US2845775A - Noise suppressors for jet engines - Google Patents

Noise suppressors for jet engines Download PDF

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Publication number
US2845775A
US2845775A US588742A US58874256A US2845775A US 2845775 A US2845775 A US 2845775A US 588742 A US588742 A US 588742A US 58874256 A US58874256 A US 58874256A US 2845775 A US2845775 A US 2845775A
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Prior art keywords
vanes
inner body
tailpipe
noise
gas passage
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US588742A
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John M Tyler
Robert E Meyer
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RTX Corp
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United Aircraft Corp
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Priority to US588742A priority Critical patent/US2845775A/en
Priority to GB16708/57A priority patent/GB818201A/en
Priority to FR1182293D priority patent/FR1182293A/fr
Priority to DEU4569A priority patent/DE1114061B/de
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Publication of US2845775A publication Critical patent/US2845775A/en
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    • 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
    • F02K1/42—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet the means being movable into an inoperative position

Definitions

  • This invention relates to the suppression of low frequency, audible noise and more particularly to the suppression of low frequency, audible noise from the exhaust of any type of a jet and in particular an aircraft jet engine wake.
  • Fig. 1 shows a cross sectional view of a typical turbo-jet engine with an embodiment of our invention attached thereto and shown in its retracted position in solid lines while shown in its operative position in phantom.
  • Fig. 2 is a fragmentary cross sectional view of an embodiment of our invention with the noise suppressor vanes retracted.
  • Fig. 2A is a fragmentary cross sectional view 'of an embodiment of our invention with the noise suppressor vanes in their operable position
  • Fig. 3 is a partial rear view of the embodiment shown in Fig. 2.
  • Fig. 3A is a partial rear view of the embodiment shown in Fig. 2A.
  • Fig. 4 is a view taken along line 4-4 of Fig. 2A.
  • Fig. 5 is a fragmentary cross sectional view of another embodiment of our invention which shows the noise suppressor vanes in their retracted position.
  • Fig. 5A is a fragmentary cross sectional view of another embodiment of our invention which shows the noise suppressor vanes in their operable position.
  • Fig. 6 is a partial rear view of the embodiment shown in Fig. 5.
  • Fig. 6A is a partial rear view of the embodiment shown in Fig. 5A.
  • Fig. 7 is a perspective view of adjacent noise suppressor vanes of the type used in Figs. 5, 5A and 6.
  • Fig. 8 is a fragmentary cross sectional view of the embodiment of our invention shown in Fig. 11 showing the externally clustered vanes in their operable position.
  • Fig. 8A is a fragmentary cross sectional view of the embodiment of our invention shown in Fig. 11 showing the externally clustered vanes in their retracted position.
  • Fig. 9 is a fragmentary cross sectional view of the embodiment of our invention shown in Fig. 11 showing the internally clustered vanes in their operable position.
  • Fig. 9A is a fragmentary cross sectional view of the embodiment of our invention shown in Fig. 11 showing the internally clustered vanes in their retracted position.
  • Fig. 10 is a view thru line 10-10 of Fig. 8A, enlarged.
  • Fig. 11 is a rear view of another embodiment of our invention which consists of both a plurality of internally clustered vanes and a plurality of externally clustered vanes.
  • Fig. 12 is a perspective view of the externally mounted vane shown in Figs. 8, 8A and 11.
  • FIG. 1 we see aircraft jet engine 10 which consists of air inlet 12, compressor section 14, combustion chamber section 16, turbine section 18, and exhaust outlet section or tailpipe 20.
  • Fig. 1 shows a plurality of hollow, fin-type vanes 22 which have a single hole 24 in the forward edge of each vane and a plurality of small holes or nozzles 26 in the trailing edge of each vane.
  • Vanes 22 are shown clustered in their inoperative position (solid lines) to form the engine tailcone in combination with movable inner body 28. Vanes 22 are also shown in their operable or silencing position in phantom. With vanes 22 in their operating position, inner body 28 has moved forward as shown in Fig. 2A in this embodiment.
  • vanes 22 are in their retracted position, so as to be clustered downstream of inner body 28 to form a conical continuation thereof the exhaust gas passes through exhaust outlet 33, which exhaust outlet'SSis formed by tailpipe 20-and inner body 28, which is concentric with tailpipe 20 and contained therein.
  • exhaust gases are permitted to pass through exhaust outlet 38 when noise suppressionis notdesired.
  • the discharge of the exhaust gases through the large nozzle or exhaust outlet 38 creates a low frequency noise.
  • vanes 22 are pivoted radially outward into their extended position so as to extend through or across the gas passage formed by tailpipe 20 and inner body 28 and extend radially outward of tailpipe 20.
  • Relatively large hole or aperture 24 in the forward edge of vane 22 intercepts or is presented to the .gas passage and causes the exhaust gases to pass through hollow vane or fin 22 and be discharged through the .plurality of relatively small holes, nozzles or apertures 26 in the trailing edge of vane 22. As mentioned supra and more fully described in referenced application, this causes the noise created by the jet wake to fall into a predominately high frequency noise spectrum.
  • Figs. 2, 2A, 3 and 3A show one embodiment of our invention of a jet engine exhaust noise suppressor.mechanism in greater detail.
  • Figs. 2 and 3 demonstrate'the suppression mechanism in its retracted or non-silencing position while Figs. 2A and 3A show the noise suppression mechanism in its operable position.
  • axially movableinner body 28 has moved rearwardly on rollers 40 which pivot in inner body at 41 andbear against support member 43 so as to form a smooth tail- .cone with the plurality of retracted vanes 22 which are clustered to form a cone just downstream of inner body 28.
