|Publication number||US3602333 A|
|Publication date||31 Aug 1971|
|Filing date||15 Oct 1969|
|Priority date||15 Oct 1969|
|Publication number||US 3602333 A, US 3602333A, US-A-3602333, US3602333 A, US3602333A|
|Inventors||Hiramatsu Koichi, Kobayashi Shunji, Kuwabara Sathihiro, Yoshihara Isao|
|Original Assignee||Chiyoda Chem Eng Construct Co|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (6), Referenced by (22), Classifications (15)|
|External Links: USPTO, USPTO Assignment, Espacenet|
United States Patent inventors Shunji Kobayshi Yokohama-shi;
Kokhl l-liramatsu, Tokyo-to; Isao Yoshihara, Tokyo-to; SathihiroKuwabara, Tokyo-to, all of, Japan Oct. 15,1969
Appl. No' Filed Division of Ser. No. 658,395, Aug. 4, 1967,
M13313 971 l Chiyoda Kako Kemetsu Kabushlki Kais Tokyo-to, Japan Patented Assignee SILENCER FOR SUCTION 0R DISCHARGE 0F FLUIDS UNDER PRESSURE 7 Claims, 13 Drawing Figs.
U.S. Cl 181/42, 181/56,18 1/60,415/119 Int. Cl ..F04b 39/00, F01n l/10,'F01n 7/20 Field ofSearch 181/42,46,
[ 56] References Cited UNITED STATES PATENTS 1,940,790 12/1933 Diehl 181/46 X 2,144,631 1/1939 Kurth l81/50X 2,415,621 2/1947 Arnhym 415/119 3,346,174 10/1967 Lievens et al 415/119 FOREIGN PATENTS 601,872 8/1934 Germany 181/60 444,206 3/1936 Great Britain 181/50 Primary Examiner-Robert S. Ward, Jr. Attorney-Marmorek & Bierman ABSTRACT: On the basis of the otiservation that a fluid under pressure difi'uses in a conical path with a certain divergent angle into a region of lower pressure, a silencer, through which a noise generating flow of a fluid is passed, is made up of a combination of concentric outer, intermediate, and inner shells respectively having shapes of hollow truncated cones with specific divergent angles in the discharge direction and provided on both surfaces or single surfaces thereof with sound absorbing layers of specific thicknesses.
PATENTEU M1831 can SHEET 1 OF 5 INVENTORS ATTORNEYS PATEHTEU was] I97:
SHEET 3 BF 5 FIG.8
wmmmmwwmwwmwww Fy j i 3 3 3 Q 3 I E i 1 \i ii \C\\ @A\\i wmmmmmwwmwwmwmm FREQUENCY (CYCLES SECOND) ATTORNEYS FIG.9
' PRIOR ART ATTORNEYS SILENCER FOR SUCTION R DISCHARGE OF FLUIDS UNDER PRESSURE This application is a division of the previously filed application for a SILENCER FOR SUCTION OR DISCHARGE OF FLUIDS UNDER PRESSURE, having Ser. No. 658,395; filed Aug. 4, I967 which issued as US. Pat. No. 3,503,465 on Mar. 31, 1970.
This invention relates generally to devices known as mufflers or silencers for reducing noise due to high-velocity flow of fluids. More particularly, the invention relates to silencers for reducing excessive and undesirable noise generated in cases wherein a gas under pressure such as steam or'a compressed gas is caused to undergo sudden expansion, wherein a gas is abruptly aspirated and/or discharged by means of a fan or blower.
More specifically, the invention contemplates the provision of a new silencer of the above stated character having the shape of a hollow cone and producing very little back pressure, thereby to provide effective suppression means with respect to frequently occurring noise constituting a public nuisance.
Heretofore, the principal measures generally resorted to for reducing noise of the character referred to above have been: a) to separate the noise source from regions where the noise would be undesirable, b) to provide a sound shielding wall or barrier between the noise source and the regions where the noise would be undesirable, and c) to muffle the noise at its source by means of one or more mufflers or silencers (hereinafter referred to as silencers).
