US20040163886A1 - Air turbine for combustion engine - Google Patents
Air turbine for combustion engine Download PDFInfo
- Publication number
- US20040163886A1 US20040163886A1 US10/756,440 US75644004A US2004163886A1 US 20040163886 A1 US20040163886 A1 US 20040163886A1 US 75644004 A US75644004 A US 75644004A US 2004163886 A1 US2004163886 A1 US 2004163886A1
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- Prior art keywords
- tube
- inlet
- outlet
- air
- housing
- 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.)
- Abandoned
Links
- 238000002485 combustion reaction Methods 0.000 title abstract description 9
- 230000006698 induction Effects 0.000 claims abstract description 27
- 239000007789 gas Substances 0.000 claims description 12
- 241000510032 Ellipsaria lineolata Species 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 239000012530 fluid Substances 0.000 description 4
- 238000009987 spinning Methods 0.000 description 4
- 230000001419 dependent effect Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 239000011888 foil Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 239000003779 heat-resistant material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
Images
Classifications
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- 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
- F01N1/086—Silencing apparatus characterised by method of silencing by reducing exhaust energy by throttling or whirling having means to impart whirling motion to the gases
- F01N1/088—Silencing apparatus characterised by method of silencing by reducing exhaust energy by throttling or whirling having means to impart whirling motion to the gases using vanes arranged on gas flow path or gas flow tubes with tangentially directed apertures
-
- 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
- F01N1/02—Silencing apparatus characterised by method of silencing by using resonance
-
- 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
-
- 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
- F01N1/16—Silencing apparatus characterised by method of silencing by using movable parts
- F01N1/166—Silencing apparatus characterised by method of silencing by using movable parts for changing gas flow path through the silencer or for adjusting the dimensions of a chamber or a pipe
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/12—Intake silencers ; Sound modulation, transmission or amplification
- F02M35/1205—Flow throttling or guiding
- F02M35/1216—Flow throttling or guiding by using a plurality of holes, slits, protrusions, perforations, ribs or the like; Surface structures; Turbulence generators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/12—Intake silencers ; Sound modulation, transmission or amplification
- F02M35/1205—Flow throttling or guiding
- F02M35/1227—Flow throttling or guiding by using multiple air intake flow paths, e.g. bypass, honeycomb or pipes opening into an expansion chamber
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/12—Intake silencers ; Sound modulation, transmission or amplification
- F02M35/1205—Flow throttling or guiding
- F02M35/1233—Flow throttling or guiding by using expansion chambers in the air intake flow path
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D9/00—Controlling engines by throttling air or fuel-and-air induction conduits or exhaust conduits
- F02D9/02—Controlling engines by throttling air or fuel-and-air induction conduits or exhaust conduits concerning induction conduits
- F02D2009/0201—Arrangements; Control features; Details thereof
- F02D2009/0283—Throttle in the form of an expander
Definitions
- the present invention relates to air turbine devices suitable for use in the intake or exhaust of a combustion engine.
- FIG. 1 is a cross-sectional side view of a first embodiment of an air turbine device in accordance with the present invention
- FIG. 2 is a cross-sectional end view of an induction chamber of FIG. 1;
- FIG. 3 is an end view of an airfoil of FIG. 1;
- FIG. 4 is an end view of a vortex ring of FIG. 1;
- FIG. 5 is a cross-sectional side view of the air turbine device of FIG. 1 illustrating the flow of air or gases through the device;
- FIG. 6 is another cross-sectional side view of the air turbine device of FIG. 1 illustrating the flow of air or gases from the induction chamber into the expansion chamber;
- FIG. 7 is a cross-sectional side view of a second embodiment of an air turbine device in accordance with the present invention attached to an exhaust system of a combustion engine;
- FIG. 8 is a cross-sectional side view of a third embodiment of an air turbine device in accordance with the present invention attached to an exhaust system of a combustion engine;
- FIG. 9 is a cross-sectional side view of a fourth embodiment of an air turbine device in accordance with the present invention.
- FIG. 10 is a cross-sectional side view of another embodiment of an air turbine device in accordance with the present invention.
- FIG. 11 is a cross-sectional end view of an expansion chamber housing an airfoil supported by a plurality of blades in accordance with the present invention
- FIG. 12 is a cross-sectional side view of an alternative embodiment of an air turbine device in accordance with the present invention.
- FIG. 13 is a cross-sectional side view of an alternative embodiment of an air turbine device in accordance with the present invention.
- FIG. 14 is a cross-sectional side view of an alternative embodiment of an air turbine device in accordance with the present invention.
- FIG. 1 an air turbine device, generally indicated at 10 , in accordance with an embodiment of the present invention.
- the air turbine device 10 is comprised of an outer housing 12 having a generally cylindrical shape.
- the housing 12 defines an inlet port 14 and an outlet port 16 .
- An inlet tube 18 is secured to the inlet port 14 for attachment of the air turbine device 10 to an exhaust system of a vehicle (not shown).
- the inlet tube 18 is provided with a pair of vortex rings 19 and 21 to help form a vortexial flow of air through the air turbine device 10 .
- the housing 12 defines an expansion chamber 20 which extends from the inlet 14 to the outlet 16 .
- the induction tube 22 is housed within the housing 12 .
- the induction tube 22 is comprised of an elongate tubular member having a plurality of perforations 24 formed therein.
- the perforations 24 are louvers which extend into the induction chamber 30 formed by the tube 22 .
- the louvers are formed by stamping or cutting the exterior wall 32 of the tube 22 to force portions 34 of the wall 32 into the interior of the tube 22 .
- the louvers 36 are preferably formed in a helical pattern around the tube 22 . It is also contemplated that one or more spiral or helical slits may be provided in the tube 22 to accomplish a similar effect.