  • hole 24 in the forward edge of vane 22 is not blocking off when vane 22 is retracted 'as it is not deemed necessary since there is no significant pressure drop across the inlet hole 24 and the outletholes 26 of vane 22.
  • tailcone 20 has inwardly directed scallops, trough or dimples-42 which butt against or come into close proximity to inner body 28 in several places about the inner periphery of tailpipe 20 as best shown in Fig. 3.
  • the function performed by theplurality of progressively inwardly directed troughs 42 is to block off the exhaust gas passage between adjacent hollow vanes 22 when they are in their extended position, as shown in Figs. 2A and 3A.
  • troughs 42 be smoothly faired forwardly or upstream so that it gradually and smoothly blends into tailpipe 20 at their forward end. While inwardly directed troughs 42 may be integral with tailpipes 20 as by being formed from the same piece of sheet metal as tailpipe 20, it is also possible that they may be separate pieces afiixed to tailpipe 20.
  • Fixed member 50 includes hydraulic cylindrical wall 38 which are formed between inner body 28 and tail'conc 20 and are bounded by adjacent inwardly directed troughs 42. In this configuration, due to the existence of inwardly directed troughs 42 a symmetrical but interrupted and non continuous exhaust outlet is presented. This is contrary to the usual concept of an exhaust outlet which presents a continuous exhaust area which is formed between two concentric members of circular cross section.
  • hollow noise suppressor vane 22 in its extended or operable position. With vanes 22 in this position the exhaust gas flow passesbetween tailpipe 20 and inner body 28, which is now in a position forward or upstream of what it was when the vanes were retracted, and then enters hole 24 in the forward edge of vane 22 and may be turned substantially radially outward by turning vanes 44 and after passing through hollow vane 22 to be discharged rearwardly into atmosphere through the plurality of rearwardly directed nozzle 26 on the trailing edge of vane 22. As best shown in the lower half of Fig.3 since the inwardly directed troughs 42 block off the area'between vanes 22, all of the exhaust gas must pass through vanes 22 and then through small areaholes or nozzles26.
  • the result of discharging the exhaust gases through a plurality of small nozzles as opposed to one nozzle is accomplished, thereby causing the noise created by the discharged exhaustgas to be predominately in a high frequency, inaudible spectrum instead of a predominately low frequency spectrum. It is important that the thrust generated by engine '10 in normal flight be unaffected by the silencing operation.
  • vanes 22 and nozzles 26 are so selected that the tested fiow characteristics of the gas flow through exhaust outlet 38 is the same as through nozzles or holes 26.
  • FIGs. 2 and 2A relativeto the mechanism which is used to actuate the plurality of hollow vanes 22 to either rotate radially inward or .cluster into conical form and form the engine tailcone in combination with inner body 28 and also to rotate radially outcontact support cylinder 43, .as shown in Fig. 4.
  • Fixed member 48 which may be cylindrical in shape, is'provided, together with fixed member 50, which is also cylindrical in shape and concentrically located infixed member '48, to form passages for pressurized actuating Seal 51 is provided to seal fluid in member St).
  • Movable pivot 'point"64- joins vane -22-to inner-body 28 such that the forward or upstream movement of inner body 28 causes vane 22 to pivot or rotate radially outward to assume the position shown in Figs. 2A and 3A.
  • the gas passage formed between inner body 28 and tailpipe 22 is of greater radial dimension R0, than the radial dimension Rr of the gas passage when the plurality of noise suppressor vanes are retracted radially inward to cluster and form the engine tailcone with inner body 28.
  • compressor air source is no longer directed into hydraulic compartment 54.
  • this embodiment has accomlished noise suppression without the need for valving or sealing flaps.
  • Figs. 5, 5A, 6, 6A and 7 show another embodiment of our invention in which the hollow vane noise suppressors are shown in their retracted positions in Figs. 5 and 6 and in their extended or silencing positions in Figs. 5A and 6A.
  • the exhaust gas flow is between tailpipe 2G and inner body 23, which is fixed and terminates short of said tailpipe 2t).
  • the plurality of hollow noise suppression vanes 22 cluster in conical formation downstream of inner body 28' so as to form the engine tailcone and to act in unison with tailpipe 2% to provide a continuous exhaust gas outlet 33 between vanes 22 and outlet 79 of tailpipe It will be noted that due to the particular shape of hollow noise suppressor vanes 22', a relatively small and probably supersonic exhaust outlet or nozzle 38' is provided for use during flight or non-noise suppression operation. Hollow vanes 22 have the plurality of small holes or nozzles 26 in their trailing edge and the single large opening 24 in its forward or leading edge. A plurality of pivotable flaps Elti are shown in Fig.
  • vanes 22' are shown in Figs. 5 and 6 to be in a clustered position downstream of inner body 28' where they form first an expanding and then a contracting conical continuation of inner body 23'.
  • James are roughly triangular in longitudinal cross section of which trailing edge 81 forms the base of the triangle, and the forward edge of the vane contains the other two triangle legs 83 and 85 plus apex 37.
  • FIGS. 5A and 6A show hollow vanes 22' in their operable position such that the exhaust gas flow passes between tailpipe 20' and inner body 28', through opening or hole 24 in the forward edge of hollow vane 22', then through hollow vane 22 to be discharged rearwardly through the plurality of small holes or nozzles 26' which direct the jet exhaust downstream so as to etfect thrust propulsion.
  • vanes 22 are shaped to nearly abut one another in their extended positions thereby diminishing the problem of the spacing between them referred to previously.
