US2325495A - Oil burner - Google Patents

Oil burner Download PDF

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Publication number
US2325495A
US2325495A US313525A US31352540A US2325495A US 2325495 A US2325495 A US 2325495A US 313525 A US313525 A US 313525A US 31352540 A US31352540 A US 31352540A US 2325495 A US2325495 A US 2325495A
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United States
Prior art keywords
oil
air
burner
chamber
tip
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Expired - Lifetime
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US313525A
Inventor
Ferguson William
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NAT AIROIL BURNER Co Inc
NATIONAL AIROIL BURNER COMPANY Inc
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NAT AIROIL BURNER Co Inc
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Application filed by NAT AIROIL BURNER Co Inc filed Critical NAT AIROIL BURNER Co Inc
Priority to US313525A priority Critical patent/US2325495A/en
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D11/00Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space

Description

July 27, 194.3 w. FERGUSON OIL BURNER Filed Jan. 12, 1940 ZZOPH@ Co/vawr/o/v SPACE v Patented July 27, 1943 OIL BURNER William Ferguson, Philadelphia, Pa., asslgnor to National Airoil Burner Company, Incorporated, a. corporation of Delaware rApplication January 12, 1940, Serial No. 313,525

2 Claims.

The invention relates to oil burners. 'I'he object is to provide an improved fuel oil burner device, and method of operation, which shall cover a wide range of oil pressures and which shall provide extremely simple and eiiicient means for projecting and atomizing the oil with such controls as shall produce complete combustion and which shall control the flame to required dimensions and which shall be free from clogging.

The invention also provides improved and eilicient method and means for controlling the distribution and pressures as required.

An important feature of the invention is that the necessary turbulence is secured without un due loss of initial pressure of the oil.

Referring to the drawing which illustrates merely by way of example, suitable means for effecting the invention.

Fig. 1 is a longitudinal section on line I-I, of Fig. 2.

Fig. 2 is a vertical cross-section on line 2-2' of Fig. 1.

Fig. 3 is a view in perspective of the tangential element.

Similar numerals refer to similar parts throughout the several views.

In the present example, as shown in the drawing, the oil pipe 1 is adapted to be connected with a'source of fuel oil under pressure. The outer or discharge end of this pipe 1 is exteriorly threaded as at 8. The burner tip 9 is conical in form and provided at its base with an annular flange III, interiorly threaded to receive the threaded end of pipe 1. This tip 9 is provided with an axial straight channel which is preferably provided with a flare at its discharge end. The body or formation I2 comprises a disc-like part I3 adapted to be positioned within the annular flange Ill of tip 9, and to be clamped between the end of pipe 1 and the opposite face of the tip member 9. This body I2 is provided with a part I4 of rectangular shape, centrally positioned on the inner face of the disc I3, and a cylindrical part or stem I5 extending from the inner face of part I4 and axially concentric with the disc I3. 'Ihis stem or cylindrical portion I5 serves as convenient means for handling the element I2, to facilitate the machine operation when making it upon the lathe. It also serves as convenient means for handling the element I2 for cleaning or replacing. It may also, in some cases, serve to distort in part, the lines of flow of oil.

It will be noted that the square or rectangular part I4 is so shaped and dimensioned as to leave spaces I6 between the corners of part I4 and the surrounding wall of pipe 1.

A centrally positioned chamber Il is provided in the disc I3 and the rectangular part I4. This chamber I 'l registers with, and delivers to the discharge channel II, but is of slightly greater cross-sectional diameter.

One or more tangential channels I8 are provided in the part I4 leading from space or spaces I6 to chamber Il.

An air pipe or sleeve I9, adapted to be connected with a source of air under pressure, surrounds the discharge end of oil pipe l and the burner tip 9, thereby forming an annular air passage 20. This air pipe I9 has a contracted or tapered discharge formation or nozzle end 2|, which cooperates with the tapered tip 9 for delivering the air in converging lines toward the axis of the channel I I. The nozzle 2I is relaively movable, in any suitable way, with respect to burner tip 9, so that the air discharge opening 22 may be adjusted to control said air delivery. For example, the air nozzle member I9 is shown as supported in telescoping relationship with the air pipe 23 leading froma source of air supply under pressure. By this means the nozzle end 2| is adapted adjustably to control as required the air passage 22.