The above measure a obviously not suitable in an industrial area, where the population density in high, in already existing plants, mills, etc., and in similar places where noise reduction is often most needed. While measure b is substantially effective when the sound shielding wall structure is appropriately designed, its installation often entails very high costs.
In most of the silencers known heretofore fore the above measure 0, sound reduction is accomplished principally by ejecting the gas causing the noise through numerous fine holes and, at the same time, reducing the gas velocity in a stepwise manner or by causing the gas to flow through a circuitous or tortuous path to reduce the gas flow velocity. In each case,
FIG. 1 is a diagrammatic representation indicating the state and behavior of the released gas in the case wherein a gas under pressure is discharged naturally to a region of low pressure through a straight tube;
FIG. 2 is a side view, in longitudinal section, showing the basic form of a silencer according to the invention, in which an outer shell of the shape of a hollow truncated cone having a certain outwardly divergent angle is connected to the straight tube shown in FIG. I; 7
FIG. 3 is a side view, in longitudinal section, showing a silencer similar to that shown in FIG. 2 in which the interior gas flow path is divided by an inner shell of the shape of a hollow truncated cone disposed coaxially with the outer shell and having sound-absorbing layers -on the inner and outer surfaces thereof;
FIG. 4 is a perspective view, showing one example of a silencer according to the invention;
, FIG. 5 is a side view, in longitudinal section, of the silencer shown in FIG. 4;
FIG. 6 is an enlarged, fragmentary view showing the details of one part of the view shown in FIG. 5;
FIG. 7 is a crosssectional view taken along the plane indicated by line VII-VII in FIG. 5;
since the gas velocity is forcibly reduced, the pressure loss of the silencer itself, that is, the back pressure, vantageously excessive.
' It is an object of the present invention to overcome the above described difficulties heretofore accompanying attempts to reduce noise.
More specifically, an object of the invention is to provide a silencer of simple and economical organization having high effectiveness in silencing noise with very low back pressure and not requiring special materials or special fabrication techniques.
According to the present invention, briefly summarized, there is provided a silencer for reducing noise generated by a flow of a fluid through an opening, the silencer comprising an outer shell of a configuration lying substantially in and along a surface corresponding to the outer boundary layer of the fluid flow in free state which it would assume prior to provision of the silencer and connected to the opening, the fluid thereby being caused to flow within the outer shell with or without one or more shell-like guide members disposed within the outer shell to divide the flow therein into a plurality of concentric flow paths without appreciably increased flow resistance and to provide streamline flow without turbulence, and sound absorbing material lining the surfaces of the outer shell and guide member or members along the flow paths.
The nature, principle, details, and utility of the invention will be more clearly apparent from the following detailed description with respect to preferred embodiments of the invention when read in conjunction with the accompanying drawings, in which like parts are designated by like reference numeral and characters.
In the drawings:
FIG. 8 is a graphical representation indicating the sound reducing effect due to a silencer of the invention;
FIG. 9 is a side view, in longitudinal section showing one example of a known axial flow air fan and indicating the air flow thereabout during operation;
FIG. 10 is a'view similar to FIG. 9 showing an axial flow air fan provided with one example of a silencer according to the invention and indicating improved air flow;
FIG. 11 is a view similar to FIG. 10 showing an axial flow air fan'provided with another example of a silencer according to the invention;
FIG. 12 is a graphical representation indicating a comparison of characteristics with respect to frequency of noise generated by a known axial flow air fan and of noise generated by an axial flow air fan provided with a silencer according to the invention; and
FIG. 13 is a diagrammatic elevational view showing the essential parts of the apparatus used for experimental measurements from which the characteristic curves of FIG. 12 were obtained.
In general, when a body of a gas under a certain first pressure is released to be discharged in a natural manner through a straight tube to a region at asecond pressure lower than the first pressure, the gas is difi'used in a conical pattern with a jet angle a which is deten'nined by the difference betweenfrrst and second pressures, this jet angle a being, in general, between 10 and 40. As this discharged gas travels away from the point of discharge, the discharge gas velocity decreases until, finally, it is dissipated.