  • a sealing flap 82 is made integral with vane 22 to perform a sealing function between adjacent vanes 22' when in their extended positions thereby preventing the discharge of exhaust gas through the area between adjacent vanes. Because sealing flap 3?. is of small size, the drag problem introduced by its use is negligible, therefore, it is virtually radially extending.
  • the actuating mechanism 93 to move the plurality of vanes 22 in unison is shown in Figs. 5 and 5A.
  • the actuating system consists of fixed hollow rod or cylinder which pivotally carries link or arm 86 which, in turn, pivotally attaches to the trailing edge of each hollow vane 22' at 92.
  • Fixed member 84 also carried fixed piston S8, which extends substantially radially therefrom to engage the inner surface of axially movable hydraulic or pneumatic cylinder 90 to form pressurizable compartments 8 and 1M therewith.
  • Vane 22 is pivotally attached to link 86 by pivot 92 and is further pivotally attached to cylindrical sealing unit 94, which projects from or is part of movable cylinder 90, at pivot 96.
  • a high pressure fluid source such as the air from compressor section 14
  • cylinder tit? moves rearwardly or to the right and since it is integrally attached to scaling cylinder 94, it moves cylinder 9 5 with it.
  • the rearward or right movement of cylinder 99 causes vanes 22 to move from their retracted position as shown in Figs. 5 and 6 to their operable or extended positions as shown in Figs. 5A and 6A. This is accomplished by the pivot, in unison, of vanes 22 about pivots 96 on sealing cylinder 94 and about pivots 92 on connecting links 86, which is in turn pivoting about fixed unit 84 at pivot point 100.
  • vanes 22 When movable cylinder 90 reaches its far right or rear position, vanes 22 are in their extended position and the plurality of flaps have rotated about their pivot points 102, by which they are pivotally attached to inner body 28' and come to rest against sealing cylinder 94 or abut against any stop lug. With vanes 22' so extended, the exhaust gas flow passes through them and through the small holes or nozzles 26 to effect noise suppression as described previously.
  • vanes 22 To cause vanes 22 to move in unison to their nonoperative or tailcone position as shown in Figs. 5 and 6, a pressure source is introduced into chamber 104 of cylinder and is removed from chamber 98 of cylinder 90 to cause movable cylinder 90 to move to its upstream or far left position, carrying sealing cylinder 94 therewith.
  • a pressure source is introduced into chamber 104 of cylinder and is removed from chamber 98 of cylinder 90 to cause movable cylinder 90 to move to its upstream or far left position, carrying sealing cylinder 94 therewith.
  • an inward and forward movement to vanes 22' is effected, due to this forward movement of pivot point 96 and the radially inward movement of pivot point W. as connecting link or rod 86 pivots about pivot 100 on fixed member 84.
  • the exhaust nozzle area at 33' is sized to engine requirements such that the exhaust gases are caused to increase to supersonic velocity at the nozzle throat (smallest area). If exhaust gases were introduced into noise suppressor vanes 22 as supersonic velocity, there would be damaging pressure and engine thrust losses.
  • the gas passage area is increased in dimension, as from Rr to R0, thereby reducing gas velocity to reduce thrust losses by permitting the gas to more smoothly turn into vane 22.
  • the exhaust gas velocity is increased in velocity for thrust purposes as it passes through small holes, apertures or nozzles 26' which direct the exhaust gases downstream during silencing operation.
  • Fig. 7 is shown to give a clearer demonstration of how the exhaust gas passes through holes 24 at the forward edge of vanes 22, then through vanes 22 to be discharged rearwardly through the plurality of holes or nozzles 26'.
  • FIGs. 8, 8A, 9, 9A and 11 we see another embodiment of our invention in which both internal and external hollow vane noise suppressors are used.
  • Figs. 9 and 9A show jet engine with convergent tailpipe and inner body 28" and nacelle 110.
  • Hollow vanes 22" are actuated and operated in the same fashion as the vanes shown and described in Figs. 2 and 2A.
  • Vanes 22" are hollow vanes which may be rotated radially outward through the exhaust gas outlet 38 and extend radially beyond the tailpipe 20 and nacelle 110.
  • Vanes 22 have a plurality of small holes, apertures or nozzles 26 in their trailing edge and of a single aperture or hole 24 in their forward edge.
  • vanes 112 utilizes the plurality of external hollow vanes 112, which are pivoted about the outlet 79' of tailpipe 20 at pivot 114 and are actuated-by any suitable unit such a pivotable hydraulic or pneumatic cylinder and piston unit 116 which is located externally of tailpipe 20" and nacelle 110 and carries actuating rod 118 which is pivotally attached to hollow vane 112 at pivot point 120.
  • any suitable unit such as a pivotable hydraulic or pneumatic cylinder and piston unit 116 which is located externally of tailpipe 20" and nacelle 110 and carries actuating rod 118 which is pivotally attached to hollow vane 112 at pivot point 120.
  • As compressed air or any other fluid source is provided to one or the other side of piston 117, which is located within cylinder 116, the force created will cause linkage 118 and hollow vane 112 to rotate or pivot either in a forward or rearward direction.
  • vanes 112 are in their extended or noise suppressing position.
  • Fig. 8 and 112 are in their extended or noise
  • vanes 112 are in their-retractedor forward position, which is their inoperative position where they lie longitudinally against tailpipe 20" or nacelle 110. Vanes 112 are positioned alternately between vanes 22 and carry pie shaped segment 122 which abuts against adjacent sides 124 and 12.6. of vanes 22" and have any opening or aperture 128 in a forward edge so that, when extended as shown in Figs. 8'
  • the exhaust gas passes through the exhaust outlet formed by tailpipe 20" and inner body 28", through opening 128 in the forward edge of vane 112, thence through vane 112 to be discharged rearwardly through the plurality of small holes or nozzles in the trailing edge of vane 112.
