US2396952A - Muffler - Google Patents
Muffler Download PDFInfo
- Publication number
- US2396952A US2396952A US544367A US54436744A US2396952A US 2396952 A US2396952 A US 2396952A US 544367 A US544367 A US 544367A US 54436744 A US54436744 A US 54436744A US 2396952 A US2396952 A US 2396952A
- Authority
- US
- United States
- Prior art keywords
- gases
- members
- jacket
- conical
- discharge
- 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
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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
- F01N1/00—Silencing apparatus characterised by method of silencing
- F01N1/08—Silencing apparatus characterised by method of silencing by reducing exhaust energy by throttling or whirling
- F01N1/083—Silencing apparatus characterised by method of silencing by reducing exhaust energy by throttling or whirling using transversal baffles defining a tortuous path for the gases or successively throttling gas flow
-
- 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
- F01N3/00—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust
- F01N3/02—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust
- F01N3/05—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust by means of air, e.g. by mixing exhaust with air
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Definitions
- This invention relates to exhaust muiiiers for internal combustion engines.
- An object of this invention is to provide a muiiier embodying the provision of a suction means for drawing the gases out of the interior thereof so as to eliminate back pressure in the engine.
- Another object of this invention is to provide a muffler wherein the gases are mixed with air prior to the discharge of the gases into the atmosphere, the air mixing with the gases providing not only a suction for the removal of the gases, but also providing a cooling medium for cooling the gases prior to their discharge into the atmosphere, and the initial expansion of the gases before discharge so as to thereby eliminate the explosive noise when the gases are discharged into the atmosphere.
- a further object of this invention is to provide a muffler of this type which is designed particularly for airplane engines in which the forward end of the muflier is formed as a scoop for drawing in air which will maintain the mufller walls cool so that the metal will not disintegrate under the heat of the gases.
- Figures 1 and 10 show a longitudinal section of a mufiler constructed according to an embodiment of this invention
- Figure 2 is a detail front elevation of the device
- Figure 3 is a detail rear elevation of the device
- Figure 4 is a sectional view taken on the line 4-4 of Figure 1.
- the numeral I ll designates generally an outer jacket or shell which is substantially elliptical in transverse section and is provided with a flat bottom wall II.
- the bottom wall II has secured thereto a pair of longitudinally extending spaced apart L-shaped bracket members I2 and I3 which provide a means whereby the mufller may be secured to a suitable support.
- the front end of the jacket I is provided 'warclly reducing member or nozzle 2
- the intermediate portion I6 has secured thereto a cylindrical nipple or discharge member H.
- An inner shell I8 which is substantially elliptical in transverse section is disposed within the jacket It being substantially smaller in size than the jacket I0 so as to provide an air passage I9 between the outer surface of the inner member I8 and the jacket Ill.
- the inner member or shell I8 is secured to the upper side of the flat wall II and extends throughout the length of the wall H.
- the rear end of the inner shell or member I8 is formed with a truncated conical intake member which has secured to the rear small end thereof a for- The rear or large end of the nozzle 2
- the forward end of the inner shell or member It has secured thereto a forwardly tapering discharge member 23 and a nipple 24 extends from the small end of the discharge member 23 and is positioned within the junction of the outer members I5 and I6 terminating at its forward end within the rear portion of the intermediate tapered member I6, as shown in Figure 1a.
- the discharge member 24 forms a reduced air space 25 which will produce a venturi action so that when the air passes forwardly through the space 25 the burned gases in the discharge member 24 will be drawn out of this member and the air entering the forwardly enlarging member I6 will mix with the burned gases so that the gases can initially expand and thereby eliminate the major portion of the explosive noise before these gases are finally discharged from the discharge nipple I1.
- a plurality of radially arranged bracmg or spacing bars 26 are interposed between the outer shell I0 and the inner shell I 8 at spaced points along the length of these members.
- the inner member I 8 at its rear portion has mounted therein a conical member 21 provided with a plurality of openings 28 at a point rearwardly from the apex thereof.
- the smaller apex portion of the conical member 21 extends into the rearwardly reducing member 20, as shown in Figure 1, and the base or large end of the conical member 21 is secured as at 29 to the inner shell I8.
- the inner shell or member I8 has positioned therein a plurality of perforate baffle members 30 and ll. the latter being formed with a solid central portion 32.
- These baille members are spaced apart lengthwise oi the interior of the inner member is and the rearmost battle it is rovided with central perforations 3t and a solid outer portion 35.