The section of Wall 24, shown in section in Fig. 1, represents the wall of an enclosed combustion space as indicated.

In operation The oil, under required pressure, for example, from lbs. to 150 lbs., is delivered to the space,

or spaces I6, and thence through the tangentialchannel or channels I8 to the central chamber Il, which delivers to the discharge channel I I in burner tip 9.

The delivery of oil, under pressure, through the tangential channel or channels I8 to the chamber I'I, causes a. whirling or revolving motion of the oil in said chamber.

Where the discharge channel, such as II, through the tip 9, is of sufficient length and cross-section, this whirling of the oil is carried on, or continued, during the passage through its channel II and even after its discharge into the combustion space. This contributes to the atomization of the oil mixed with the air delivered by nozzle 2|. The resulting turbulence of the issuing oil facilitates the mixing of the air therewith, thus securing a much more effective combustion. 'I'he controlled pressure of the oil feed, and the adjusted delivery of the air through the nozzle 2|, renders the adjustment of the flame. as to shape and size, much more effective.

The relatively long passage in the burner tip, and its ample cross-sectional dimension add greatly to the emclency of the burner, because very little of the initial oil pressure is lost, in its passage from chamber Il to the combustion space. The relatively long passage Il, from the chamber I1 to the discharge end of the burner tip 9, protects the chamber I1 from undue heat, and prevents accumulations which tend to clog, and thus impair or interrupt satisfactory functioning.

The initial pressures of the oil which may be utilized. may have a wide range. For example I have operated the burner successfully with as little as ten pounds fuel oil pressure, or the pressure may be as high as three hundred torfour hundred pounds pressure. depending upon the size of the channels I8 and Il, for a given capacity.

It is believed that little atomization results from merely passing the fuel through the channels I8 and Il.

Itis rather believed that the fuel oil issues from channel II, either in a film or fairly large particles, preferably the former, and that this im is acted upon by the air delivered through nozzie 2 I, which completes the atomization.

In other words, it is believed that channel II.

may be considered more as a distributor, to supply the oil evenly to the column of air, and this is notwithstanding the fact. as I understand, that designers and vendors of competitive burners claim that atomization is completed in the burner tip, rather than as above described.

What I claim is:

1. In an oilburner. the combination, with an oil supply pipe and a burner tip having a relatively long passage. of an integral body having a disk-like part and a rectangular part. the disklike part being clamped between the oil pipe and the tip, the said body having a centrally disposed chamber delivering to the said elongated channel, and a passage delivering tangentially through the rectangular part to said chamber.

2. In an oil burner, the combination, with an oil supply pipe and a burner tip having an elongated channel, of an integral body having a disklike part, a, rectangular part, and a cylindrical part, of less diameter than that of the rectangular part, projecting axially from the rectangular part, the disklike part being clamped between the oi1 pipe and the tip, the said body having a. centrally disposed chamber delivering to the said elongated channel, and a. passage delivering tangentially through the rectangular part to said chamber.

WILLIAM FERGUSON.

US313525A 1940-01-12 1940-01-12 Oil burner Expired - Lifetime US2325495A (en)

