US2825398A - Liquid fuel injection nozzles - Google Patents

Liquid fuel injection nozzles Download PDF

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Publication number
US2825398A
US2825398A US353777A US35377753A US2825398A US 2825398 A US2825398 A US 2825398A US 353777 A US353777 A US 353777A US 35377753 A US35377753 A US 35377753A US 2825398 A US2825398 A US 2825398A
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Prior art keywords
nozzle
annular
fuel injection
liquid fuel
air
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US353777A
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Clarke John Stanley
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ZF International UK Ltd
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Lucas Industries Ltd
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Priority to US353777A priority Critical patent/US2825398A/en
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    • 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
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • 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
    • F23D11/106—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 at the burner outlet
    • F23D11/107—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 at the burner outlet at least one of both being subjected to a swirling motion

Definitions

  • LIQUID FUEL INJECTION NOZZLES Filed May 8, 1953 United rates Patent 6 LIQUID FUEL INJECTION NOZZLES John Stanley Clarke, Blacko, near Nelson, England, assignor to Joseph Lucas (Industries) Limited, Birmingham, England Application May 8, 1953, Serial No. 353,777 1 Claim. (Cl. 158-76)
  • This invention relates to liquid fuel injection nozzles of the swirl-type for use in the combustion chambers of jet engines, gas turbines or other like purposes.
  • the present invention has for its object to enable the two air streams to perform their purpose in a more effective manner than heretofore.
  • the invention comprises a nozzle having combined with its outer end a pair of air passages both of which are fed from a common annular passage around the nozzle, one of the passages being adapted to direct an air stream inwards across the nozzle and the other being formed by an annular arrangement of slots which are open at both sides and are adapted to impart a rotary motion to the air stream passing therethrough.
  • Figure l is a sectional side elevation and Figure 2 an end elevation of a nozzle embodying the invention.
  • Figure 3 is a sectional view illustrating diagrammatically the slots forming one of the air passages.
  • Figure 4 is a part sectional side elevation and Figure 5 an end view illustrating a modification of the nozzle shown in Figure 1.
  • annular air passage b adapted to receive air from the air stream normally flowing over the nozzle, this passage being formed by a sleeve c placed over the nozzle.
  • the front end of the sleeve is of annular form and extends across a part of the front end of the nozzle, the said end of the sleeve being spaced from the nozzle to provide a passage d through which an air stream from the annular passage b can flow inwards towards the fuel delivery orifice of the nozzle. Also in the said end of the sleeve Patented Mar.
  • slots 1 which are open at each side and are situated opposite or adjacent to the said annular air passage b.
  • the slots are shaped and disposed as shown in Figure 3 so that they can impart a rotary motion to the stream passing through the slots. Further the slots may be radially disposed or, alternatively (and as shown in Figure 2) they may be so inclined that they can impart an additional radiallyinward component of motion to the stream passing through them.
  • the front end of the sleeve 0 is made of annular and truncated conical form. Otherwise it is essentially similar to the construction shown in Figures 1-3.
  • this comprises a pair of coaxial swirl chambers h, i fed by separate fuel pipes j, k, but as the details of construction form no part of the present invention no further description is necessary. Moreover, the invention is not limited to a nozzle of the particular construction shown in Figure 1.
  • a liquid fuel injection assembly comprising a body defining a nozzle having a discharge end, said discharge end including a substantially planar face, a sleeve mounted on and surrounding the body for at least a. portion of its length and including the discharge end, with said sleeve being spaced from the perimeter of the body to provide an annular air passage between the said sleeve and the body, an inwardly directed annular end on the sleeve extending across a part of said planar face of the body in closely spaced relationship to said discharge end to define a passage substantially perpendicular to the annular air passage to allow air to flow inwardly from the annular air passage toward the discharge end of the said body, the annular end of the sleeve defining the end of the injection assembly said annular end of the sleeve being provided with a plurality of slots open at both sides, with a portion of said slots facing the annular passage and being shaped to impart rotary motion to air passing therethrough from the annular passage with the air emanating