  • engine nacelle 110 projects beyond outlet 79' of tailpipe 20" so as to form a convergent-divergent exhaust nozzle there with when the vanes are in their retracted or non-operative Fig. 5A, 6A position.
  • surface 119 of nacelle 110 is divergent radially outward from exhaust outlet 38".
  • engine nacelle 110 which encloses tailpipe 20 and into which externally retractable vanes 112 are nested in their retracted position.
  • vane actuating unit 116 As a forwardly directed force is placed upon vanes 112 by connecting rods 118 due to the proper pressurizing of vane actuating unit 116, so as to retract the vanes, it will be noted that pie shaped segment 122 of vane 112 will snugly fit into pie shaped aperture 132 of nacelle 110 so as to perform an exhaust gas blocking action and provide a smooth exhaust outlet for engine 10.
  • Pivotable doors 134 serve to enclose retracted vanes 122 when in their retracted positions.
  • Doors 134 are shown in cross section in Fig. 10 and consist of two pivotable units 136 and 138 which have base members 140 and 142 which are integrally attached to curved members 144 and 146 and each pivots about points 148 and 150.
  • base members 140 and 142 are provided at the forward end of door unit 134 only.
  • turning vanes may be used at the inlet of the hollow vanes to assist exhaust gas turning.
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe, an inner body substan tially concentric with and contained within said tailpipe so as to form a gas passage therebetween, a plurality of hollow vanes each having a relatively large aperture in one side and a plurality of relatively small apertures in another side, said vanes being rotatably mounted on said device for movement from a clustered position downstream of said inner body, where they form a conical continuation of the inner body, outwardly to present said large apertures to said gas passage with the plurality of relatively small holes in the other side directed downstream, and means defining the limits of movement of said vanes.
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe, an inner body substantially concentric with and contained within said tailpipe so as to form a gas passage therebetween, a plurality of hollow vanes mounted on said device and each having a relatively large aperture in one side and a plurality of relatively small apertures in another side, means to move said vanes from a clustered position downstream of said inner body, where they form a conical continuation of the inner body, outwardly to present said large apertures to said gas passage with the plurality of relatively small holes in the other side directed downstream, and means to block off said gas passage between adjacent vanes when the vanes are moved outward.
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe, an inner body substantially concentric with and contained within said tailpipe so as to form a gas passage therebetween, a plurality of hollow vanes each having a relatively large aperture in one side and a plurality of relatively small apertures in another side, said vanes being mounted on said device for movement to a clustered position downstream of said inner body, where they form a conical continuation of the inner body, and to an outwardly extended position to present said large aperture to said gas passage with the plurality of relatively small holes in the other side directed downstream, means to so move said vanes, and means to substantially block oft" said gas passage between adjacent vanes when in the outwardly extended position.
  • a noise suppression mechanism comprising an outer duct and inner body concentric with and located within said outer duct so as to form a gas passage therebetween, a. plurality of elongated hollow vanes attached to said inner body and each having one hole in the forward edge thereof and a plurality of rearwardly directed small holes in the trailing edge thereof, an actuating mechanism connected to said vanes for moving them so that they may be clustered in conical form to provide a conical extension of said inner body when in their inoperative position and so that they may be extended radially outward beyond said outer duct while extending across said gas passage so that said forward holes are presented to said gas passage whereby said hollow vanes provide a passage between said small holes and said gas passage, and means to block off said gas passage between said vanes when the vanes are in their extended position.
  • a noise suppression mechanism comprising an outer duct and inner body concentric with and located within said outer duct so as to form a gas passage therebetween, a plurality of hollow vanes attached to said inner body and each having one hole in the forward edge thereof and a plurality of rearwardly directed small holes in the trailing edge thereof, an actuating mechanism connected to said vanes for moving them to a clustered position to form a conical extension of said inner body when in their inoperative position and to an operable position in which the vanes extend radially outward beyond said outer duct while traversing said gas passage so that said forward hole is presented to said gas passage and said hollow vane connects said small holes to said gas passage while said small holes are directed downstream, and a plurality of inwardly directed troughs each projecting from said outer duct to said inner body so that said troughs blend smoothly into said outer duct at their forward ends and project progressively inward until they are in close relation to said inner body at their downstream ends to block said gas passage between said vanes when said vanes are in said
  • a noise suppression mechanism attached to the downstream end of said turbine section comprising an outer duct of circular cross-section, and inner body of circular cross-section concentric with and located within said outer duct so as to form the engine exhaust gas passage therebetween, a plurality of hollow vanes attached to said inner body and each having one hole in the forward edge thereof and a plurality of rearwardly directed small holes in the trailing edge thereof, and an actuating mechanism connected to said vanes for moving them so that they may be clustered in conical form just downstream of said inner body when in their inoperative position to form the engine tailcone therewith and so that said vanes may be extended radially outward beyond said outer duct while traversing said exhaust passage whereby said forward holes connect said exhaust gas passage through said hollow vanes to said small holes to cause the engine exhaust gas passing through said gas passage to pass through said vanes and be discharged rearwardly through said small holes.