A gas discharge of this nature is accompanied by the generation of excessively loud noise, which is understood to be caused by turbulence accompanying the gas discharge. More explicitly, a turbulent gas flow consisting principally of eddies or vortices is produced-by the velocity differences at the interface layer between the discharged gas stream and the surrounding stationary gas and by the differences in the velocities at various parts throughout the discharged gas. The transformation .of this turbulent flow into vibration energy gives rise to the excessively loud noise. Therefore, a measure for imparting sound reducing effect can be realized by suppressing as much as possible turbulent flow in the above mentioned interface layer and within the discharge gas flow.
The silencer of the present invention, in general, has a principal outer shell structure of a shape in which the cross-sectional area of the gas flow path therethrough increases progressively in the flow direction at a rate such that the resulting divergent angle of the flow path formed within the shell structure coincides substantially with the jet angle of the high-pressure gas determined by the above mentioned pressure difference, the inner surface of the shell structure, that is, the surface of the structure to contact the gas to be subjected to noise reduction, being covered with a sound-absorbing layer.
The principle of the invention will first be considered with reference to FIG. 1. When a gas under pressure is discharged through a straight tube 1, it disperses witha jet angle a, and the velocity distributions at various cross sections of the resulting gas flow are as indicated by intennittent-line curves 5. These velocity gradients within the gas flow progressively decrease in the flow direction and become zero at a point where the gas becomes fully mixed and diffused with the atmosphere. 7
Since the velocity gradient at the interface layer 2 between the discharged gas flow and the outside air 3 at any cross section is a maximum, vortices of maximum intensity are present in layer form in this interface layer 2. The intensity of these vortices decreases progressively with the distance from the discharge outlet of the straight tube 1 until it is finally dissipated. I
In a silencer according-to the invention of basic form as illustrated in FIG. 2, an outer shell 7' is communicatively connected at its inner or upstream end to the above mentioned straight tube 1 and is formed with an outwardly divergent angle. In the case wherein this divergent angle is caused be equal to the jet angle a resulting from the natural discharge of the gas, the inner surface of the outer shell 7 will coincide with the interface 2 which would exist in the case of natural discharge. Accordingly, direct contact between the flowing gas and the outside air 3 is prevented by the presence of the outer shell 7 constituting a physical barrier therebetween, whereby there is no generation of a turbulent flow layer due to inductive action of the flowing gas on the outside air 3. 7
Thus, generation of noise can be suppressed. Moreover, by thus providing an outer shell 7 with a divergent angle equal to or close to the above mentioned jet angle, there is no possibility of development of a back pressure in thedischarged gas.
As the discharged gas flows through the outer shell 7, its velocity progressively decreases until, at the discharge outlet 8 of the shell 7 opening to the atmosphere, the velocity is amply reduced, whereby the noise generated in the region downstream from the discharge outlet 8 is of very low level.
The velocity gradient at the inner surface of the outer she'll 7 existing'in the position of theabove mentioned interface layer is still of large magnitude and generates noise of high intensity. Accordingly, as a noise reducing measure, the entire inner surface of the shell 7 is covered with 'a sound absorbing layer 9 made of a sound absorbing material of a specific thickness, as mentioned hereinbefore. The sound absorbing layer 9 absorbs most of the noise generated at the part corresponding to the above mentioned interface layer and, at the same time, functions also to absorb noise generated by velocity gradients arising within the discharge gas stream. The velocity distribution across one cross section of the silencer interior is indicated in FIG. 2 by intermittent-line curve 50 constituting an envelope of the velocitycomponents 10-.l, 10-2, etc. at that cross section.
The gas flow path .within the silencer illustrated in FIG. 2 may be divided into two concentric flow paths as shown in FIG. 3 by an inner shell 7a disposed coaxially relative to the outer shell 7 and covered over the inner and outer surfaces thereof with sound absorbing layers 9a, 9a. In this case, the gas discharged through tube 1 is caused to'flow in divided flow paths with velocity distributions as indicated by intermittentline curves as, for example, curve Sa-I. Thus, it will be apparent that the resulting velocity distributions are different from that indicated by curve 50 in FIG. 2, and the absolute velocity differences mutually between the velocity components 100-], 100 2, etc., are remarkably reduced. Therefore, the inner shell 70 provides an increase in the sound absorbing area and, moreover, functions also to impart a flow straightening effect and to decrease velocity gradients.