- the terms louvers or perforations are intended to include such structure.
- the louvers 36 extend around the interior surface 38 of the tube 22 and face in a direction so as to encourage air flowing toward the outlet 40 of the tube to flow from the tube 22 into the expansion chamber 20 .
- a pair of vortex rings 42 and 44 are secured within the tube 22 proximate the outlet 40 of the tube 22 .
- the vortex rings 42 and 44 provide a slight amount of back pressure to the air turbine device, which is sometimes necessary to the operation of some gas engines.
- the vortex rings help to maintain the vortexial flow of air as the air leaves the outlet 40 .
- a disc-shaped member 50 Attached to the inlet 46 of the tube 22 is a disc-shaped member 50 which extends across the expansion chamber proximate the inlet 14 of the housing 12 .
- the disc-shaped member 50 forms an airfoil in the path of the air flowing through the housing 12 .
- This airfoil 22 defines a central aperture 52 which is in fluid communication with the inner vortex chamber 30 .
- the airfoil 22 has a diameter that is less than the diameter defined by the inner surface 54 of the housing 12 . As such, air entering the inlet tube 18 can either flow through the aperture 52 or through the annular space 56 formed between the airfoil 50 and the inner surface 54 of the housing 12 .
- FIG. 3 illustrates a front view of the airfoil 50 shown in FIG. 1.
- the airfoil 50 is provided with the circular aperture 52 which is concentric with the airfoil 50 .
- the size of the airfoil 50 as well as the diameter of the aperture 52 is dependent upon the flow of air from the exhaust of the combustion engine.
- the size of the vortex expansion chamber is dependent upon the diameter of the inlet coupled thereto.
- the diameter of the expansion chamber is defined by 1.5 times the inlet pipe diameter.
- the length of the expansion chamber to accommodate the second harmonic resonance is 2.0 times the diameter of the expansion chamber.
- the length of the expansion chamber to accommodate the third harmonic resonance is 3.5 times the diameter of the expansion chamber.
- the outermost airfoil diameter is approximately 5.4 inches and the diameter of the aperture or bore of the airfoil is approximately 1.6 inches.
- the area of the annular space between the airfoil and the expansion chamber and the area of the aperture are sized to produce the most efficient flow of air through the device.
- the ratio of air passing around the airfoil compared to the air passing through the airfoil for a six inch diameter expansion chamber is approximately 2.7 to 1.
- FIG. 4 illustrates a vortex ring, such as vortex ring 19 shown in FIG. 1. Similar to the dimensions of the airfoil 50 , the size of the vortex ring 19 is dependent upon the inner diameter of the inlet tube 18 to which the vortex ring 19 is attached. The vortex ring 19 extends into the inlet tube to form a slight constriction but not enough to cause any appreciable restriction of flow therethrough. Obviously, as shown in FIG. 1, the outer diameter of the vortex ring 19 is defined by and thus equal to the inner diameter of the inlet tube 18 .
- FIG. 5 the flow of exhaust 60 through the air turbine device 10 is illustrated.
- the air is directed either through 62 or around 64 and 66 the airfoil 50 .
- the air passing around the airfoil 50 will necessarily be at a higher velocity than the air 62 that flows directly through the aperture 52 .
- the faster moving air 64 and 66 will create a low pressure zone within the outer vortex or expansion chamber 20 .
- the air 62 entering the inner vortex or induction chamber 30 will be at a lower velocity than the air in the expansion chamber 20 and thus at a higher pressure. As such, the air 71 within the induction chamber 30 will be encouraged to flow into the expansion chamber 20 . As shown in FIG. 6, the flow of air 70 from the induction chamber 30 to the expansion chamber 20 is further assisted or encouraged by the louvers 36 formed in the tube 22 .
- the arrangement of the louvers 36 force the air 70 into a vortexial flow 72 around the tube 22 .
- this flow 72 reenters the inner tube 22 in order to pass out through the exit or exhaust port 79 as represented by arrow 80 , the inner flow 71 of air is also encouraged into a vortexial flow.
- both the flow of air around the tube 22 and inside the tube 22 is flowing in a vortexial manner.
- FIG. 7 illustrates another embodiment of a tunable air turbine device, generally indicated at 100 , which includes the air turbine device 10 shown in FIG. 1.
- the air turbine device 10 has an opening 102 formed in the housing to which a tunning chamber 104 , preferably comprised of an elongate tube, is attached.
- the tuning chamber 104 forms a second flow passage from the air turbine device 10 but is linked to and in fluid communication with the expansion chamber 20 .
- the tuning chamber 104 reconnects and is in fluid communication with an exhaust port 106 attached to the exit port 40 of the air turbine device 10 .
- the amount of air 110 flowing through the tuning chamber 104 is controlled by a valve 112 , preferably an electronically controllable butterfly valve, which can partially or totally restrict the flow of air 110 through the tuning chamber 104 .
- the butter fly valve 112 may be powered by a 12 volt power supply 114 and include a variably controllable open position gauge 116 and/or an open/close controller 118 .
- the resonant sound emanating through the tuning chamber 104 will have had a lesser amount of high frequency noise cancelled by the air turbine device.
- FIG. 8 another preferred embodiment of an air turbine device, generally indicated at 200 , is adapted for use in marine applications.
- An air turbine device 202 having a configuration similar to that illustrated in FIG. 1 is attached to an exhaust manifold 204 .
- the exhaust flow diverter 204 includes an exhaust inlet 206 which is coupled to the exhaust manifold (not shown) of an inboard boat motor.
- An actuator 208 controls a valve 210 housed within the exhaust flow diverter 204 .