  • a noise suppression mechanism comprising an outer duct of circular cross-section, and axially movable inner body of circular cross-section concentric with and located within said outer duct so as to form a gas passage therebetween, a plurality of hollow vanes attached to said inner body and each having one hole in the forward edge thereof and a plurality of rearwardly directed small holes in the trailing edge thereof, an actuating mechanism connected to said vanes for moving them to a clustered position of conical form to provide a conical extension of said inner body when said inner body is in its farthest rearward position and said vanes are in their inoperative position and for moving them to an operable position in which the vanes extend radially outward beyond said outer duct while extending across said gas passage so that said forward hole is presented to said gas passage when said inner body is in its farthest forward position so that said hollow vanes form passages between said gas passage and said small holes which are now rearwardly directed.
  • a device for suppressing the noise of a jet engine exhaust comprising a convergent tailpipe of circular cross-section, a convergent and axially movable inner body substantially concentric with and contained within said tailpipe so as to form a gas passage therebetween and form an exhaust outlet therewith, and a plurality progressively inwardly directed troughs circumferentially spaced about said tailpipe and each projecting from said tailpipe to said inner body such that the forward ends of said troughs blend smoothly with said tailpipe while the rearward ends of said troughs are in close relation to said inner body so as to cause said gas passage to be symmetrical but non-continuous, a plurality of elongated hollow vanes mounted on said device for movement and each having a relatively large aperture near the base of its leading edge and having a plurality of relatively small apertures in its trailing edge, vane actuating means attached to said vanes comprising a pressurized cylinderpiston unit to move said vanes into a clustered position immediately downstream of said inner
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe having an outlet, an inner body substantially concentric with and contained within said tailpipe and terminating short of said tailpipe outlet so as to form a gas passage therebetween, a plurality of hollow vanes each having a relatively large aperture in one side and a plurality of relatively small apertures in another side, said vanes being movable from a clustered position'downstream of said inner body, where they form first an expanding and then a contracting conical continuation of said inner body so that a relatively small exhaust outlet is formed between said tailpipe and said vanes so clustered, outwardly to an operable position in which said large apertures are presented to an enlarged gas passage due to the movement and positioning of said vanes rearwardly while the plurality of relatively small holes in the other sides of said vanes are directed downstream, and means to block ofi D said gas passage between adjacent vanes when said vanes are in said operable position.
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe having an outlet, an inner body substantially concentric with and contained within said tailpipe and terminating short of said tailpipe outlet so as to form a gas passage therebetween, a plurality of hollow vanes each having a relatively large aperture in a first side and a plurality of relatively small apertures in a second side, said vanes being mounted on said device for movement to a clustered position downstream of said inner body Where they form first an expanding and then a contracting conical continuation of said inner body due to the shape of said vanes so that a relatively small exhaust outlet is formed between said tailpipe and said vanes so clustered, and for movement from said clustered position outwardly to an operable position to present said large aperture to an enlarged gas passage due to the movement and positioning of said vanes rearwardly while the plurality of relatively small holes in the second sides are directed downstream, and means to block off said gas passage between adjacent vanes when said vanes are in said operable position, and means to so move said vanes.
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe having an outlet, a-fixed inner body substantially concentric with and contained within said tailpipe and terminating short of said tailpipe outlet so as to form a gas passage therebetween, a plurality of hollow vanes each having a relatively large aperture in one side and a plurality of relatively small apertures in another side, said vanes being positionable in a clustered position downstream of said inner body where they form first an expanding and then a contracting conical continuation of said inner body so that a relatively small exhaust outlet is formed between said tailpipe and said vanes so clustered, means to seal said large vane apertures from said gas passage when said vanes are so'clustered, said vanes also being positionable outward to present said large apertures to an enlarged gas passage due to the movement of said vanes and sealing means while the plurality of relatively small holes are directed downstream, means to block off said gas passage between adjacent vanes when said vanes are moved outward, and means to so position said vanes.