In another embodiment of the invention as illustrated in or a'compressed gas (hereinafter referred to as "fluid") and an outer shell 7 contiguously connected to the discharge end of the inlet pipe 15 and enclosing and forming a part of a noise silencing structure. The inlet pipe 15 has a flange 15a at its inlet end for connection to a pipe line or some item of equipment (not shown) which the fluid is to be released.
The inlet pipe 15 has the form of an increaser, and the ratio of the cross-sectional areas at its inlet and outlet is from 1:1 to 1:2. The noise silencing structure is of concentric construction and comprises a central inner shell 7c, an intermediate shell 7b, and the outer shell 7, the inner and intermediate shells 7c and 7b being coaxially supported and secured to the outer shell 7 by support struts 14, 14. The discharge end 16 of the noise silencing structure thus constituted is diagonally cut and lies in a plane at an angle of from 30 to 60 relative to the iongitudinal axis of the structure.
Wl-lile a single intermediate shell 7b and a central inner shell 70 are shown in the illustrated example, two or more intermediate shells may be used with orwithout the central inner shell, depending on the desired effectiveness of the silencer.
As shown in FIG. 6, the outer shell 7 is a hollow truncated cone formed from a material of high mechanical strength such as steel sheetorplate and is covered over its entire inner surface with a sound absorbing layer 12 of a specific thickness made of a sound absorbing material such as glass fiber or asbestos. The entire inner surface of the layer 12 is covered with-a retaining layer 13 made of a perforated sheet material to retain and protect the surface of the sound absorbing layer 12 and to prevent erosion thereof.
The intermediate shell 7b is similarly a hollow truncated cone formed from a material such as steel sheet or plate and is covered over the entire inner and outer surfaces thereof with sound absorbing layers l2, 12 similar to that of the outer shell 7, which layers l2, 12 are similarly covered with respective retaining layers 13, 13.
The inner shell 7c comprises an outer shell 13a of a perforated sheet material formed into a hollow truncated cone of small taper and a sound absorbing material 12a filling the interior of the cone.
As is well known, the discharge end 16 of the silencer cut diagonally at an angle of from 30 to 6 relative to the silencer axis as described above causes mutual nullification of resonance effects of specific frequencieswithin the silencer shells, and the increased area of the exit section makes possible further decrease in the velocity of the fluid at the discharge end. Moreover, there is no occurrence of reaction due to change of direction of the fluid flow within the silencer, whereby directivity can be imparted thereto.
In the silencer of the above described construction, the fluid under pressure passes through the inlet pipe 15 and flows into the noise silencing structure. The fluid then proceeds to flow v described silencer are determined in the following manner.
The angle of divergence of the shells of the silencer are determined within a range of from 7 to 33, which is from 3' to 10 narrower than the jet angle determined by the aforementioned pressure difference, that is, from 10 to 40. The sectional area of the discharge end 16 is so determined that the fluid discharge velocity at the section will be less than 60 meters/sec. Furthermore, the length L of the silencer is also selected in accordance with the required degree of noise 7 reduction, similarly as in the selection of the number of intermediate shells and in the decision on whether or not to use an inner shell. 1 i
The noise reducing effectiveness of the silencer according to the invention is indicated by the results as shown in FIG. 8
of one instance of actual practice. In this graphical representation, contour line (A) is one of a family of similar contour lines shown therebelow each of which is an isophonic contour joining the respective points of sound pressure levels which noise at various frequencies impart isophonically to the human ear and is generally referred to as a noise rating number (NRN) curve. The noise rating number is generally expressed in terms of the magnitude of the sound pressure level at a frequency of 1,000 c./s.
In the same FIG. 8, curve (B) is a frequency characteristic curve of noise emitted from a specific noise source (in this case, high-pressure steam at a pressure of kg./cm. discharged into the atmosphere through a 2-inch nozzle at a flowrate of 3 tons/hour), the noise being measured at a position 8 meters directly in front of the nozzle.
