US3531048A - Supersonic streaming - Google Patents
Supersonic streaming Download PDFInfo
- Publication number
- US3531048A US3531048A US718447A US3531048DA US3531048A US 3531048 A US3531048 A US 3531048A US 718447 A US718447 A US 718447A US 3531048D A US3531048D A US 3531048DA US 3531048 A US3531048 A US 3531048A
- Authority
- US
- United States
- Prior art keywords
- nozzle
- supersonic
- inlet
- diameter
- boundary layer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 239000007789 gas Substances 0.000 description 18
- 239000007788 liquid Substances 0.000 description 12
- 239000003921 oil Substances 0.000 description 12
- 239000012530 fluid Substances 0.000 description 9
- 230000006641 stabilisation Effects 0.000 description 7
- 238000011105 stabilization Methods 0.000 description 7
- 230000000694 effects Effects 0.000 description 5
- 239000003381 stabilizer Substances 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 239000000443 aerosol Substances 0.000 description 3
- 238000004891 communication Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- DDMOUSALMHHKOS-UHFFFAOYSA-N 1,2-dichloro-1,1,2,2-tetrafluoroethane Chemical compound FC(F)(Cl)C(F)(F)Cl DDMOUSALMHHKOS-UHFFFAOYSA-N 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 230000008020 evaporation Effects 0.000 description 2
- 238000001704 evaporation Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000003292 diminished effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000010771 distillate fuel oil Substances 0.000 description 1
- 239000004922 lacquer Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
Definitions
- This invention relates to supersonic gas streams.
- Objects of this invention are to make possible supersonic streaming with yet smaller nozzles and inlet pressures; to make possible in any event greater simplicity, flexibility, and efficiency; and, in preferred embodiments, to make possible effectively harnessing the energies of supersonic streams for efficient use without any need for cooperating tuned resonators and to make practical massing a plurality of such streams to cooperatively do work corresponding to the sum of their energies.
- the invention features use to obtain supersonic streaming of nozzles in each of which the effective throat diameter (D*) is less that half the nozzle forming throat diameter (D).
- the invention features use of a cylindrical inner surface, throat plane stabilization by injection under nozzle inlet pressure (P of four gas streams spaced 90 from one another with their axes in said plane, gas input at an unconfined nozzle inlet, gas implosion around said input and in consequence of it, and injection in the zone of the just-mentioned implosion of a liquid to be atomized.
- D is less than one-quarter inch
- D* is less than one-tenth inch
- the ratio of the distance from the inlet to the throat plane L* to the nozzle forming diameter D is in the range of from 0.9 to 1.5
- outlet Mach number (M is less than three
- gas is injected at an inlet pressure (P,) of from 0.1 to p.s.i.g., the volume (V) of gas injected at P, is from 0.2 to 50 cubic feet per minute (c.f.m.), and from four to one thousand nozzles are multiplexed for cooperatively doing work.
- the invention makes possible inexpensive manufacture of supersonic nozzles, relative freedom from supersonic breakdown owing to line pressure fluctuation, higher supersonic burst frequency (number of bursts of supersonic jets per minute; for more efficient atomization, for example, with more smaller bursts in relation to a given volume of liquid), and metering of conditions external to the nozzle (through letting such conditions participate in throat stabilization, to affect D*).
- FIG. 1 is a front elevation, partially broken away, of the most-preferred embodiment of the invention
- FIG. 2 is a side elevation, partially broken away, of said embodiment
- FIG. 3 is a sectional view, partially broken away, taken at 33 of FIG. 2;
- FIG. 4 is a sectional view, partially broken away, taken at 44 of FIG. 2;
- FIG. 5 is an isometric view of one of the four nozzles of said embodiment
- FIG. 6 is a vertical cross-sectional view taken through the longitudinal centerline of a modified nozzle according to the invention.
- FIG. 7 is a vertical cross-sectional view taken through the longitudinal centerline of another modification according to the invention.
- FIG. 8 is a vertical cross-sectional view taken through the longitudinal centerline of still another modification according to the invention.
- FIG. 9 is an end elevation of the nozzle of FIG. 8.
- FIGS. 1 through 4 an oil burner, in the preferred embodiment of the invention.
- Oil supply pipe 10 is mounted in oil manifold 12, through the forward wall of which extend eight oil delivery holes 14.
- the holes 14 are in four sets of two holes each.
- Air supply pipe 16 is mounted in a first air manifold 18, from which extends four nozzle feed tubes 20 and four second air manifold 22 feed tubes 24.
- Four nozzles 26 are mounted with inlets coplanar with the outlets of nozzle feed tubes 20, and have inside diameters great r than the outside diameters of the tubes 20, so that at annular zones 28 the interiors of nozzles 26 are in communication with the atmosphere.