- the staggering o the openings or perforations in the several baifles will term a tortuous passage for the gases passing through the inner member It.
- the inner member l8 at its forward portion has secured therein a conical member 36 which is formed with openings 31 and an open apex 38.
- the open apex 38 discharges centrally into the rearportion of the discharge member 24, as shown in Figu e 1a.
- the intake member 23 is adapted to be connected to the exhaust; or an internal combustion engine, and preferably,
- this engine is an airplane engine with the bracket members l2 and I3 secured lengthwise oi. the airplane and in a position where the scoop It will draw in air as the propellers connected to the engine are rotating.
- the exhaust gases will pass about the imperforate rear end portion of the conical member 2'7 and will initially enter the interior of the conical member through the perforations or openings rearwardiy of the apex thereof.
- the burned gases will then pass through the openings in the bafiies 30, 3t and 33 and will then enter the forward conical member 36. A portion of the gases will passcentrally through the conical member 36 and through the open apex thereof, whereas some oi. the burned gases will pass through the openings 3'5 in the conical member 36.
- the burned gases will enter the iorward discharge member 24 and will then mix in the mixing chamber 39 formed in the intermediate mem her It.
- the air flowing through the space H between the jacket i and the inner member It will pass through the space 25 and will form a suction in addition to providing an expansive medium where the burned gases can initially ex pand before being discharged through the for ward discharge nipple it into the atmosphere.
- the provision of the air space IS and the space 25 about the inner sheii it provides a cooling medium for maintaining the inner member it cool and this moving air also provides a means for eliminating back pressure on the engine due to the venturi action at the discharge end or the discharge member 24.
- the several parts forming the muiiier hereinbeiore described are secured together by spot welding or other suit-' able fastening means.
- the inner tubular member [8 may initially have the battles 3
- the bracing members 26 are welded or fixed to the tubular member is before insertion of this member in the jacket and after insertion in the jacket ID, the latter may be spot welded or the like to the bracing members and associated parts.
- a muflier comprising an inner tubular member, tapered members extending from the opposite ends of said inner member, an intake nipple connected to the reduced end of one of said tapered members, a pair of oppositely extending apertured conical members disposed within said inner tubular member and having the bases thereof secured to the latter with the apieces thereof outermost and with the bases thereof spaced apart, the apex of one of said conical members being formed with an opening, said conical members having the small ends thereof projecting into said tapered members, an outer jacket disposed in spaced relation about said inner tubular member, a flared scoop at one end of said jacket, a tapered jacket at the other end of said outer jacket and engaging loosely about an adjacent one of said first tapered members, a forwardly flared member extending from the small end of said tapered jacket, a forwardly extending discharge nipple extending from the forward smali end of the other of said tapered members and disposed'partly within said tapered jacket and partly within said forwardly flared member
Description
March 19, 1946. F. P. HUBER MUFFLER Filed Jul 11, 1944 2 Sheets-Sheet 1 Fm; Pffu Zer F. P. HUBER Filed July 11, 1944 MUFFLER fSheets-Sheet 2 grwamm' Patented Mar. 19, 1946 UNITED STATES PATENT OFFICE MUFFLER Frank P. Huber, New Orleans, La.
Application July 11, 1944, Serial No. 544,367
(or. 1s1-51) 1 Claim.
This invention relates to exhaust muiiiers for internal combustion engines.
An object of this invention is to provide a muiiier embodying the provision of a suction means for drawing the gases out of the interior thereof so as to eliminate back pressure in the engine.
Another object of this invention is to provide a muffler wherein the gases are mixed with air prior to the discharge of the gases into the atmosphere, the air mixing with the gases providing not only a suction for the removal of the gases, but also providing a cooling medium for cooling the gases prior to their discharge into the atmosphere, and the initial expansion of the gases before discharge so as to thereby eliminate the explosive noise when the gases are discharged into the atmosphere.
A further object of this invention is to provide a muffler of this type which is designed particularly for airplane engines in which the forward end of the muflier is formed as a scoop for drawing in air which will maintain the mufller walls cool so that the metal will not disintegrate under the heat of the gases.
With the foregoing objects and others which may hereinafter appear the invention consists of the novel construction, combination and arrangement of parts as will be more specifically referred to and illustrated in the accompanying drawings wherein is shown an embodiment of the invention, but it is to be understood that changes, modifications and variations may be resorted to which fall within the scope of the invention as claimed.