Description

March 4, 1958 J. s. CLARKE 2,825,398
LIQUID FUEL INJECTION NOZZLES Filed May 8, 1953 United rates Patent 6 LIQUID FUEL INJECTION NOZZLES John Stanley Clarke, Blacko, near Nelson, England, assignor to Joseph Lucas (Industries) Limited, Birmingham, England Application May 8, 1953, Serial No. 353,777 1 Claim. (Cl. 158-76) This invention relates to liquid fuel injection nozzles of the swirl-type for use in the combustion chambers of jet engines, gas turbines or other like purposes.
To minimise soot formation on the discharge end of the nozzle, it is already known to provide on the said end a pair of air passages whereby one stream of air can be directed inwards towards the emerging fuel, and another adjacent stream has imparted to it a swirling motion.
The present invention has for its object to enable the two air streams to perform their purpose in a more effective manner than heretofore.
The invention comprises a nozzle having combined with its outer end a pair of air passages both of which are fed from a common annular passage around the nozzle, one of the passages being adapted to direct an air stream inwards across the nozzle and the other being formed by an annular arrangement of slots which are open at both sides and are adapted to impart a rotary motion to the air stream passing therethrough.
In the accompanying drawings:
Figure l is a sectional side elevation and Figure 2 an end elevation of a nozzle embodying the invention.
Figure 3 is a sectional view illustrating diagrammatically the slots forming one of the air passages.
Figure 4 is a part sectional side elevation and Figure 5 an end view illustrating a modification of the nozzle shown in Figure 1.
Referring to Figures 1-3, there is formed around the exterior of the main part a of the nozzle an annular air passage b adapted to receive air from the air stream normally flowing over the nozzle, this passage being formed by a sleeve c placed over the nozzle. The front end of the sleeve is of annular form and extends across a part of the front end of the nozzle, the said end of the sleeve being spaced from the nozzle to provide a passage d through which an air stream from the annular passage b can flow inwards towards the fuel delivery orifice of the nozzle. Also in the said end of the sleeve Patented Mar. 4, 1958 is formed an annular arrangement of slots 1 which are open at each side and are situated opposite or adjacent to the said annular air passage b. The slots are shaped and disposed as shown in Figure 3 so that they can impart a rotary motion to the stream passing through the slots. Further the slots may be radially disposed or, alternatively (and as shown in Figure 2) they may be so inclined that they can impart an additional radiallyinward component of motion to the stream passing through them.
In the modified construction shown in Figures 4 and 5, the front end of the sleeve 0 is made of annular and truncated conical form. Otherwise it is essentially similar to the construction shown in Figures 1-3.
As regards the example of the nozzle a shown in Figure 1, this comprises a pair of coaxial swirl chambers h, i fed by separate fuel pipes j, k, but as the details of construction form no part of the present invention no further description is necessary. Moreover, the invention is not limited to a nozzle of the particular construction shown in Figure 1.
Having thus described my invention what I claim as new and desire to secure by Letters Patent is:
A liquid fuel injection assembly comprising a body defining a nozzle having a discharge end, said discharge end including a substantially planar face, a sleeve mounted on and surrounding the body for at least a. portion of its length and including the discharge end, with said sleeve being spaced from the perimeter of the body to provide an annular air passage between the said sleeve and the body, an inwardly directed annular end on the sleeve extending across a part of said planar face of the body in closely spaced relationship to said discharge end to define a passage substantially perpendicular to the annular air passage to allow air to flow inwardly from the annular air passage toward the discharge end of the said body, the annular end of the sleeve defining the end of the injection assembly said annular end of the sleeve being provided with a plurality of slots open at both sides, with a portion of said slots facing the annular passage and being shaped to impart rotary motion to air passing therethrough from the annular passage with the air emanating from the slots minimizing soot formation on the outer surface of the inwardly directed annular end of the sleeve.
References Cited in the file of this patent UNITED STATES PATENTS 1,526,429 Morse Feb. 17, 1925 1,719,090 Stillman July 2, 1929 2,325,893 Vollmer Aug. 3, 1943 2,414,442 Breault Jan. 21, 1947 2,603,280 Bernhard July 15, 1952
US353777A 1953-05-08 1953-05-08 Liquid fuel injection nozzles Expired - Lifetime US2825398A (en)

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935848A (en) * 1955-02-09 1960-05-10 Louis S Billman Fuel injection system for ramjet aircraft
US2959003A (en) * 1957-06-20 1960-11-08 Rolls Royce Fuel burner
US3090420A (en) * 1960-01-20 1963-05-21 Sacco Ernesto Burner for liquid fuels
US3139724A (en) * 1958-12-29 1964-07-07 Gen Electric Dual fuel combustion system
US3630024A (en) * 1970-02-02 1971-12-28 Gen Electric Air swirler for gas turbine combustor
US4863105A (en) * 1985-02-13 1989-09-05 Westinghouse Electric Corp. High reliability fuel oil nozzle for a gas turbine
US20130199191A1 (en) * 2011-06-10 2013-08-08 Matthew D. Tyler Fuel injector with increased feed area
US20130323660A1 (en) * 2012-06-05 2013-12-05 Riello S.P.A. COMBUSTION HEAD FOR A LOW NOx LIQUID FUEL BURNER

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1526429A (en) * 1922-08-22 1925-02-17 Albert W Morse Liquid-fuel burner
US1719090A (en) * 1925-11-21 1929-07-02 Babcock & Wilcox Co Oil burner
US2325893A (en) * 1941-02-14 1943-08-03 Lennox Furnace Company Liquid fuel burner
US2414442A (en) * 1944-02-03 1947-01-21 Delphis C Breault Burner construction
US2603280A (en) * 1952-07-15 Bernhard

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2603280A (en) * 1952-07-15 Bernhard
US1526429A (en) * 1922-08-22 1925-02-17 Albert W Morse Liquid-fuel burner
US1719090A (en) * 1925-11-21 1929-07-02 Babcock & Wilcox Co Oil burner
US2325893A (en) * 1941-02-14 1943-08-03 Lennox Furnace Company Liquid fuel burner
US2414442A (en) * 1944-02-03 1947-01-21 Delphis C Breault Burner construction

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935848A (en) * 1955-02-09 1960-05-10 Louis S Billman Fuel injection system for ramjet aircraft
US2959003A (en) * 1957-06-20 1960-11-08 Rolls Royce Fuel burner
US3139724A (en) * 1958-12-29 1964-07-07 Gen Electric Dual fuel combustion system
US3090420A (en) * 1960-01-20 1963-05-21 Sacco Ernesto Burner for liquid fuels
US3630024A (en) * 1970-02-02 1971-12-28 Gen Electric Air swirler for gas turbine combustor
US4863105A (en) * 1985-02-13 1989-09-05 Westinghouse Electric Corp. High reliability fuel oil nozzle for a gas turbine
US20130199191A1 (en) * 2011-06-10 2013-08-08 Matthew D. Tyler Fuel injector with increased feed area
US20130323660A1 (en) * 2012-06-05 2013-12-05 Riello S.P.A. COMBUSTION HEAD FOR A LOW NOx LIQUID FUEL BURNER

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