To the nozzle of the above described noise source, a silencer in accordance with the invention was connected. This silencer comprised outer, intermediate, and inner shells and had an overall length of 1.4 meters, an inlet throat diameter of 2 inches, a shell divergent angle of 6, and a diagonally cut discharge end at an angle of 45 relative to the silencer axis. Steam was discharged under the same conditions as in the case when the curve (B) wasobtained, and the resulting noise was measured at the same position, whereupon completely satisfactory noise-reducing results as indicated by curve (C) were obtained.
While the invention has been described above with respect to silencers for fluid discharge, it should be understood that the present invention can be applied also to silencers for reducing noise arising from fluid suction or aspiration with the same facility and effectiveness.
The silencer according to the present invention has the following advantageous features.
I. Since the flow direction of the fluid does not change, the pressure loss due to the silencer is very small. Accordingly, when the silencer is used, for example, for reducing the noise of discharge of a safety valve, the adjustment of the discharge pressure of the safety valve is facilitated.
2. Since a reaction force is not produced at the time of fluid discharge, the construction 'of the mounting part of the silencer can be simplified, and the handling of the silencer also is facilitated.
3. High noise-reducing performance is obtained by a silencer of simple organization and relatively small overall size.
4. Since the organization is simple, and the overall size is small, the adaptability of the silencer with respect to the required degree of noise reduction is excellent.
The silencer of the present invention in various embodiments thereof has wide applicability, one typical example of which is the use of the silencer to reduce the noise of an axial flow fan of an air-cooled heat exchanger, as described below.
With the recent scarcity of water for industrialuse in most industrial areas, there has been a rapid increase in the use of air-cooled heat exchangers to take the place of formerly used water-cooled heat exchangers. Since an air-cooled heat exchanger of this. type requires a supply of a large flowrate of air at a relatively low pressure, an axial flow fan is generally used for supplying this air. In general, an axial flow fan for this purpose is of large size with a propeller diameter of the order of from 1.8 to 5 meters-and produces an air velocity below meters/sec. Moreover, the air flow through the fan is such that, on the suction side, the flow velocity is high at the outer periphery and decreases toward the center, and vortices are formed in the vicinityof the rotational axis, whereby a part of the fan driving power is wasted.
Furthermore, the noise. generated by an axialflow fan is as high asfrom. 90w 1 l0 phon (average), at a distance equal to the propeller diameter from the end. of the fan casing; Since the frequency characteristic of this noise issuch that a greater part of the components are of frequencies below 500 c./s., noise reductionisdifllcult and, in general, has heretofore'been neglected, whereby this noise has been a source of discomfort to person in the vicinity of fans of this type and even a source of public nuisance.
This noise can be reduced in a simple manner by the application of the silencer of the present invention whereby noise components of frequencies higher than 200 c./s. which cause discomfort to the human ear of the noise generated by an axial flow fan of the type referred to above are reduced without causing any appreciable rise in the power required for driving the fan.
The causes of noise generated by an axial flow fan may be divided into the following kinds.
1. Intermittent cutting of air layers by the rotating propeller blades.
2. Vortices created particularly in the vicinity of the rotational axis and blade tips.
3. vibration of the propeller blades.
4. Other causes such as vibrations of structural parts.
Noise due to cause 4, above, can be suppressed by adirect measure such as increasing the rigidity of the structural parts. All of the causes other than cause 4, however, are due to the basic nature of construction and operation of the fan, and, therefore, a supplementary measure such as the installation of a silencer is more practical and effective.
In one example as illustrated in FIG. 9 of an axial flow fan of the type referred to above, a propeller 23 fixed to and driven by a shaft 22 is positioned to rotate within a ring 21 and thereby to draw air through a nest 30 of a large number of thin tubes, such as a radiator, through which tubes a fluid is passed and thereby cooled, and the air thus drawn is discharged to the opposite side of the propeller, as indicated by arrows. On the discharge side, vortices as indicated by arrows are formed by differences in the flow velocities of the flowing air.
As mentioned hereinbefore, when vortices are formed in the vicinity of the rotational axis, the air flowrate is reduced correspondingly, whereby the effective air delivery of the fan decreases, and, consequently, there is a'loss.of air delivery power.