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe having an outlet, a fixed inner body substantially concentric with and contained within-said tailpipe and terminating short of said tailpipe outlet to form a gas passage therebetween, a plurality of hollow vanes each having a relatively large aperture in one side and a plurality of relatively small apertures in another side, said vanes being movable to a-clustered position downstream of said inner body where they form first an expanding and then a contracting conical continuati n of said inner body whereby a relatively small continuous exhaust outlet is formed between said tailpipe and said vanes so clustered, means to seal said large apertures from said gas passage when said 'vanes are so clustered, said vanes also being movable in unison and rearwardly and outwardly simultaneously to an operable position to present said large aperture to an enlarged gas passage due to the movement and positioning of said vanes rearwardly and in which operable position the plurality of relatively small holes in the other sides are directed downstream, means to
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe having an outlet, an inner body substantially concentric with and contained within said tailpipe and terminating short of said tailpipe outlet to form a gas passage therebetween, a plurality of hollow vanes each having a relatively large aperture in its forward edge and a plurality of relatively small apertures in its trailing edge, each of said vanes being roughly triangular in longitudinal cross-section with said trailing edge as the triangle base and which forward edge includes the other triangle legs including the triangle apex, said vanes being retractable to a clustered position downstream of said inner body where they form first an expanding and then a contracting conical continuation of said inner body due to the shape of said vanes whereby a relatively small supersonic exhaust outlet is formed between said tailpipe out-let and said vane apexes, said vanes also being movable rearw-ardly and outwardly to an operable position to present said large aperture to an enlarged gas passage due to the movement and positioning of said vanes rearwardly while the pluralit
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe, an inner body substantially concentric with and contained within said tailpipe so as to form a gas passage therebetween, a first plurality of hollow vanes mounted on said device for movement and each having a relatively large aperture in one side and a plurality of relatively small apertures in another side, said vanes being movable from a clustered position downstream of said inner body, where they form a conioal continuation of the inner body, outwardly to an operable position to present said large apertures to said gas passage while the plurality of relatively small holes 'in the other edges are directed downstream, 'and a second plurality of hollow vanes mounted on said device for movement and each having a relatively large aperture in one side and a plurality of relatively small apertures in another side, said second plurality of vanes being movable from a retracted position external of said tailpipe outwardly tocan operable position to present said large aperture to said gas passage in locations between the vanes of said first plurality while the plurality of
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe, an inner body substantially concentric with and contained within said tailpipe so as to form a gas passage therebetween, a first plurality of hollow vanes mounted on said device for movement and each having a relatively large aperture in one side and a plurality of relatively small apertures in another side, said vanes being movable from a clustered position downstream of said inner body, where they form a conical continuation of the inner body, outwardly to an operable position to present said large apertures to said gas passage while the plurality of relatively small apertures are directed downstream, a second plurality of hollow vanes mounted on said device for movement and each having relatively large aperture in one side and a plurality of relatively small apertures in another side, said second plurality of vanes being movable from a retracted position external of and longitudinally against said tailpipe out- Wardly to an operable position to present said large aperture to said gas passage in locations between the vanes of said first plurality while the plurality of relatively small holes in said second van
  • a device for suppressing the noise of a jet engine exhaust comprising a tailpipe, an axially movable inner body substantially concentric with and contained within said tailpipe so as to form a gas passage therebetween, a first plurality of elongated hollow vanes each pivotally attached to said inner body and each having a relatively large aperture in its leading edge and a plurality of relatively small apertures in its trailing edge, said vanes being movable from a clustered position downstream of said inner body, where they form a conical mounted on said device for movement and located ex ternally of said tailpipe and each having a relatively large aperture in one side and plurality of relatively small apertures in another side, said second plurality of vanes being movable between a retracted position longitudinally against said tailpipe outwardly to an operable position to present said large aperture to said gas passage in locations between the vanes of said first plurality while the plurality of relatively small holes in said second vane plurality are directed downstream, means to actuate said first plurality of vanes, means to actuate
  • a device for suppressing the noise of a jet engine exhaust comprising a convergent tailpipe of circular crosssection, a convergent and axially movable inner body substantially concentric with and contained within said tailpipe to form a gas passage therebetween and form an exhaust outlet therewith, a plurality of elongated hollow vanes each having a relatively large aperture near the base of their leading edge and having a plurality of relatively small apertures in their trailing edge, vane actuating means attached to said vanes comprising a pressurized cylinder-piston unit to move said vanes into a clustered position immediately downstream of said inner body when said inner body is at one end of its travel Where the vanes form a smooth conical continuation of the inner body to form an engine tailcone therewith, said tailcone being of such size to form an exhaust gas outlet of relatively small total area with said tailpipe, said actuating means also moving said vanes outwardly to an extended position to present said large leading edge apertures to a larger gas passage formed when said inner body is at the