- the valve 210 is preferably a butterfly valve which can partially or totally obstruct the air flow into the air turbine device 202 , as controlled by a user. Similar to the butterfly valve illustrated with respect to FIG.
- the butterfly valve 210 may be powered by a 12 volt power supply 212 and include a variably controllable open position gauge 216 and/or an open/close controller 218 .
- the air that is restricted by the butterfly valve 210 is diverted into the diverter outlet 220 .
- the diverter outlet is coupled to the factory stern drive outlet (i.e., the exhaust outlet already existing on the marine vessel).
- the exhaust flow diverter 204 is thus controllable to allow a portion or all of the exhaust air flow entering the exhaust inlet of the diverter to flow through the air turbine device 202 .
- the outlet 222 of the diverter 204 is coupled to the inlet 224 of the air turbine device.
- the outlet 226 of the air turbine device 202 is coupled or mounted to the hull 228 of the boat or marine vessel.
- the outlet 226 is positioned above the water line 230 so that, unlike the factory exhaust which uses the water to act as an air turbine device, the flow of exhaust out of the air turbine device 202 is not impeded by the back pressure that would otherwise be caused if the outlet 226 of the air turbine device 202 was submerged.
- Such a free flowing air turbine device configuration increases horse power while providing a compact air turbine device that does not add significant weight or size to an existing vessel.
- FIG. 9 illustrates another embodiment of an air turbine device, generally indicated at 300 in accordance with the principles of the present invention. Similar to other embodiments described herein, the air turbine 300 is comprised of an inlet 302 , an expansion chamber outer housing 304 and an outlet 306 . The inlet 302 and outlet 306 are of similar diameter, with the housing 304 having a larger diameter and interposed between the inlet and the outlet. A chop core 308 is positioned within expansion chamber 316 and defines an induction chamber 310 .
- the chop core 308 is provided with a plurality of louvers 312 that extend into the induction chamber 310 and are arranged along the inner wall 314 of the chop core 308 so as to encourage rotational flow of the air or exhaust gases entering the induction chamber out into the annular expansion chamber 316 defined between chop core 308 and the expansion chamber outer housing 304 .
- the louvers may be spirally or helically configured around the chop core 308 .
- An airfoil 318 is positioned in the proximal end 320 of the housing 304 and is attached to the proximal end 322 of the chop core 308 .
- the airfoil 318 has a frustoconical shape with a curved outer surface 320 and a longitudinally extending central bore 322 extending from the proximal end 324 of the airfoil 318 to the distal end 326 and in fluid communication with the induction chamber 310 .
- the airfoil 318 may be comprised of a ceramic material, metal or other heat resistant materials.
- the airfoil 318 divides the air entering the device 300 through the input 302 so that a portion of the air enters the induction chamber 310 through the bore 322 while the remaining air flow enters the induction chamber 310 from the expansion chamber 316 .
- An aspect of the invention is to cause the air flow through the device to rotate into a vortex.
- the spinning air causes the air to flow more efficiently through the device 300 .
- the air flow is first caused to rotate relative to the device 310 at the intake 302 by a pair of vortex convolutions 328 and 330 that are formed into the intake portion 302 of the device 300 .
- the vortex convolutions 328 and 330 are each formed by bending, casting or otherwise forming the intake 302 to form annular recesses 331 , 332 and 333 in order to form the interior annular recesses or convolutions 328 and 330 .
- the air flow encounters the convolutions 328 and 330 passes through the convolutions, the air is caused to spin.
- the air continues to spin as it passes over and around the airfoil 318 .
- the perforations or louvers 312 are configured to cause rotation of the air flow counter to the rotation caused by the convolutions 330 , 328 as the air is drawn by the convolutions from the induction chamber to the expansion chamber 316 through the louvers 312 .
- This mixing of the air flow in the expansion chamber and induction chamber causes turbulence in the air flow. The result of such turbulence is a cancellation of noise otherwise present in the exhaust flow.
- This turbulent flow then recombines in the outlet 306 and is again caused to spin into a vortex as it passes through a second set of convolutions 336 and 338 formed in the outlet 306 in a similar manner to the convolutions 328 and 330 formed in the intake 302 .
- Such a vortex at the outlet 306 again encourages the flow of air out of the device 300 .
- the length of the expansion chamber 304 also has an effect on the noise cancellation ability of the device 300 . That is, the length of the device 300 can be tuned to cancel out various noise frequencies including multiple harmonics. That is, by tuning the length of the device 300 to match the frequencies generated by a particular engine, the first, second and third harmonics can be dampened producing a more quiet running engine.
- FIG. 10 another embodiment of an air turbine device, generally indicated at 400 , is shown.
- the device is comprised of an intake 402 , an expansion chamber housing 404 defining an expansion chamber 405 and an exhaust port 406 .
- an airfoil 408 Positioned within the expansion chamber 405 is an airfoil 408 that defines a longitudinally extending bore 412 and divides the air into a portion that flows around the air foil and a portion that flows through the air foil.
- a pair of airfoil convolutions 414 and 416 are provided in the bore 412 of the airfoil 408 to encourage vortex flow of the air through the airfoil and into the expansion chamber 405 .
- the airfoil 408 is concentrically centered within the expansion chamber 405 and held relative thereto with a plurality of vanes or blades 418 and 420 . There may be two, three, four or more of the blades 418 and 420 .
- the blades 418 and 420 as shown are configured to be spirally or helically oriented around the outer surface 422 of the airfoil 408 so as to cause rotation of the air flowing around the airfoil 408 .
- the orientation of the blades 418 and 420 is such that the air flowing around the airfoil 408 is counter rotated to the air flowing through the bore 412 .