In the drawings:
Figures 1 and 10 show a longitudinal section of a mufiler constructed according to an embodiment of this invention,
Figure 2 is a detail front elevation of the device,
Figure 3 is a detail rear elevation of the device, and
Figure 4 is a sectional view taken on the line 4-4 of Figure 1.
Referring to the drawings, the numeral I ll designates generally an outer jacket or shell which is substantially elliptical in transverse section and is provided with a flat bottom wall II. The bottom wall II has secured thereto a pair of longitudinally extending spaced apart L-shaped bracket members I2 and I3 which provide a means whereby the mufller may be secured to a suitable support.
The front end of the jacket I is provided 'warclly reducing member or nozzle 2|.
with a flared scoop I4 for drawing air into the interior of the jacket and the rear portion of the jacket I0 is provided with a forwardly tapering member I5 having an oppositel flared tapered portion I6 secured to the reduced forward end thereof. The intermediate portion I6 has secured thereto a cylindrical nipple or discharge member H. An inner shell I8 which is substantially elliptical in transverse section is disposed within the jacket It being substantially smaller in size than the jacket I0 so as to provide an air passage I9 between the outer surface of the inner member I8 and the jacket Ill. The inner member or shell I8 is secured to the upper side of the flat wall II and extends throughout the length of the wall H. The rear end of the inner shell or member I8 is formed with a truncated conical intake member which has secured to the rear small end thereof a for- The rear or large end of the nozzle 2| has secured thereto or formed integral therewith a cylindrical nipple or intake member 22.
The forward end of the inner shell or member It has secured thereto a forwardly tapering discharge member 23 and a nipple 24 extends from the small end of the discharge member 23 and is positioned within the junction of the outer members I5 and I6 terminating at its forward end within the rear portion of the intermediate tapered member I6, as shown in Figure 1a.
The discharge member 24 forms a reduced air space 25 which will produce a venturi action so that when the air passes forwardly through the space 25 the burned gases in the discharge member 24 will be drawn out of this member and the air entering the forwardly enlarging member I6 will mix with the burned gases so that the gases can initially expand and thereby eliminate the major portion of the explosive noise before these gases are finally discharged from the discharge nipple I1. A plurality of radially arranged bracmg or spacing bars 26 are interposed between the outer shell I0 and the inner shell I 8 at spaced points along the length of these members.
The inner member I 8 at its rear portion has mounted therein a conical member 21 provided with a plurality of openings 28 at a point rearwardly from the apex thereof. The smaller apex portion of the conical member 21 extends into the rearwardly reducing member 20, as shown in Figure 1, and the base or large end of the conical member 21 is secured as at 29 to the inner shell I8. The inner shell or member I8 has positioned therein a plurality of perforate baffle members 30 and ll. the latter being formed with a solid central portion 32. These baille members are spaced apart lengthwise oi the interior of the inner member is and the rearmost battle it is rovided with central perforations 3t and a solid outer portion 35. The staggering o: the openings or perforations in the several baifles will term a tortuous passage for the gases passing through the inner member It. The inner member l8 at its forward portion has secured therein a conical member 36 which is formed with openings 31 and an open apex 38. The open apex 38 discharges centrally into the rearportion of the discharge member 24, as shown in Figu e 1a.
In the use or this mufller the intake member 23 is adapted to be connected to the exhaust; or an internal combustion engine, and preferably,
this engine is an airplane engine with the bracket members l2 and I3 secured lengthwise oi. the airplane and in a position where the scoop It will draw in air as the propellers connected to the engine are rotating. The exhaust gases will pass about the imperforate rear end portion of the conical member 2'7 and will initially enter the interior of the conical member through the perforations or openings rearwardiy of the apex thereof.
The burned gases will then pass through the openings in the bafiies 30, 3t and 33 and will then enter the forward conical member 36. A portion of the gases will passcentrally through the conical member 36 and through the open apex thereof, whereas some oi. the burned gases will pass through the openings 3'5 in the conical member 36. The burned gases will enter the iorward discharge member 24 and will then mix in the mixing chamber 39 formed in the intermediate mem her It. The air flowing through the space H between the jacket i and the inner member It will pass through the space 25 and will form a suction in addition to providing an expansive medium where the burned gases can initially ex pand before being discharged through the for ward discharge nipple it into the atmosphere.