- Each nozzle 26 includes four holes 30 with axes coplanar in a plane perpendicular to the nozzle axis and through which holes the second air manifold is in communication with the interiors of nozzles 26.
- oil under pressure passes through pipe 10 and manifold 12, and is discharged in eight streams through holes 14.
- air under pressure passes through pipe 16, manifold 18, and nozzle feed tubes 20 into the inlets of nozzles 26. Movement of the air through the inlet of the nozzle draws into the nozzle both atmospheric air and the oil emerging from the pairs of holes 14 respectively generally aligned with the zones 28 into nozzles 26 through the zones 28.
- the low air inlet pressure and the small nozzle diameter cooperate to produce a rapid buildup in boundary layer thickness downstream of each nozzle inlet, with a consequent rapid diminution of effective diameter for air streaming; i.e., in every practical respect, to form a converging nozzle portion sculptured in boundary layer.
- the boundary layer becomes, at about the plane in which lie the axes of holes 30, of such thickness that the effective diameter for air flow (flow occurs in the boundary layer too, of course, but much more slowly, and for purposes of calculating D*, the boundary layer may be treated as though motionless) is D*, the diameter at which effective air flow rate therethrough is such that the ratio of inlet pressure to throat plane pressure (P /P is that characteristic of transition from subsonic to supersonic flow; i.e., transonic.
- the diameter of the orifice through which air is introduced to each nozzle inlet (the inside diameter of each tube 20) is small (less than half the nozzle inlet inside diameter), the sensitivity of nozzle operation to variation in c.f.m. is further reduced.
- each nozzle 26 in the preferred embodiment is:
- Countersink 32 designed to smooth divergence of the boundary layer, is at 45 to the nozzle axis (90 included angle).
- Light fuel oil is introduced through holes 24 at the rate of 32 pounds per hour, at a presssure of p.s.i.g.; P is 6 p.s.i.g.; and under these conditions air c.f.m. is 1.2, D* is 0.065 inch, and the effective outlet diameter D of the nozzle (the boundary layer still being of sufficient thickness to leave an effective air flow opening of outlet diameter D.) is 0.100 inch.
- the vacuum produced at the outlet P is one p.s.i.a., and the speed of the jet emerging (M is Mach 2.6.
- Provision for subsonic implosion in the zone 28 is helpful both in creating the desired thickness of boundary layer with less use of for boundary layer creation, and consequent less waste of energy input from, the air injected into each nozzle; and in counteracting any tendency toward boundary layer separation.
- the amount of implosion is self-regulating, so that the sizes of zones 28 are not critical. It is essential in practicing my invention that boundary layer conditions be laminar, not turbulent.
- the oil After entering the nozzle, the oil is carried through it in the boundary layer, being moved therein, and distributed over the entire inner nozzle surface thereof, in a generally helical Way. Because P is subatmospheric, as the oil emerges from the nozzle it is sucked from the zones nearer the metal nozzle inside diameter into the supersonic jet, whereupon the atmospheric implosion thereinto does work on the oil to atomize it enormously and efficiently, whereupon it burns with unusual efficiency in the air with which it is by then well mixed.
- the primary determinant of effective nozzle shape is the boundary layer. While this layer has in the prior nozzle art been regarded only as an unavoidable evil, it is in the present invention the element which makes possible sophisticated function with elemental form. Boundary layer thickens, at subsonic fiow rates, at P and diameter drop. At supersonic flow rates, in a diverging nozzle, a thick boundary layer rapidly diminishes in thickness.
- thermodynamic One-Dimensional Isentropic Compressible Flow Functions tables permit picking off the ratio of effective nozzle outlet area (A,,) to effective throat area (A*) necessary to obtain the chosen P (The Mach number at the outlet, M may also be picked off such tables.) It is then necessary to select a length of nozzle that will, for the inside diameter concerned, provide for a boundary layer buildup from the inlet to the throat plane to there give about the effective throat diameter D* corresponding ot the now-fixed A, and for boundary layer decay from the throat plane to the outlet, to provide there the effective outlet area A now fixed.
- Boundary layer thickness under various conditions can of course be empirically determined, as by measurement with probes, as is well known, so that a suitable distance from inlet to throat plane may be fixed based on information as to boundary layer growth under particular conditions.
- P the same, boundary layer thickness as between two nozzles, at a corresponding position along their length, is greater in the one of smaller diameter, and this, if the larger diameter is no more than five times the smaller in ratio corresponding approximately to the ratio of the cubes of the two diameters.
- the throat plane stabilizer is provided at the distance from the inlet thus chosen.