- FIG. 11 shows a cross-sectional end view of an expansion chamber housing 500 with blades 501 , 502 , 503 and 504 supporting an airfoil cone 506 .
- the blades 501 to 504 are attached to the inner surface 508 of the housing 500 and to the outer surface 510 of the airfoil cone 506 so as to cause rotation of the air flow passing around the airfoil cone 506 in the direction of the blades 501 to 504 . It is desirable to orient the blades 501 to 504 so that the air flowing over the airfoil cone 510 is spinning in a direction opposite to the rotation of the air flowing through the internal passageway 512 extending through the airfoil cone 506 .
- An intake air turbine 600 is comprised of an intake port 602 , an expansion chamber housing 604 and an exhaust port 606 . Housed within the expansion chamber housing 604 is an airfoil 608 that divides the air flow similar to that shown in the other embodiments herein.
- the intake port 602 is provided with vortex convolutions 610 and 612 that cause the air flow to rotate relative thereto. As an intake device, the flow of air from the intake port 602 to the exhaust port 606 is encouraged to rotate throughout the device.
- the air flowing through the expansion chamber both around and through the bore 620 of the airfoil, is rotated in the same direction so as to increase the flow of air through the exhaust port 606 and into the intake manifold (not shown) of a combustion engine.
- the blades 616 and 618 that support the airfoil 608 within the housing 604 are helically oriented around the airfoil to encourage this consistent rotational flow of air around the airfoil so as to minimize turbulence as the air flow recombines in the expansion chamber 622 .
- the exhaust port vortex convolutions 624 and 626 encourage continued and uniform vortex rotation of the air flow.
- the air turbine 700 includes an inlet 702 , an expansion chamber housing 704 defining an expansion chamber 706 , and an outlet 708 .
- the expansion chamber 706 is in communication with the inlet 702 and the outlet 708 .
- the inlet 702 and outlet 708 have a substantially similar diameter with the expansion chamber 706 having a diameter greater than the inlet 702 and outlet 708 .
- An inlet tube 710 couples to the housing 704 and is aligned with the inlet 702 .
- an outlet tube 712 couples to the housing 704 and is aligned with the outlet 708 .
- a tube or chop core 714 is disposed within the expansion chamber 706 and defines an induction chamber 716 within.
- the tube 714 includes a plurality of perforations or louvers 718 that extend into the induction chamber 716 .
- the perforations 718 are arranged along an inner wall 720 of the tube 714 so as to encourage rotational flow of the air or exhaust gases entering the induction chamber 716 .
- the perforations 718 may be spirally or helically disposed around the tube 714 .
- the tube 714 includes a proximal end 722 having a tube input 724 .
- the tube 714 divides passing gases so that a portion of the gases enter the induction chamber 716 through the tube input 724 while the remaining air flow enters the induction chamber 716 through the perforations 718 .
- the separated air flow recombines in the induction chamber 716 and exits through the outlet 708 .
- the tube 714 provides two air paths that are separated from an original incoming air flow and then recombined.
- the tube 714 may maintain a consistent diameter along its entire length.
- the tube 714 further includes a distal end 726 that is coupled to the outlet 708 .
- the air turbine 700 may further include one or more inlet vortex convolutions 728 , 730 disposed within the inlet tube 710 .
- the vortex convolutions cause the air flow to rotate into a vortex.
- the spinning air causes the air to flow more efficiently through the device 700 .
- the vortex convolutions 728 , 730 are formed by bending, casting or otherwise forming the inlet 710 to form annular recesses 732 , 734 in order to form the interior annular recesses or convolutions 728 , 730 .
- the air is caused to spin.
- the air continues to spin as it passes through and around the tube 714 .
- the outlet tube 712 may include outlet vortex convolutions 732 , 734 that create a vortex in the passing air flow.
- the outlet vortex convolutions 732 , 734 are disposed within the outlet tube 712 in a manner similar to the convolutions 724 , 726 formed in the inlet tube 710 .
- a vortex in the outlet tube 712 encourages the flow of air out of the air turbine 700 .
- FIG. 14 an alternative embodiment of an air turbine 800 is shown similar to that illustrated in FIG. 13.
- the tube 714 includes a converging portion 802 that is coupled to a main body 804 of the tube 714 .
- the converging portion 802 provides decreasingly smaller diameters for the tube input 724 .
- the converging portion 802 extends for a relatively small length compared to the entire tube length.
- the main body of the tube 714 has a diameter that remains substantially the same.
- the converging portion 802 encourages air flow through the tube input 718 .
- FIGS. 13 and 14 do not provide the same level of performance as previous embodiments incorporating airfoils.
- the air turbines 700 , 800 provide improved performance over conventional devices and require relatively few components. It will be obvious to those having skill in the art that many changes may be made to the details of the above-described embodiments without departing from the underlying principles of the invention. The scope of the present invention should, therefore, be determined only by the following claims.
Abstract
An air turbine apparatus is suitable for use as the intake or exhaust of a combustion engine. A housing defines an expansion chamber that communicates with an inlet and outlet. A tube is disposed proximate to the inlet and includes a plurality of perforations to encourage air flow from the expansion chamber to an induction chamber within the tube.
Description
- This application claims priority to U.S. patent application Ser. No. 10/077,324 filed Feb. 15, 2002 and entitled “Air Turbine for Combustion Engine,” and which is hereby incorporated by reference.
- The present invention relates to air turbine devices suitable for use in the intake or exhaust of a combustion engine.