The provision of the air space IS and the space 25 about the inner sheii it provides a cooling medium for maintaining the inner member it cool and this moving air also provides a means for eliminating back pressure on the engine due to the venturi action at the discharge end or the discharge member 24. The several parts forming the muiiier hereinbeiore described are secured together by spot welding or other suit-' able fastening means. In the assembly or the device the inner tubular member [8 may initially have the battles 3| and 33 welded or flxed therein after which the conical members can be inserted and welded and the tapered end portions 20 and 23 may then be electrically welded or the like to the ends of the tubular member It. The bracing members 26 are welded or fixed to the tubular member is before insertion of this member in the jacket and after insertion in the jacket ID, the latter may be spot welded or the like to the bracing members and associated parts.
What I claim is:
A muflier comprising an inner tubular member, tapered members extending from the opposite ends of said inner member, an intake nipple connected to the reduced end of one of said tapered members, a pair of oppositely extending apertured conical members disposed within said inner tubular member and having the bases thereof secured to the latter with the apieces thereof outermost and with the bases thereof spaced apart, the apex of one of said conical members being formed with an opening, said conical members having the small ends thereof projecting into said tapered members, an outer jacket disposed in spaced relation about said inner tubular member, a flared scoop at one end of said jacket, a tapered jacket at the other end of said outer jacket and engaging loosely about an adjacent one of said first tapered members, a forwardly flared member extending from the small end of said tapered jacket, a forwardly extending discharge nipple extending from the forward smali end of the other of said tapered members and disposed'partly within said tapered jacket and partly within said forwardly flared member and a plurality of apertured bafiles fixed in said inner tubular member between the bases of said conical members and having the apertures anranged to form a tortuous passage.
FRANK P. man.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US544367A US2396952A (en) | 1944-07-11 | 1944-07-11 | Muffler |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US544367A US2396952A (en) | 1944-07-11 | 1944-07-11 | Muffler |
Publications (1)
Publication Number | Publication Date |
---|---|
US2396952A true US2396952A (en) | 1946-03-19 |
Family
ID=24171885
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US544367A Expired - Lifetime US2396952A (en) | 1944-07-11 | 1944-07-11 | Muffler |
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US (1) | US2396952A (en) |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2495386A (en) * | 1946-11-07 | 1950-01-24 | Parsons & Marine Eng Turbine | Combustion unit |
US2511359A (en) * | 1948-03-27 | 1950-06-13 | William B Mcleod | Muffler with fluid mingling and side branch chambers |
US2685936A (en) * | 1950-08-08 | 1954-08-10 | Lockheed Aircraft Corp | Sound reduction equipment for use with jet-propulsion units |
US2987136A (en) * | 1955-03-31 | 1961-06-06 | Power Jets Res & Dev Ltd | Apparatus for reducing noise |
US3053340A (en) * | 1958-07-21 | 1962-09-11 | Gen Electric | Noise suppression nozzle |
US3146072A (en) * | 1961-09-19 | 1964-08-25 | Morgan Rubie Freddie | Fume eliminator |
US3279168A (en) * | 1964-05-01 | 1966-10-18 | Stephen G Gerlach | Muffler and oxidizer means |
US4265332A (en) * | 1979-06-21 | 1981-05-05 | Fmc Corporation | Heat extracting muffler system |
US5722235A (en) * | 1996-08-26 | 1998-03-03 | Ccl, Inc. | Exhaust gas back pressure attenuator for truck exhaust stacks |
US5824970A (en) * | 1994-07-20 | 1998-10-20 | Gracia; Albert Louis | Marine engine silencer having internal apertured baffle and weir plate |
EP1241328A1 (en) * | 2001-03-13 | 2002-09-18 | J. Eberspächer GmbH & Co. KG | Exhaust gas cooling element for an exhaust system of an internal combustion engine |