- the length downstream of the throat plane is preferably the shortest possible, consistent with supersonic maximum divergence, a half-angle of about 45; and of course consistent too with retaining any remaining boundary layer needed, in a particular design, to maintain A at the proper level.
- I stabilize the location of D" primarily by means of air imploded from the atmosphere through four ports 40 spaced apart with axes coplanar, and secondarily by means of a sharp ring 42 extending into the nozzle.
- D remains the larger, general inside diameter of the nozzle, since the thickness of the ring 42, in a direction longitudinal of the nozzle, in relation to the diameter along which such thickness is measured, is less than 0.3 even at a diameter corresponding with the general, cylindrical inside diameter.
- Countersink 46 is at 30 to the nozzle axis. With P 6 p.s.i.g. and c.f.m. 1.2, this design provides D* of 0.065 inch, D of 0.110 inch, and M of 2.60.
- this nozzle too is disclosed for use in atomizing oil for burning, and injection of oil, as well as atmospheric subsonic inlet implosion, are just as in the first embodiment described.
- liquid to be atomized may be introduced, not at the inlet, but rather through the plane stabilization holes; and the liquid thus injected may itself be the plane stabilization fluid. It is then again transported to the nozzle outlet in the boundary layer, to be acted on as in the inlet introduction examples.
- liquid to be atomized can if desired be introduced near the supersonic jet without ever passing through any portion of the nozzle, and be drawn into it by the vacuum of the jet to be worked on and atomized, in the same way. If two liquids are to be brought together for quick reaction, one may be introduced in the last-mentioned manner, and the other in one of the other two.
- liquid is introduced, its quantity should of course be matched to the energy and nature of the supersonic jet, so that there will be neither liquid in such amount that its momentum overrides the supersonic implosion effect, nor in quantity insufficient to take advantage of the full supersonic jet energy content.
- I may also stabilize by means of a thin ring projecting into the nozzle alone.
- the nozzle forming throat diameter is simply the inside diameter of the cylindrical nozzle. Strictly speaking, I mean by D: to designate the innermost diameter, intermediate the nozzle inlet and outlet, at which the dimensions at that diameter in a lengthwise direction (L divided by the diameter (D is in excess of 0.3.)
- the innermost diameter of ring 60 is 0.165 inch, and the convergent half angle from the inlet to the ring 60 is 17.
- P, 6 p.s.i.g. and c.f.m. 1.2 this design provides D* of 0.065 inch, D. of 0.110 inch, and an M of 2.60
- D* adjustment to match c.f.m. variation in retaining supersonic function results mainly from inlet implosion rate variation (as it does too to some degree in the embodiments previously described), so that here inlet implosion is especially important.
- the FIG. 8 nozzle consists of two inexpensive parts, a housing 70 which is ordinary A inch standard copper tubing, and a copper inner member indicated generally at 72, which may be made inexpensively on a screw machine.
- the inner member 72 includes an upstream portion 74 which in cross-section outer outline is a circle from which two parallel fiat surfaces 76 remove segments of corresponding size.
- the surfaces 76 define with the inner surface of housing 70 passages 78 communicating with annular zone 80, which in turn communicates through the four holes 82 with the inside of inner member 72.
- conduit 88 Extending through hole 84 in housing 70 and seated in partially blind hole 86 in member 72 is conduit 88 from an aerosol can (not shown). Hole 86 is in communication through blind hole 90 with orifice 92, which is 0.016 inch in diameter (and concentric with D Within 0.001 inch). Other specific dimensions are:
- Countersing 94 is at 45 to the nozzle axis.
- the Freon 114 provides gas through orifice 92 to the nozzle at P, of 2.0 p.s.i.g., and a volume of 0.650 c.f.m. Under these conditions D* is 0.046 inch, D is 0.087 inch, and M is 2.40. Not only does zone provide for implosion through holes 82, but provides heat for transfer across ring-like portion 96 of the inner member 72, to evaporate any Freon remaining liquid, warm up Freon gas cooled by evaporation, and provide heat by conduction to the walls of holes 84, 90, and 92, to aid in evaporation.
- this nozzle produces not only a very fine spray, but one, unlike prior art aerosol sprays, that is not cool to the touch.
- My nozzle has the additional advantage that the Freons high density, interacting with air imploded downstream of the nozzle outlet, works to improve yet further atomization, unlike shear nozzles, in which its high density yields no particular advantage.
- a particular advantage of the invention is that, because resonators are no longer necessary, extensive multiplexing (i.e., placing the nozzle so close together that their outlet jets or resonators would interfere if resonators were 'used) is practical.