- FIG. 1 is a cross-sectional side view of a first embodiment of an air turbine device in accordance with the present invention;
- FIG. 2 is a cross-sectional end view of an induction chamber of FIG. 1;
- FIG. 3 is an end view of an airfoil of FIG. 1;
- FIG. 4 is an end view of a vortex ring of FIG. 1;
- FIG. 5 is a cross-sectional side view of the air turbine device of FIG. 1 illustrating the flow of air or gases through the device;
- FIG. 6 is another cross-sectional side view of the air turbine device of FIG. 1 illustrating the flow of air or gases from the induction chamber into the expansion chamber;
- FIG. 7 is a cross-sectional side view of a second embodiment of an air turbine device in accordance with the present invention attached to an exhaust system of a combustion engine;
- FIG. 8 is a cross-sectional side view of a third embodiment of an air turbine device in accordance with the present invention attached to an exhaust system of a combustion engine;
- FIG. 9 is a cross-sectional side view of a fourth embodiment of an air turbine device in accordance with the present invention;
- FIG. 10 is a cross-sectional side view of another embodiment of an air turbine device in accordance with the present invention;
- FIG. 11 is a cross-sectional end view of an expansion chamber housing an airfoil supported by a plurality of blades in accordance with the present invention;
- FIG. 12 is a cross-sectional side view of an alternative embodiment of an air turbine device in accordance with the present invention;
- FIG. 13 is a cross-sectional side view of an alternative embodiment of an air turbine device in accordance with the present invention; and
- FIG. 14 is a cross-sectional side view of an alternative embodiment of an air turbine device in accordance with the present invention.
- Referring to the drawings wherein like numerals indicate like elements throughout, there is shown in FIG. 1 an air turbine device, generally indicated at10, in accordance with an embodiment of the present invention. The
air turbine device 10 is comprised of anouter housing 12 having a generally cylindrical shape. Thehousing 12 defines aninlet port 14 and anoutlet port 16. It should be noted that while thehousing 12 has a cylindrical shape, those of skill in the art will appreciate that other geometrical shapes may be feasible. Aninlet tube 18 is secured to theinlet port 14 for attachment of theair turbine device 10 to an exhaust system of a vehicle (not shown). Theinlet tube 18 is provided with a pair ofvortex rings air turbine device 10. Thehousing 12 defines anexpansion chamber 20 which extends from theinlet 14 to theoutlet 16. - Housed within the
housing 12 is aninduction tube 22 which is fixedly mounted to theoutlet 16 of thehousing 12. Theinduction tube 22 is comprised of an elongate tubular member having a plurality ofperforations 24 formed therein. In the preferred embodiment, theperforations 24 are louvers which extend into theinduction chamber 30 formed by thetube 22. The louvers are formed by stamping or cutting theexterior wall 32 of thetube 22 to forceportions 34 of thewall 32 into the interior of thetube 22. As shown in FIG. 2, thelouvers 36 are preferably formed in a helical pattern around thetube 22. It is also contemplated that one or more spiral or helical slits may be provided in thetube 22 to accomplish a similar effect. Thus, the terms louvers or perforations are intended to include such structure. - Referring again to FIG. 1, the
louvers 36 extend around theinterior surface 38 of thetube 22 and face in a direction so as to encourage air flowing toward theoutlet 40 of the tube to flow from thetube 22 into theexpansion chamber 20. A pair ofvortex rings tube 22 proximate theoutlet 40 of thetube 22. Thevortex rings outlet 40. - Attached to the
inlet 46 of thetube 22 is a disc-shaped member 50 which extends across the expansion chamber proximate theinlet 14 of thehousing 12. The disc-shaped member 50 forms an airfoil in the path of the air flowing through thehousing 12. Thisairfoil 22 defines acentral aperture 52 which is in fluid communication with theinner vortex chamber 30. In addition, theairfoil 22 has a diameter that is less than the diameter defined by theinner surface 54 of thehousing 12. As such, air entering theinlet tube 18 can either flow through theaperture 52 or through theannular space 56 formed between theairfoil 50 and theinner surface 54 of thehousing 12. - FIG. 3 illustrates a front view of the
airfoil 50 shown in FIG. 1. Theairfoil 50 is provided with thecircular aperture 52 which is concentric with theairfoil 50. The size of theairfoil 50 as well as the diameter of theaperture 52 is dependent upon the flow of air from the exhaust of the combustion engine. The size of the vortex expansion chamber, however, is dependent upon the diameter of the inlet coupled thereto. The diameter of the expansion chamber is defined by 1.5 times the inlet pipe diameter. The length of the expansion chamber to accommodate the second harmonic resonance is 2.0 times the diameter of the expansion chamber. The length of the expansion chamber to accommodate the third harmonic resonance is 3.5 times the diameter of the expansion chamber. For a six inch expansion chamber diameter, the outermost airfoil diameter is approximately 5.4 inches and the diameter of the aperture or bore of the airfoil is approximately 1.6 inches. In order to create the desired vortex effect and mixing the air flows passing around and through the airfoil, the area of the annular space between the airfoil and the expansion chamber and the area of the aperture are sized to produce the most efficient flow of air through the device. In proportion, the ratio of air passing around the airfoil compared to the air passing through the airfoil for a six inch diameter expansion chamber is approximately 2.7 to 1. - FIG. 4 illustrates a vortex ring, such as
vortex ring 19 shown in FIG. 1. Similar to the dimensions of theairfoil 50, the size of thevortex ring 19 is dependent upon the inner diameter of theinlet tube 18 to which thevortex ring 19 is attached. Thevortex ring 19 extends into the inlet tube to form a slight constriction but not enough to cause any appreciable restriction of flow therethrough. Obviously, as shown in FIG. 1, the outer diameter of thevortex ring 19 is defined by and thus equal to the inner diameter of theinlet tube 18. - Referring now to FIG. 5, the flow of