One example of a silencer of the invention installed on the discharge side of the above described axial flow fan as illustrated in FIG. 10 to overcome the above described difficulties comprises a silencer outer shell 24 and an inner shell 26. The outer shell 24 is made of steel sheet formed into a truncated cone with an outwardly divergent angle and'coveredover its inner surface with a sound absorbing material such as asbestos or glass fiber of a specific thickness. Accordingly, the outer shell 24 causes the dynamic pressure of the fan to be recovered as an effective static pressure and, moreover, has the efiectof reducing the noise.
In-the case where the fan diameter is large, or when necessitated by the-required degree of noise suppression, it is possible to installalso an intermediate shell 25 as shown in FIG. 1 l. Theintermediate shell 25 is made of steel sheet formed into a truncated cone with an outwardly divergent angle and is covered over its inner and outer surfaces with a sound absorbing material of specific thickness. In this case, the intermediate shell 25 functions as a flow straightening 'guide plate on the discharge side and also has the effect of absorbing and diminishing noise.
The length l in the axial direction of the outer shell 24 and the intermediate shell 25 is determined from the relationship of the frequency range of the noise to be reduced and the velocity of sound. One or more intermediate shells 25 can be used depending on the required degree of noise reduction.
The inner shell 26 is made of steel sheet formed into a truncatedcone'with an outwardly divergent angle and is closed at its outer or downstream end by a cover plate 27. The inner and: outer surface of the inner shell 26 and its cover plate 27 are covered with a sound absorbing material. The inner or upstream. end of the inner shell 26 is covered by a sound absorbing structure consisting of a combination of a perforate plate 29and a porous sound absorbing material.
Thus, the inner shell 26 has a construction which is a modification of the so-called Helmholtz resonator. Ac-
cordingly, a part of the noise energyis passed through the perforated plate 29 and enters the interior of the inner shell 26 whereby sounds of certain frequencies are damped in accordance with the principle of the Helmholtz resonator, and the sounds of other frequencies are absorbed and reduced in intensity by the sound absorbing material covering the inner surface of the inner shell 26.
Furthermore, the upstream and lateral outer surfaces of the inner shell 26 serve to smooth and straighten the vortices produced in the vicinity of the propeller axis and, therefore, have the effect of increasing the fan efficiency. The shape and dimensions of the inner shell 26 are determined by the frequencies of the noise to be reduced.
By the above-described outwardly divergent construction, the silencer according to the invention causes recovery of the fan dynamic pressure as effective static pressure, and vortices are eliminated by the position of the inner shell on the silencer axis thereby to cause an increase in the fan eff ciency. Moreover, the silencer of the invention has high noise-reducing effectiveness due to the multiplication; in effect, of the noise-reducing effect of the sound absorbing material of large surface area disposed in the form of concentric cones coaxially relatively to the silencer axis and the noise-reducing effect due to the hollow inner shell.
In the reduction of noise through the use of a silencer according to the invention, the noise-reducing performance of the silencer can be adjusted in accordance with the requirements by appropriately selecting factors such as the shape and dimensions of the inner shell 26, the use of one or more intermediate shells 25, the number of intermediate shells 25, and the length l of the shells. 4
Furthermore, it is possible, as illustrated in FIG. 11, to install the above-described silencer on the discharge side of the propeller 23 and, in addition, to install another silencer comprising an outer shell 31, an intermediate shell 32, and an inner shell'33 on the inlet or suction side of the propeller. In such an installation, it is necessary that the silencer on the suction side have an organization capable of reducing noise and a streamlined configuration such that the silencer parts will not disturb the flow ofair and will not constitute parts imposing unnecessary air resistance.
The noise-reducing effectiveness of the silencer of the in- 1 vention is further indicated by the NRN curves shown in FIG. 12 resulting from an actual instance of installation of a silencer according to the invention in a large axial flow fan which was connected to an air-cooled heat exchanger and had a propeller of 3.6-meter diameter rotating at 300 r.p.m. As indicated in FIG. 13, the fan constituting a noise source S was positioned at a height of 7 meters above the ground level (LL, and the noise emitted therefrom was measured at a sound receptionpoint P positioned 1 meter above the ground level at a horizontal distance of 1 1.5 meters from the noise source S.
