US3558056A - Streaming nozzle - Google Patents
Streaming nozzle Download PDFInfo
- Publication number
- US3558056A US3558056A US778200A US3558056DA US3558056A US 3558056 A US3558056 A US 3558056A US 778200 A US778200 A US 778200A US 3558056D A US3558056D A US 3558056DA US 3558056 A US3558056 A US 3558056A
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- US
- United States
- Prior art keywords
- zone
- nozzle
- nozzle device
- outlet end
- outlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
- F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
- F23D11/102—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
Definitions
- STREAMING NOZZLE This invention relates to streaming at supersonic speeds using small nozzles of the general character disclosed in the pending applications of Nathaniel Hughes, Ser. No. 7l8,447, filed Apr. 3, 1968, now Pat. No. 3,531,048 Supersonic Streaming;" and Ser. No. 734,089, filed Jun. 3, 1968, now US. Pat. No. 3,542,291, Streaming, in which effective nozzle surfaces within essentially cylindrical bores are defined by boundary layer eflects.
- Objects of the invention are to increase the intensity of the shock process at the outlet of such nozzles and, in preferred embodiments in jet aircraft engines, to increase fuel atomization.
- the invention features implosion at the nozzle outlet of a stream of compressible fluid flowing toward the outlet at greater than environmental pressure.
- the imploding stream fully surrounds the outlet, is confined by a shroud that extends toward the noule outlet to define a zone tapering toward the nozzle axis, and consists of a mixture of gas and liquid; and the imploding stream and all streams to the nozzle including those through throat plane stabilizer holes, are connected to a common source of liquidcarrying gas under pressure.
- FIG. 1 is a side view, mostly in section, of a portion of a jet aircraft engine embodying the invention
- FIG. 2 is an exploded isometric view thereof
- FIG. 3 is a sectional view through the longitudinal axis of the nozzle shown as a part of FIGS. 1 and 2;
- FIG. 4 is an end view, partially broken away, of the nozzle of FIG. 3.
- nozzle nut is screwed over fuel metering plate 12 and onto pedestal 14, which communicates with a fuel manifold (not shown) through passages 16 and I8.
- Passages l6 and 18 respectively feed fuel oil to annular recess 20 and bore 22 concentric therewith in pedestal 14.
- Four oblique fuel inlet holes 30 each 0.043 inch in diameter) equally spaced circumferentially in plate 12 communicate with recess 20 through enlarged passages 38 (two of which are shown in FIG. 1).
- Two fuel inlet holes 50 (each 0.02 inch in diameter) communicate through enlarged passages 54 with bore 22.
- nut 10 Forward of plate 12, nut 10 extends into combustion can 58 (a fragment of which is shown in FIG. 1) and defines mixing chamber 60, through the wall of which, outside can 58, extend air inlet holes 62.
- Nozzle 70 is welded in countersunk circular opening 72 in front wall 73 of nut 10 centrally of a ring of oblique exit'holes 74.
- annular shroud 76 extends out from nut 10 and bends around in front of holes 74 and then back in toward wall 73 and nozzle 70, defining a zone 78.
- Central inlet hole 82 extends through rear wall 80 of nozzle 70 and is concentric with an imaginary circle containing the centers of eight equally spaced smaller inlet holes 84 arranged in pairs, toward opposite ends of diameters of nozzle 70.
- Cylindrical boundary layer confining wall 88 has, toward its outlet, four radial throat stabilizing holes 90 (which together constitute a throat plane stabilizer), with coplanar axes spaced 90 from one another.
- the front of the nozzle is open to the interior of can 58, and includes 45 countersink 100.
- .IP-4 jet engine fuel is introduced through holes 30 and 50 into relatively large chamber 60 to mix with air entering through holes 62.
- the angular relationship of holes 30 causes the streams of fuel to hit one another, improving the mixing.
- the inlet air pressure is, e.g., 0.2 p.s.i.g., air flow is at a rate of 8 lbs./hr., and fuel flow is at a rate of lbs./hr.
- air flow is at a rate of 8 lbs./hr.
- fuel flow is at a rate of lbs./hr.
- These figures may increase respectively to 12 p.s.i.g., 200 lbs./hr., and 1,100 lbs./hr. during steady operation, after start-up.
- Part of the compressible air fuel mixture passes through inlet hole 82 into the nozzle defined by boundary layer confined within wall 88.
- Fluid mixture also moves outside wall 88 and through holes to stabilize the plane of the throat of the nozzle sculpted in boundary layer in the manner taught in the said patent applications.