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Exhaust Silencers (AREA)
  • Control Of Turbines (AREA)
US588742A 1956-06-01 1956-06-01 Noise suppressors for jet engines Expired - Lifetime US2845775A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US588742A US2845775A (en) 1956-06-01 1956-06-01 Noise suppressors for jet engines
GB16708/57A GB818201A (en) 1956-06-01 1957-05-27 Suppression of jet propulsion engine exhaust noise
FR1182293D FR1182293A (fr) 1956-06-01 1957-05-31 Suppression du bruit d'échappement des moteurs à réaction
DEU4569A DE1114061B (de) 1956-06-01 1957-05-31 Abgasschalldaempfer fuer Strahltriebwerke

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US588742A US2845775A (en) 1956-06-01 1956-06-01 Noise suppressors for jet engines

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US2845775A true US2845775A (en) 1958-08-05

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US (1) US2845775A (de)
DE (1) DE1114061B (de)
FR (1) FR1182293A (de)
GB (1) GB818201A (de)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2882992A (en) * 1957-04-15 1959-04-21 United Aircraft Corp Low-drag exhaust silencer
US2938335A (en) * 1958-04-14 1960-05-31 Boeing Co Noise suppressor and thrust reverser
US2940537A (en) * 1957-01-04 1960-06-14 Gen Sound Control Inc Means and techniques for silencing sound energy
US2952124A (en) * 1957-07-29 1960-09-13 Boeing Co Plug type noise suppressor and thrust reverser
US3032981A (en) * 1957-02-11 1962-05-08 Boeing Co Noise suppressor and thrust reverser for jet engine nozzles
US3036429A (en) * 1957-11-25 1962-05-29 Boeing Co Convertible low-noise jet engine nozzles
US3055174A (en) * 1957-01-14 1962-09-25 Boeing Co Retractable noise suppressor for jet engines
US3061038A (en) * 1959-10-30 1962-10-30 Boeing Co Jet engine noise suppression nozzle with multiple settings
US3067968A (en) * 1958-12-29 1962-12-11 Heppenstall Charles William Retractable jet engine noise suppressor
US3695388A (en) * 1971-06-14 1972-10-03 Textron Inc Quiet jet discharge nozzle
US3865311A (en) * 1972-07-10 1975-02-11 Textron Inc Quiet jet discharge nozzle
US20070029132A1 (en) * 2005-08-05 2007-02-08 Feight Robert P Ported aerodynamic exhaust tailpipe
US20090014235A1 (en) * 2007-07-13 2009-01-15 Paccar Inc Flow diffuser for exhaust pipe
US20090013675A1 (en) * 2007-07-13 2009-01-15 Paccar Inc Flow diffuser for exhaust pipe
US20170122255A1 (en) * 2015-10-28 2017-05-04 Pratt & Whitney Canada Corp. Chevron system for gas turbine engine
US20170335728A1 (en) * 2016-05-23 2017-11-23 Honeywell International Inc. Exhaust systems and methods for gas turbine engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1009776A (en) * 1964-08-25 1965-11-10 Rolls Royce Supersonic jet propulsion nozzle
BE755612A (fr) * 1969-06-18 1971-02-15 Gen Electric Tuyeres de propulsion a systeme suppresseur de bruit ameliore