exhaust 60 through theair turbine device 10 is illustrated. As the flow ofexhaust 60 enters theexpansion chamber 20, the air is directed either through 62 or around 64 and 66 theairfoil 50. The air passing around theairfoil 50 will necessarily be at a higher velocity than theair 62 that flows directly through theaperture 52. The faster movingair expansion chamber 20. - The
air 62 entering the inner vortex orinduction chamber 30 will be at a lower velocity than the air in theexpansion chamber 20 and thus at a higher pressure. As such, the air 71 within theinduction chamber 30 will be encouraged to flow into theexpansion chamber 20. As shown in FIG. 6, the flow ofair 70 from theinduction chamber 30 to theexpansion chamber 20 is further assisted or encouraged by thelouvers 36 formed in thetube 22. - Referring again to FIG. 5, the arrangement of the
louvers 36 force theair 70 into avortexial flow 72 around thetube 22. As thisflow 72 reenters theinner tube 22 in order to pass out through the exit orexhaust port 79 as represented byarrow 80, the inner flow 71 of air is also encouraged into a vortexial flow. As such, both the flow of air around thetube 22 and inside thetube 22 is flowing in a vortexial manner. - FIG. 7 illustrates another embodiment of a tunable air turbine device, generally indicated at100, which includes the
air turbine device 10 shown in FIG. 1. Theair turbine device 10 has anopening 102 formed in the housing to which atunning chamber 104, preferably comprised of an elongate tube, is attached. Thetuning chamber 104 forms a second flow passage from theair turbine device 10 but is linked to and in fluid communication with theexpansion chamber 20. Thetuning chamber 104 reconnects and is in fluid communication with anexhaust port 106 attached to theexit port 40 of theair turbine device 10. - The amount of
air 110 flowing through thetuning chamber 104 is controlled by avalve 112, preferably an electronically controllable butterfly valve, which can partially or totally restrict the flow ofair 110 through thetuning chamber 104. Thebutter fly valve 112 may be powered by a 12volt power supply 114 and include a variably controllableopen position gauge 116 and/or an open/close controller 118. The resonant sound emanating through thetuning chamber 104 will have had a lesser amount of high frequency noise cancelled by the air turbine device. By controlling the amount offlow 110 through thetuning chamber 104, a user can effectively control the tone of the sound from the airturbine device system 100. - As shown in FIG. 8, another preferred embodiment of an air turbine device, generally indicated at200, is adapted for use in marine applications. An
air turbine device 202 having a configuration similar to that illustrated in FIG. 1 is attached to anexhaust manifold 204. Theexhaust flow diverter 204 includes anexhaust inlet 206 which is coupled to the exhaust manifold (not shown) of an inboard boat motor. Anactuator 208 controls avalve 210 housed within theexhaust flow diverter 204. Thevalve 210 is preferably a butterfly valve which can partially or totally obstruct the air flow into theair turbine device 202, as controlled by a user. Similar to the butterfly valve illustrated with respect to FIG. 7, thebutterfly valve 210 may be powered by a 12volt power supply 212 and include a variably controllableopen position gauge 216 and/or an open/close controller 218. The air that is restricted by thebutterfly valve 210 is diverted into thediverter outlet 220. The diverter outlet is coupled to the factory stern drive outlet (i.e., the exhaust outlet already existing on the marine vessel). - The
exhaust flow diverter 204 is thus controllable to allow a portion or all of the exhaust air flow entering the exhaust inlet of the diverter to flow through theair turbine device 202. As such, theoutlet 222 of thediverter 204 is coupled to theinlet 224 of the air turbine device. Theoutlet 226 of theair turbine device 202 is coupled or mounted to thehull 228 of the boat or marine vessel. Theoutlet 226 is positioned above thewater line 230 so that, unlike the factory exhaust which uses the water to act as an air turbine device, the flow of exhaust out of theair turbine device 202 is not impeded by the back pressure that would otherwise be caused if theoutlet 226 of theair turbine device 202 was submerged. Such a free flowing air turbine device configuration increases horse power while providing a compact air turbine device that does not add significant weight or size to an existing vessel. - FIG. 9 illustrates another embodiment of an air turbine device, generally indicated at300 in accordance with the principles of the present invention. Similar to other embodiments described herein, the
air turbine 300 is comprised of aninlet 302, an expansion chamberouter housing 304 and anoutlet 306. Theinlet 302 andoutlet 306 are of similar diameter, with thehousing 304 having a larger diameter and interposed between the inlet and the outlet. Achop core 308 is positioned withinexpansion chamber 316 and defines aninduction chamber 310. Thechop core 308 is provided with a plurality oflouvers 312 that extend into theinduction chamber 310 and are arranged along theinner wall 314 of thechop core 308 so as to encourage rotational flow of the air or exhaust gases entering the induction chamber out into theannular expansion chamber 316 defined betweenchop core 308 and the expansion chamberouter housing 304. Thus, the louvers may be spirally or helically configured around thechop core 308. - An
airfoil 318 is positioned in theproximal end 320 of thehousing 304 and is attached to theproximal end 322 of thechop core 308. Theairfoil 318 has a frustoconical shape with a curvedouter surface 320 and a longitudinally extendingcentral bore 322 extending from theproximal end 324 of theairfoil 318 to thedistal end 326 and in fluid communication with theinduction chamber 310. Theairfoil 318 may be comprised of a ceramic material, metal or other heat resistant materials. Theairfoil 318 divides the air entering thedevice 300 through theinput 302 so that a portion of the air enters theinduction chamber 310 through thebore 322 while the remaining air flow enters theinduction chamber 310 from theexpansion chamber 316. - An aspect of the invention is to cause the air flow through the device to rotate into a vortex. The spinning air causes the air to flow more efficiently through the