- a supersonic nozzle comprising a gas conduit with an inlet and an outlet and a throat plane stabilizer intermediate thereof, said nozzle being adapted to accept at said inlet a subsonic stream at a pressure P give said stream transonic speed at said plane, and discharge at said outlet a supersonic stream at a pressure P,, said conduit having a minimum forming diameter D at least twice the throat diameter D* characteristic of said P, with said P 2.
- said stabilizer comprises an even plurality of fluid inlets.
- nozzle of claim 9 in which a liquid delivery element is mounted to inject liquid to move into said zone.
- the method of producing a supersonic jet which comprises the steps of introducing a gas at subsonic velocity and low pressure into a nozzle of small diameter so that boundary layer rapidly thickens along the nozzle length to form in effect the converging portion of a converging-diverging nozzle, stabilizing the longitudinal position at which the boundary layer becomes of thickness great enough to leave a hole for effective gas movement of D adapted to provide P required by operating P, for transition to supersonic flow, decreasing the boundary layer downstream of said position through supersonic parabolic decay, and discharging the effectively moving stream from the nozzle when the boundary layer has diminished so that the effective outlet opening is in the proper ratio to D* for supersonic flow, D* being less than half D 13.
- the method of claim 12 in which gas is imploded at the inlet of said nozzle by virtue of the said introducing of the first-mentioned said gas.
- the nozzle of claim 1 which is multiplexed with from 3 to 999 other nozzles of claim 1. 10 239-102
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Description
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US71844768A | 1968-04-03 | 1968-04-03 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3531048A true US3531048A (en) | 1970-09-29 |
Family
ID=24886117
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US718447A Expired - Lifetime US3531048A (en) | 1968-04-03 | 1968-04-03 | Supersonic streaming |
Country Status (1)
Country | Link |
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US (1) | US3531048A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3668869A (en) * | 1971-01-28 | 1972-06-13 | Westinghouse Electric Corp | Fuel spray ignition atomizer nozzle |
US3750947A (en) * | 1971-09-02 | 1973-08-07 | Energy Sciences Inc | Atomizing nozzle assembly |
US5042461A (en) * | 1988-05-17 | 1991-08-27 | Sumitomo Bakelite Company Limited | Horn used in an ultrasonic surgical operating instrument |
US20090020621A1 (en) * | 2007-07-17 | 2009-01-22 | S.C. Johnson & Son, Inc. | Aerosol dispenser assembly haveing voc-free propellant and dispensing mechanism therefor |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3371869A (en) * | 1963-12-23 | 1968-03-05 | Sonic Dev Corp | Compressible fluid sonic pressure wave atomizing apparatus |
-
1968
- 1968-04-03 US US718447A patent/US3531048A/en not_active Expired - Lifetime
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3371869A (en) * | 1963-12-23 | 1968-03-05 | Sonic Dev Corp | Compressible fluid sonic pressure wave atomizing apparatus |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3668869A (en) * | 1971-01-28 | 1972-06-13 | Westinghouse Electric Corp | Fuel spray ignition atomizer nozzle |
US3750947A (en) * | 1971-09-02 | 1973-08-07 | Energy Sciences Inc | Atomizing nozzle assembly |
US5042461A (en) * | 1988-05-17 | 1991-08-27 | Sumitomo Bakelite Company Limited | Horn used in an ultrasonic surgical operating instrument |
US20090020621A1 (en) * | 2007-07-17 | 2009-01-22 | S.C. Johnson & Son, Inc. | Aerosol dispenser assembly haveing voc-free propellant and dispensing mechanism therefor |
US9242256B2 (en) * | 2007-07-17 | 2016-01-26 | S.C. Johnson & Son, Inc. | Aerosol dispenser assembly having VOC-free propellant and dispensing mechanism therefor |
US10427862B2 (en) | 2007-07-17 | 2019-10-01 | S.C. Johnson & Son, Inc. | Aerosol dispenser assembly having VOC-free propellant and dispensing mechanism therefor |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GREEN, NORMAN E., STATELESS Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:PARKER & HALE, A CA PARTNERSHIP;REEL/FRAME:004071/0640 Effective date: 19821112 Owner name: NATHANIEL HUGHES, STATELESS Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:PARKER & HALE, A CA PARTNERSHIP;REEL/FRAME:004071/0640 Effective date: 19821112 Owner name: GREEN, NORMAN E. Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:PARKER & HALE, A CA PARTNERSHIP;REEL/FRAME:004071/0640 Effective date: 19821112 Owner name: NATHANIEL HUGHES Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:PARKER & HALE, A CA PARTNERSHIP;REEL/FRAME:004071/0640 Effective date: 19821112 Owner name: VORTRAN CORPORATION, 315 SOUTH BEVERLY DRIVE, SUIT Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNORS:HUGHES, NATHANIEL;GREEN NORMAN E.;REEL/FRAME:004066/0868 Effective date: 19821116 |