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2715312A (en) * 1945-07-21 1955-08-16 Power Jets Res & Dev Ltd Jet spoiler for gas turbine jet propulsion plant
US2771740A (en) * 1950-11-16 1956-11-27 Lockheed Aircraft Corp Afterburning means for turbo-jet engines

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Publication number Priority date Publication date Assignee Title
GB675624A (en) * 1950-05-08 1952-07-16 Mcdonnell Aircraft Corp Device for varying the effective area of discharge orifices of jet propulsion engines

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2715312A (en) * 1945-07-21 1955-08-16 Power Jets Res & Dev Ltd Jet spoiler for gas turbine jet propulsion plant
US2771740A (en) * 1950-11-16 1956-11-27 Lockheed Aircraft Corp Afterburning means for turbo-jet engines

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2940537A (en) * 1957-01-04 1960-06-14 Gen Sound Control Inc Means and techniques for silencing sound energy
US3055174A (en) * 1957-01-14 1962-09-25 Boeing Co Retractable noise suppressor for jet engines
US3032981A (en) * 1957-02-11 1962-05-08 Boeing Co Noise suppressor and thrust reverser for jet engine nozzles
US2882992A (en) * 1957-04-15 1959-04-21 United Aircraft Corp Low-drag exhaust silencer
US2952124A (en) * 1957-07-29 1960-09-13 Boeing Co Plug type noise suppressor and thrust reverser
US3036429A (en) * 1957-11-25 1962-05-29 Boeing Co Convertible low-noise jet engine nozzles
US2938335A (en) * 1958-04-14 1960-05-31 Boeing Co Noise suppressor and thrust reverser
US3067968A (en) * 1958-12-29 1962-12-11 Heppenstall Charles William Retractable jet engine noise suppressor
US3061038A (en) * 1959-10-30 1962-10-30 Boeing Co Jet engine noise suppression nozzle with multiple settings
US3695388A (en) * 1971-06-14 1972-10-03 Textron Inc Quiet jet discharge nozzle
US3865311A (en) * 1972-07-10 1975-02-11 Textron Inc Quiet jet discharge nozzle
US20070029132A1 (en) * 2005-08-05 2007-02-08 Feight Robert P Ported aerodynamic exhaust tailpipe
US7703573B2 (en) * 2005-08-05 2010-04-27 Paccar Inc Ported aerodynamic exhaust tailpipe
US20090014235A1 (en) * 2007-07-13 2009-01-15 Paccar Inc Flow diffuser for exhaust pipe
US20090013675A1 (en) * 2007-07-13 2009-01-15 Paccar Inc Flow diffuser for exhaust pipe
US7971432B2 (en) 2007-07-13 2011-07-05 Paccar Inc Flow diffuser for exhaust pipe
US20170122255A1 (en) * 2015-10-28 2017-05-04 Pratt & Whitney Canada Corp. Chevron system for gas turbine engine
US20170335728A1 (en) * 2016-05-23 2017-11-23 Honeywell International Inc. Exhaust systems and methods for gas turbine engine
US10184372B2 (en) * 2016-05-23 2019-01-22 Honeywell International Inc. Exhaust systems and methods for gas turbine engine
US10954834B2 (en) 2016-05-23 2021-03-23 Honeywell International Inc. Exhaust systems and methods for gas turbine engine
US11255239B2 (en) 2016-05-23 2022-02-22 Honeywell International Inc. Exhaust systems and methods for gas turbine engine

Also Published As

Publication number Publication date
FR1182293A (fr) 1959-06-24
DE1114061B (de) 1961-09-21
GB818201A (en) 1959-08-12

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