In FIG. 12, curve (E) is the acoustic output curve of the large axial flow fan and corresponds to NRN-110 Curve (F) indicates the frequency characteristic values of the noise at the sound reception point P in the case wherein sound insulation and sound absorption effects are not considered and, corresponding to NRN-75, indicates the reduction of curve (E) due to distance- Curve (G) is the NRN curve corresponding to an allowable value of noise at the sound reception point P of NRN-40. Accordingly, in the case bf an allowable noise value of NRN-40, it is necessary to take various noise-reducing measures before the noise characteristic curve assumes sound pressure levels below those of the curve (G).
In accordance with the graph shown in FIG. 12, we carried out tests on the characteristics of the silencer of the invention. Curve (l-I) indicates the sound reducing effect due to the provision of a sound shielding wall -00 as shown in FIG. 13. From this result it was clearly apparent that a measure of this order wherein a small-scale noise shielding OOa was provided was insufficient to reduce the noise to a value below the above mentioned allowable noise value.
Then, when a silencer according to the invention was installed on the discharge side of the large axial flow fan, and measurements were made at the sound reception point P, it was possible to obtain results, as expected, as indicated by curve (.I). In FIG. 12, the region with diagonal cross hatching indicates the sound pressure level values reduced by the silencer of the invention.
It should be understood, of course, that the foregoing disclosure relates to only preferred embodiments of the invention and that it is intended to cover all changes and modifications of the examples of the invention herein chosen or the purposes of the disclosure, which do not constitute departures from the spirit and scope of the invention as set forth in the appended claims.
What we claim is:-
l. A silencer for suction or discharge of a fluid due to a pressure difference comprising: an inlet pipe for said fluid having the construction of an increaser pipe; an outer shell made of a rigid plate material having a sound shielding characteristic, said outer shell having the shape of a hollow truncated cone with an outwardly divergent angle and contiguously .connected at the small-diameter end thereof to the inlet pipe, the inner surface of the outer shell being covered with a sound absorbing layer of a specific thickness; at least one intermediate shell having the shape of a hollow truncated cone and supported within and coaxially with the outer shell by at least one supporting member; and an inner shell disposed coaxially at the centerline of the outer shell, the combination of the outer shell, said at least one intermediate shell, and the inner shell constituting a noise-reducing mechanism.
2. The silencer as claimed in claim 1 in which each intermediate shell is covered over the inner and outer surfaces thereof with respective sound absorbing layers filled with sound absorbing material.
3. The silencer asclaimed in claim I in which the inner shell has a hollow interior space filled with a sound absorbing material 7 I 4. The silencer as claimed in claim 1 in which the outer shell, each intermediate shell, and the inner shell have respective outwardly divergent angles within the range of from 7 to 33.
5. The silencer as claimed in claim 1 in which the outer, large-diameter end of the entire silencer is cut ofi alonga plane-at an angle of from 30 to 60 relative to the silencer centerline.
6. A silencer for an axial flow fan for causing flow of a fluid, comprising an outer shell and an inner shell-disposed within the outer shell, each shell having the shape. of a hollow. truncated cone or pyramid with a divergent angle in the outward, discharge direction and having sound absorbing material on surfaces thereof along which said fluid is to flow, said shells being disposed and supported in respective positions coaxial with said axial flow fan, the inner shell being a hollow vessel structure closed at the end thereof in the outward, discharge direction and having an open opposite end covered by a porous sound absorbing structure, the outer surface of the inner shell being covered with a sound absorbing material.
7. A silencer for an axial flow fan having a propeller driven by a shaft on the upstream side thereof and disposed coaxially within a cylindrical structure, said silencer comprising, in combination: a downstream silencer structure disposed coaxially with and downstream from the propeller and consisting, essentially, in concentric arrangement,
an outer shell connected at its upstream end to the downstream end of said cylindrical structure, an inner shell closed at its downstream end and having an open upstreamend covered by a poroussound absorbing structure, and
at least one intermediate shell disposed between the 'o'uterand inner shells,
each of said shells having the shape of a hollow truncated cone with a divergent angle in the downstream direction and having sound absorbing material on surfaces thereof along which said fluid is to flow; and
and inner shells, 7 each of said shells having the shape of a hollow truncated cone with a divergent angle in the upstream direction and having sound absorbing material on surfaces thereof along which said fluid is to flow.