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2453378A (en) * 1941-11-07 1948-11-09 Asiatic Petroleum Co Ltd Liquid-cooled nozzle arrangement for combustion chambers of jet propulsion apparatus
US2568240A (en) * 1947-05-26 1951-09-18 Marley Company Inc Spray nozzle
US2636778A (en) * 1948-08-27 1953-04-28 Michelsen Karl Apparatus for atomizing liquids
US2700416A (en) * 1949-06-30 1955-01-25 Rolls Royce Fuel injection means for gas-turbine engines and combustion equipment used therewith
US2730170A (en) * 1949-09-14 1956-01-10 Swift & Co Shielded soap spray nozzle
US2774629A (en) * 1950-09-08 1956-12-18 Thompson Prod Inc Variable area fuel nozzles
US2952619A (en) * 1957-01-11 1960-09-13 Exxon Research Engineering Co Feed injector for coking for chemicals
US3072343A (en) * 1961-04-19 1963-01-08 Zink Co John Atomizer for liquid fuel
US3215351A (en) * 1963-06-04 1965-11-02 Master Cons Inc Oil burner nozzle
US4621492A (en) * 1985-01-10 1986-11-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Low loss injector for liquid propellant rocket engines
US4664619A (en) * 1985-11-29 1987-05-12 Otis Engineering Corporation Burner nozzle
US4783008A (en) * 1986-06-09 1988-11-08 H. Ikeuchi & Co., Ltd. Atomizer nozzle assembly
EP0410562A1 (en) * 1989-05-09 1991-01-30 Halliburton Company Burner nozzle
US5058808A (en) * 1990-08-24 1991-10-22 Halliburton Company Burner nozzle
US5067657A (en) * 1989-11-01 1991-11-26 Halliburton Company Burner nozzle
US6551095B2 (en) * 1997-12-05 2003-04-22 Saint-Gobain Glass France Combustion process and fuel injection burner for implementing such a process
US20100112498A1 (en) * 2007-03-26 2010-05-06 Saint-Gobain Emballage Hollow jet injector for liquid fuel
US20130078597A1 (en) * 2010-06-09 2013-03-28 Chris Thorp Dental nozzle

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2453378A (en) * 1941-11-07 1948-11-09 Asiatic Petroleum Co Ltd Liquid-cooled nozzle arrangement for combustion chambers of jet propulsion apparatus
US2568240A (en) * 1947-05-26 1951-09-18 Marley Company Inc Spray nozzle
US2636778A (en) * 1948-08-27 1953-04-28 Michelsen Karl Apparatus for atomizing liquids
US2700416A (en) * 1949-06-30 1955-01-25 Rolls Royce Fuel injection means for gas-turbine engines and combustion equipment used therewith
US2730170A (en) * 1949-09-14 1956-01-10 Swift & Co Shielded soap spray nozzle
US2774629A (en) * 1950-09-08 1956-12-18 Thompson Prod Inc Variable area fuel nozzles
US2952619A (en) * 1957-01-11 1960-09-13 Exxon Research Engineering Co Feed injector for coking for chemicals
US3072343A (en) * 1961-04-19 1963-01-08 Zink Co John Atomizer for liquid fuel
US3215351A (en) * 1963-06-04 1965-11-02 Master Cons Inc Oil burner nozzle
US4621492A (en) * 1985-01-10 1986-11-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Low loss injector for liquid propellant rocket engines
US4664619A (en) * 1985-11-29 1987-05-12 Otis Engineering Corporation Burner nozzle
US4783008A (en) * 1986-06-09 1988-11-08 H. Ikeuchi & Co., Ltd. Atomizer nozzle assembly
EP0410562A1 (en) * 1989-05-09 1991-01-30 Halliburton Company Burner nozzle
US5044558A (en) * 1989-05-09 1991-09-03 Halliburton Company Burner nozzle with replaceable air jetting assembly
US5067657A (en) * 1989-11-01 1991-11-26 Halliburton Company Burner nozzle
US5058808A (en) * 1990-08-24 1991-10-22 Halliburton Company Burner nozzle
US6551095B2 (en) * 1997-12-05 2003-04-22 Saint-Gobain Glass France Combustion process and fuel injection burner for implementing such a process
US20100112498A1 (en) * 2007-03-26 2010-05-06 Saint-Gobain Emballage Hollow jet injector for liquid fuel
US20130078597A1 (en) * 2010-06-09 2013-03-28 Chris Thorp Dental nozzle
US9173725B2 (en) * 2010-06-09 2015-11-03 Astek Innovations Limited Dental nozzle

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