device 300. The air flow is first caused to rotate relative to thedevice 310 at theintake 302 by a pair ofvortex convolutions intake portion 302 of thedevice 300. The vortex convolutions 328 and 330 are each formed by bending, casting or otherwise forming theintake 302 to formannular recesses convolutions convolutions airfoil 318. The perforations orlouvers 312 are configured to cause rotation of the air flow counter to the rotation caused by theconvolutions expansion chamber 316 through thelouvers 312. This mixing of the air flow in the expansion chamber and induction chamber causes turbulence in the air flow. The result of such turbulence is a cancellation of noise otherwise present in the exhaust flow. - This turbulent flow then recombines in the
outlet 306 and is again caused to spin into a vortex as it passes through a second set ofconvolutions outlet 306 in a similar manner to theconvolutions intake 302. Such a vortex at theoutlet 306 again encourages the flow of air out of thedevice 300. - The length of the
expansion chamber 304 also has an effect on the noise cancellation ability of thedevice 300. That is, the length of thedevice 300 can be tuned to cancel out various noise frequencies including multiple harmonics. That is, by tuning the length of thedevice 300 to match the frequencies generated by a particular engine, the first, second and third harmonics can be dampened producing a more quiet running engine. - Referring now to FIG. 10 another embodiment of an air turbine device, generally indicated at400, is shown. The device is comprised of an
intake 402, anexpansion chamber housing 404 defining anexpansion chamber 405 and anexhaust port 406. - Positioned within the
expansion chamber 405 is anairfoil 408 that defines alongitudinally extending bore 412 and divides the air into a portion that flows around the air foil and a portion that flows through the air foil. A pair ofairfoil convolutions bore 412 of theairfoil 408 to encourage vortex flow of the air through the airfoil and into theexpansion chamber 405. - The
airfoil 408 is concentrically centered within theexpansion chamber 405 and held relative thereto with a plurality of vanes orblades blades blades outer surface 422 of theairfoil 408 so as to cause rotation of the air flowing around theairfoil 408. The orientation of theblades airfoil 408 is counter rotated to the air flowing through thebore 412. As the air recombines in theexpansion chamber 405, counter spinning air flows cause turbulence therein between so as to cause cancellation of noise from the engine to produce a muffling effect while allowing essentially the free flow of exhaust gases through thedevice 400. The air then recombines in theexpansion chamber 405 and exits through theexhaust port 406 with theconvolutions device 400. - FIG. 11 shows a cross-sectional end view of an
expansion chamber housing 500 withblades airfoil cone 506. Theblades 501 to 504 are attached to theinner surface 508 of thehousing 500 and to theouter surface 510 of theairfoil cone 506 so as to cause rotation of the air flow passing around theairfoil cone 506 in the direction of theblades 501 to 504. It is desirable to orient theblades 501 to 504 so that the air flowing over theairfoil cone 510 is spinning in a direction opposite to the rotation of the air flowing through theinternal passageway 512 extending through theairfoil cone 506. - Finally, as shown in FIG. 12, the principles of the present invention may be applied to the intake of a combustion engine as well. An
intake air turbine 600 is comprised of anintake port 602, anexpansion chamber housing 604 and anexhaust port 606. Housed within theexpansion chamber housing 604 is anairfoil 608 that divides the air flow similar to that shown in the other embodiments herein. Theintake port 602 is provided withvortex convolutions intake port 602 to theexhaust port 606 is encouraged to rotate throughout the device. That is the air flowing through the expansion chamber, both around and through thebore 620 of the airfoil, is rotated in the same direction so as to increase the flow of air through theexhaust port 606 and into the intake manifold (not shown) of a combustion engine. Theblades airfoil 608 within thehousing 604 are helically oriented around the airfoil to encourage this consistent rotational flow of air around the airfoil so as to minimize turbulence as the air flow recombines in theexpansion chamber 622. In the event of any such turbulence, the exhaustport vortex convolutions - Referring to FIG. 13, an alternative embodiment of an
air turbine 700 is shown. As with previously described embodiments, theair turbine 700 includes aninlet 702, anexpansion chamber housing 704 defining anexpansion chamber 706, and anoutlet 708. Theexpansion chamber 706 is in communication with theinlet 702 and theoutlet 708. Theinlet 702 andoutlet 708 have a substantially similar diameter with theexpansion chamber 706 having a diameter greater than theinlet 702 andoutlet 708. Aninlet tube 710 couples to thehousing 704 and is aligned with theinlet 702. Likewise, anoutlet tube 712 couples to thehousing 704 and is aligned with theoutlet 708. - A tube or
chop core 714 is disposed within theexpansion chamber 706 and defines aninduction chamber 716 within. Thetube 714 includes a plurality of perforations orlouvers 718 that extend into theinduction chamber 716. Theperforations 718 are arranged along aninner wall 720 of thetube 714 so as to encourage rotational flow of the air or exhaust gases entering theinduction chamber 716. Theperforations 718 may be spirally or helically disposed around thetube 714. - The
tube 714 includes aproximal end 722 having atube input 724. Thetube 714 divides passing gases so that a portion of the gases enter theinduction chamber 716 through thetube input 724 while the remaining air flow enters theinduction chamber 716 through theperforations 718. The separated air flow recombines in theinduction chamber 716 and exits through theoutlet 708. Thus, thetube 714 provides two air paths that are separated from an original incoming air flow and then recombined. Thetube 714 may maintain a consistent diameter along its entire length. Thetube 714 further includes adistal end 726 that is coupled to theoutlet 708. - As in previous embodiments, the