US6564901B2 (en) | 2000-03-09 | 2003-05-20 | Woodrow E. Woods | Muffler for marine engine |
US20080190689A1 (en) * | 2007-02-12 | 2008-08-14 | Ballard Ebbin C | Inserts for engine exhaust systems |
US7458208B1 (en) * | 2007-03-21 | 2008-12-02 | Dando Jr Clifford Benton | Exhaust gas extractor system |
US20090321181A1 (en) * | 2007-02-12 | 2009-12-31 | Ballard Iii Ebbin C | Inserts for engine exhaust systems |
US20110048847A1 (en) * | 2009-09-02 | 2011-03-03 | United States Of America As Represented By The Secretary Of The Navy | Noise attenuation device for reducing noise attenuation in a jet engine test cell |
US7918310B1 (en) * | 2009-09-02 | 2011-04-05 | The United States Of America As Represented By The Secretary Of The Navy | Noise attenuation device for reducing jet engine noise during testing |
WO2014128080A1 (en) * | 2013-02-19 | 2014-08-28 | Bayerische Motoren Werke Aktiengesellschaft | Motor vehicle having an exhaust system |
WO2015089589A1 (en) * | 2013-12-19 | 2015-06-25 | Rowe Heath | Fire prevention shield |
US20170350301A1 (en) * | 2015-03-24 | 2017-12-07 | Bayerische Motoren Werke Aktiengesellschaft | Air Gap-Insulated Muffler |
-
1944
- 1944-07-11 US US544367A patent/US2396952A/en not_active Expired - Lifetime
Cited By (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2495386A (en) * | 1946-11-07 | 1950-01-24 | Parsons & Marine Eng Turbine | Combustion unit |
US2511359A (en) * | 1948-03-27 | 1950-06-13 | William B Mcleod | Muffler with fluid mingling and side branch chambers |
US2685936A (en) * | 1950-08-08 | 1954-08-10 | Lockheed Aircraft Corp | Sound reduction equipment for use with jet-propulsion units |
US2987136A (en) * | 1955-03-31 | 1961-06-06 | Power Jets Res & Dev Ltd | Apparatus for reducing noise |
US3053340A (en) * | 1958-07-21 | 1962-09-11 | Gen Electric | Noise suppression nozzle |
US3146072A (en) * | 1961-09-19 | 1964-08-25 | Morgan Rubie Freddie | Fume eliminator |
US3279168A (en) * | 1964-05-01 | 1966-10-18 | Stephen G Gerlach | Muffler and oxidizer means |
US4265332A (en) * | 1979-06-21 | 1981-05-05 | Fmc Corporation | Heat extracting muffler system |
US5824970A (en) * | 1994-07-20 | 1998-10-20 | Gracia; Albert Louis | Marine engine silencer having internal apertured baffle and weir plate |
US5722235A (en) * | 1996-08-26 | 1998-03-03 | Ccl, Inc. | Exhaust gas back pressure attenuator for truck exhaust stacks |
US20040026166A1 (en) * | 2000-03-09 | 2004-02-12 | Woods Woodrow E. | Muffler for marine engine |
US6564901B2 (en) | 2000-03-09 | 2003-05-20 | Woodrow E. Woods | Muffler for marine engine |
EP1241328A1 (en) * | 2001-03-13 | 2002-09-18 | J. Eberspächer GmbH & Co. KG | Exhaust gas cooling element for an exhaust system of an internal combustion engine |
US7905321B2 (en) * | 2007-02-12 | 2011-03-15 | Ballard Iii Ebbin C | Inserts for engine exhaust systems |
US20080190689A1 (en) * | 2007-02-12 | 2008-08-14 | Ballard Ebbin C | Inserts for engine exhaust systems |
US20090321181A1 (en) * | 2007-02-12 | 2009-12-31 | Ballard Iii Ebbin C | Inserts for engine exhaust systems |
US7458208B1 (en) * | 2007-03-21 | 2008-12-02 | Dando Jr Clifford Benton | Exhaust gas extractor system |
US20110048847A1 (en) * | 2009-09-02 | 2011-03-03 | United States Of America As Represented By The Secretary Of The Navy | Noise attenuation device for reducing noise attenuation in a jet engine test cell |
US7918310B1 (en) * | 2009-09-02 | 2011-04-05 | The United States Of America As Represented By The Secretary Of The Navy | Noise attenuation device for reducing jet engine noise during testing |
WO2014128080A1 (en) * | 2013-02-19 | 2014-08-28 | Bayerische Motoren Werke Aktiengesellschaft | Motor vehicle having an exhaust system |
WO2015089589A1 (en) * | 2013-12-19 | 2015-06-25 | Rowe Heath | Fire prevention shield |
US20170030263A1 (en) * | 2013-12-19 | 2017-02-02 | Heath ROWE | Fire prevention shield |
US10087836B2 (en) * | 2013-12-19 | 2018-10-02 | Heath ROWE | Fire prevention shield |
AU2014366841B2 (en) * | 2013-12-19 | 2019-01-31 | Heath ROWE | Fire prevention shield |
US20170350301A1 (en) * | 2015-03-24 | 2017-12-07 | Bayerische Motoren Werke Aktiengesellschaft | Air Gap-Insulated Muffler |
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