- Another part of the mixture passes through holes 84 each of which is small enough to promote within its own confining cylindrical wall sufficient boundary layer growth to provide barely supersonic flow. (Flow within boundary layer confining wall 88 in said nozzle helps to speed up the flow through the holes 84 by increasing the pressure drop thereacross.)
- the characteristic burst frequencies of the main portion of said nozzle, and of the streams leaving holes 84, produce a superheterodyne effect, with resultant beats which may be measured, for example to monitor functioning.
- the included cone angle of the atomized stream is 70 during start-up and before ignition, and about at initial ignition, the doubling being attributable to the great intensity of heat owing to localization (through efficient atomization and mixing) of the zone of combustion.
- the ignited cone angle may be about 85.
- the preferred embodiment used in a jet aircraft engine as described, enables the efficient processing of large quantities of fuel even during engine start-up when air inlet pressure and flow rate are low. Smoking is reduced, and ignition is facilitated by wide cone angles.
- the diameter of hole 8 or the number of holes 84 can be increased to obtain even wider con angles. Holes 84 must always, however, be arranged in pairs along diameters of hole 82.
- Nozzle parameters are calculated in the manner set forth in said pending applications.
- the parameters are:
- Each hole 84 has a diameter and length of 0.032 inch.
- the centerlines of opposing pairs of holes 84 are 0.226 inch apart.
- a nozzle device comprising means to provide a supersonic jet through said nozzle, said means including:
- said stabilizer comprises an even plurality of orifices in said wall, said orifices being arranged in coaxial pairs 180 apart.
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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)
Abstract
Description
Claims (7)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US77820068A | 1968-11-22 | 1968-11-22 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3558056A true US3558056A (en) | 1971-01-26 |
Family
ID=25112588
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US778200A Expired - Lifetime US3558056A (en) | 1968-11-22 | 1968-11-22 | Streaming nozzle |
Country Status (1)
Country | Link |
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US (1) | US3558056A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3977604A (en) * | 1974-07-03 | 1976-08-31 | Taro Yokoyama | Fuel injection nozzle assembly |
US20160230999A1 (en) * | 2015-02-05 | 2016-08-11 | Mitsubishi Hitachi Power Systems, Ltd. | Atomizer and Combustion Device Using the Same |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1458378A (en) * | 1921-01-21 | 1923-06-12 | Mckneat Mfg Company | Oil burner |
US2217975A (en) * | 1937-09-04 | 1940-10-15 | Ward W Waisner | Liquid and gas mixing nozzle |
US2483951A (en) * | 1944-12-13 | 1949-10-04 | Lucas Ltd Joseph | Liquid fuel nozzle |
US3265313A (en) * | 1962-05-01 | 1966-08-09 | Secretariat De M Marsot | Device for mixing two fluid streams |
US3275239A (en) * | 1962-07-17 | 1966-09-27 | Kurt M Oesterle | Apparatus for the electrostatic precipitation of coating material |
US3334657A (en) * | 1963-10-28 | 1967-08-08 | Smith | Adjustable fluid mixing devices |
-
1968
- 1968-11-22 US US778200A patent/US3558056A/en not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1458378A (en) * | 1921-01-21 | 1923-06-12 | Mckneat Mfg Company | Oil burner |
US2217975A (en) * | 1937-09-04 | 1940-10-15 | Ward W Waisner | Liquid and gas mixing nozzle |
US2483951A (en) * | 1944-12-13 | 1949-10-04 | Lucas Ltd Joseph | Liquid fuel nozzle |
US3265313A (en) * | 1962-05-01 | 1966-08-09 | Secretariat De M Marsot | Device for mixing two fluid streams |
US3275239A (en) * | 1962-07-17 | 1966-09-27 | Kurt M Oesterle | Apparatus for the electrostatic precipitation of coating material |
US3334657A (en) * | 1963-10-28 | 1967-08-08 | Smith | Adjustable fluid mixing devices |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3977604A (en) * | 1974-07-03 | 1976-08-31 | Taro Yokoyama | Fuel injection nozzle assembly |
US20160230999A1 (en) * | 2015-02-05 | 2016-08-11 | Mitsubishi Hitachi Power Systems, Ltd. | Atomizer and Combustion Device Using the Same |
US10113746B2 (en) * | 2015-02-05 | 2018-10-30 | Mitsubishi Hitachi Power Systems, Ltd. | Atomizer and combustion device using the same |
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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 |