air turbine 700 may further include one or moreinlet vortex convolutions inlet tube 710. The vortex convolutions cause the air flow to rotate into a vortex. The spinning air causes the air to flow more efficiently through thedevice 700. The vortex convolutions 728, 730 are formed by bending, casting or otherwise forming theinlet 710 to formannular recesses convolutions convolutions tube 714. - The
outlet tube 712 may includeoutlet vortex convolutions outlet vortex convolutions outlet tube 712 in a manner similar to theconvolutions inlet tube 710. A vortex in theoutlet tube 712 encourages the flow of air out of theair turbine 700. - Referring to FIG. 14 an alternative embodiment of an
air turbine 800 is shown similar to that illustrated in FIG. 13. Thetube 714 includes a convergingportion 802 that is coupled to amain body 804 of thetube 714. The convergingportion 802 provides decreasingly smaller diameters for thetube input 724. The convergingportion 802 extends for a relatively small length compared to the entire tube length. The main body of thetube 714 has a diameter that remains substantially the same. The convergingportion 802 encourages air flow through thetube input 718. - The embodiments illustrated in FIGS. 13 and 14 do not provide the same level of performance as previous embodiments incorporating airfoils. However, the
air turbines
Claims (15)
1. An air turbine apparatus, comprising:
a housing defining an expansion chamber;
an inlet coupled to the housing, the inlet having a diameter less than the expansion chamber;
an outlet coupled to the housing;
a tube proximate to the inlet to directly receive incoming gases, the tube including
an induction chamber extending longitudinally therethrough and aligned with the inlet and outlet,
a proximal end disposed adjacent to the inlet to directly receive incoming gases,
a plurality of perforations formed therein, and
a distal end coupled to the outlet,
wherein the tube defines first and second air flow paths, the first air flow path being straight and passing through the inlet, through the induction chamber, and through the outlet, the second air flow path passing through the perforations and then combining with the first air flow path.
2. The apparatus of claim 1 , further comprising an inlet tube coupled to the housing and aligned with the inlet.
3. The apparatus of claim 2 , wherein the inlet tube includes a convolution.
4. The apparatus of claim 1 , further comprising an outlet tube coupled to the housing and aligned with the outlet.
5. The apparatus of claim 4 , further wherein the outlet tube includes a convolution.
6. The apparatus of claim 1 , wherein the perforations extend inwardly into the tube.
7. The apparatus of claim 1 , wherein the tube maintains approximately the same diameter along its longitudinal length.
8. The apparatus of claim 1 , wherein the diameter of the tube is approximately the same as the inlet and outlet.
9. An air turbine apparatus, comprising:
a housing defining an expansion chamber;
an inlet coupled to the housing, the inlet having a diameter less than the expansion chamber;
an outlet coupled to the housing;
a tube proximate to the inlet to directly receive incoming gases, the tube including
an induction chamber extending longitudinally therethrough and aligned with the inlet and outlet,
a proximal end disposed adjacent to the inlet to directly receive incoming gases,
a converging portion,
a body, coupled to the converging portion, the body maintaining approximately the same diameter along its length,
a plurality of perforations formed within the body of the tube, and
a distal end coupled to the outlet,
wherein the tube defines first and second air flow paths, the first air flow path being straight and passing through the inlet, through the induction chamber, and through the outlet, the second air flow path passing through the perforations and then combining with the first air flow path.
10. The apparatus of claim 9 , further comprising an inlet tube coupled to the housing and aligned with the inlet.
11. The apparatus of claim 10 , wherein the inlet tube includes a convolution.
12. The apparatus of claim 9 , further comprising an outlet tube coupled to the housing and aligned with the outlet.
13. The apparatus of claim 12 , further wherein the outlet tube includes a convolution.
14. The apparatus of claim 9 , wherein the perforations extend inwardly into the tube.
15. The apparatus of claim 9 , wherein the diameter of the body of the tube is approximately the same as the inlet and outlet.
Priority Applications (1)
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US10/756,440 US20040163886A1 (en) | 2002-02-15 | 2004-01-13 | Air turbine for combustion engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US10/077,324 US6679351B2 (en) | 2001-02-15 | 2002-02-15 | Air turbine for combustion engine |
US10/756,440 US20040163886A1 (en) | 2002-02-15 | 2004-01-13 | Air turbine for combustion engine |
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US10/077,324 Continuation-In-Part US6679351B2 (en) | 2001-02-15 | 2002-02-15 | Air turbine for combustion engine |
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US20040163886A1 true US20040163886A1 (en) | 2004-08-26 |
Family
ID=32867452
Family Applications (1)
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US10/756,440 Abandoned US20040163886A1 (en) | 2002-02-15 | 2004-01-13 | Air turbine for combustion engine |
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
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CN102628392A (en) * | 2012-04-11 | 2012-08-08 | 宁波市鄞州吉士汽配有限公司 | Muffler |
US8640821B2 (en) * | 2012-01-18 | 2014-02-04 | Honda Motor Co., Ltd. | Exhaust system of engine |
CN106401722A (en) * | 2015-03-25 | 2017-02-15 | 丰田自动车株式会社 | Muffler |
US20180038249A1 (en) * | 2016-08-05 | 2018-02-08 | Gibson Performance Corp. | Muffler with venturi exhaust line |
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
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US8640821B2 (en) * | 2012-01-18 | 2014-02-04 | Honda Motor Co., Ltd. | Exhaust system of engine |
CN102628392A (en) * | 2012-04-11 | 2012-08-08 | 宁波市鄞州吉士汽配有限公司 | Muffler |
CN106401722A (en) * | 2015-03-25 | 2017-02-15 | 丰田自动车株式会社 | Muffler |
US20180038249A1 (en) * | 2016-08-05 | 2018-02-08 | Gibson Performance Corp. | Muffler with venturi exhaust line |
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