeywell International, Inc. Integrated support and mixer for turbo machinery
US7882696B2 (en) * 2007-06-28 2011-02-08 Honeywell International Inc. Integrated support and mixer for turbo machinery
US20100224348A1 (en) * 2009-03-03 2010-09-09 Rolls-Royce Deutschland Ltd & Co Kg Method for the manufacture of an ejector nozzle tube
US8782896B2 (en) 2009-03-03 2014-07-22 Rolls-Royce Deutschland Ltd & Co Kg Method for the manufacture of an ejector nozzle tube
US20130327417A1 (en) * 2012-06-07 2013-12-12 Jeffrey L. Gardner Self aligning venturi pipe assembly
US10150438B2 (en) * 2017-05-03 2018-12-11 Nissan North America, Inc. Rear exhaust finisher assembly
US20230112668A1 (en) * 2021-10-11 2023-04-13 Boom Technology, Inc. Dissimilarly shaped aircraft nozzles with tandem mixing devices, and associated systems and methods

Also Published As

Publication number Publication date
CA927614A (en) 1973-06-05
DE2121485A1 (de) 1971-11-25
FR2087076A5 (fr) 1971-12-31
GB1345786A (en) 1974-02-06

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