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US1940790 *||18 Oct 1930||26 Dec 1933||Diehl Walter S||Fluid conducting passage|
|US2144631 *||24 Aug 1936||24 Jan 1939||Anemostat Corp||Air distributing device|
|US2415621 *||20 Oct 1944||11 Feb 1947||Solar Aircraft Co||Fan|
|US3346174 *||5 Jul 1966||10 Oct 1967||Trane Co||Compact axial flow fan|
|DE601872C *||28 Jul 1933||27 Aug 1934||Franz Josef Kurth||Vorrichtung zur Verhuetung der Flammenbildung|
|GB444206A *||Title not available|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US3977493 *||1 Nov 1973||31 Aug 1976||Kay Keith Richardson||Exhaust control method and apparatus|
|US4240250 *||27 Dec 1977||23 Dec 1980||The Boeing Company||Noise reducing air inlet for gas turbine engines|
|US5810566 *||15 Nov 1996||22 Sep 1998||Atlas Copco Airpower||Pulse damper or acoustic outlet piece for a compressor and compressor equipped therewith|
|US6672424 *||15 Dec 1999||6 Jan 2004||Turbomeca||Acoustically treated turbomachine multi-duct exhaust device|
|US7334998||6 Dec 2004||26 Feb 2008||The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration||Low-noise fan exit guide vanes|
|US7364011 *||4 Apr 2003||29 Apr 2008||Martin Hirschorn||Attenuating power booster|
|US7472774 *||27 Jan 2006||6 Jan 2009||Lockheed Martin Corporation||Versatile engine muffling system|
|US7905321 *||28 Aug 2009||15 Mar 2011||Ballard Iii Ebbin C||Inserts for engine exhaust systems|
|US8066096 *||4 Nov 2010||29 Nov 2011||Hamilton Sundstrand Corporation||Inlet silencer|
|US8967949||19 Jul 2010||3 Mar 2015||Soler & Palau Research, S.L.U.||Sound-proofed helicocentrifugal fan|
|US20030213643 *||4 Apr 2003||20 Nov 2003||Martin Hirschorn||Attenuating power booster|
|US20040099477 *||17 Sep 2001||27 May 2004||Mats Abom||Sound absorbent|
|US20060086563 *||21 Oct 2004||27 Apr 2006||Ingersoll-Rand Company||Compressor discharge pulsation dampener|
|US20060104819 *||6 Dec 2004||18 May 2006||United States Of America, Administrator Of The National Aeronautics And Space Administration||Low-noise fan exit guide vanes|
|US20090321181 *||28 Aug 2009||31 Dec 2009||Ballard Iii Ebbin C||Inserts for engine exhaust systems|
|US20120204534 *||15 Feb 2011||16 Aug 2012||General Electric Company||System and method for damping pressure oscillations within a pulse detonation engine|
|EP0774581A1||11 Nov 1996||21 May 1997||Atlas Copco Airpower N.V.||Pulse damper or acoustic outlet piece for a compressor and compressor equipped therewith|
|EP0933503A3 *||20 Jan 1999||17 Nov 1999||ALSTOM Energy Systems GmbH||Silencer for a gas turbine exhaust channel|
|WO2001042631A1 *||7 Dec 2000||14 Jun 2001||Abb Ab||Exhaust system|
|WO2005057001A2 *||7 Dec 2004||23 Jun 2005||United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration||Low-noise fan exit guide vanes|
|WO2005057001A3 *||7 Dec 2004||6 Apr 2006||Nasa||Low-noise fan exit guide vanes|
|WO2011015680A1 *||19 Jul 2010||10 Feb 2011||Soler & Palau Research, S.L.U.||Sound-proofed helicocentrifugal fan|
|U.S. Classification||181/252, 415/119|
|International Classification||F04B39/00, F01B31/16, F04D29/66, F01B31/00, F02C7/24|
|Cooperative Classification||F04D29/664, F02C7/24, F01B31/16, F04B39/0083|
|European Classification||F02C7/24, F04B39/00D14, F04D29/66C4B, F01B31/16|