US3102393A - Combustion apparatus - Google Patents

Combustion apparatus Download PDF

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Publication number
US3102393A
US3102393A US37392A US3739260A US3102393A US 3102393 A US3102393 A US 3102393A US 37392 A US37392 A US 37392A US 3739260 A US3739260 A US 3739260A US 3102393 A US3102393 A US 3102393A
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United States
Prior art keywords
disc
fuel
wall
recess
combustion
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Expired - Lifetime
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US37392A
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English (en)
Inventor
Clare Harold
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Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means

Definitions

  • This invention relates to combustion apparatus for the continuous combustion of liquid fuel.
  • the invention is primarily concerned with combustion apparatus for gas turbine plant.
  • fuel is continuously supplied into a combustion chamber to which is fed a supply of compressed air, and the effluent, after combustion of the fuel, is expanded through a gas turbine.
  • Various means have been proposed for supplying the fuel into the combustion chamber and one of these consists of a fuel-distributing disc rotatably mounted in the chamber, and means for introducing liquid fuel on to the side face of the disc so that, on rotation thereof, fuel is thrown off the disc as a sheet of fuel.
  • the fuel sheet so produced is atomised by a high velocity air stream as it leaves the disc face.
  • Such an arrangement has advantages in continuous combustion plant, in particular gas turbine plant, in that the normal diffuser section of the combustion chamber can then be omitted which results in a reduction in the overall axial length of the plant.
  • combustion ap paratus comprises a rotatably mounted fuel-distributing disc and means for introducing liquid fuel onto a side face of the disc with a swirling motion about the axis of rotation of the disc.
  • the fuel may be swirled either in the direction of rotation of the disc or in the opposite sense.
  • the side face of the disc is formed with a coaxial recess having mounted therein a swirler, means being provided for introducing liquid fuel into the recess so that it flows through the swirler onto the face of the disc.
  • the junction between the radially outer wall of the recess and the side face of the disc may be formed as a weir with a smoothly curved surface.
  • FIGURE 1 is a part axial-section of a gas turbine com- Patented Sept. 3, 1963 ice bustion chamber, the final stage of an axial flow compressor and a part of a gas turbine together with the interconnecting shaft also being shown.
  • FIGURE 2 is an enlarged view of part of FIGURE 1.
  • FIGURE 3 is a cross-section of the view shown in FIGURE 2 taken along the line lI-I-III.
  • FIGURE 4 is a view in axial cross section of a modified form of part of the fuel disc shown in FIGURE 2.
  • FIGURE 5 is a section on the line V-V of FIG- URE 4.
  • FIGURE 1 shows part of a gas turbine plant which is generally similar to that described and illustrated in copending U.S. patent application Serial No. 828,085, Deacon et al., filed July 20, 1959, now Patent No. 3,020,718.
  • the plant comprises an axial flow compressor, an annular combustion chamber 2 and an axial flow turbine 3, the rotors of the compressor and turbine being mounted on a common two-part shaft 4.
  • the compressor is arranged to supply compressed air through an annular inlet duct 2a into the combustion chamber 2 from which combustion products discharge into the turbine 3, the rotor of which is thereby driven, and drives the rotor of compressor through the shaft 4.
  • the combustion zone of the combustion chamber 2 is defined externally by a flame tube outer wall 5 spaced from the outer casing wall 6 of the combustion chamber and forming therewith a coolant passage 7.
  • the combustion zone has a radially inner wall comprising two skins 8 and 9 spaced apart to provide a passage 10 for the flow of coolant fluid therebetween.
  • the upstream end wall of the combustion zone is formed by the downstream face of a fuel-distributing disc 11 which is mounted for rotation on the axis of the plant with its periphery lying adjacent to the air inlet to the combustion chamber, and the face extending transversely to the direction of air flow through the inlet.
  • the disc 11 is supported on a sleeve 12 which is mounted on the shaft 4 so as to rotate therewith in the sense indicated by the arrow A in FIGURE 3.
  • the face of disc 11 has formed therein a coaxial annular recess or trough 13, the radially outer wall of which has a face which is contiguous with the face of the disc 11, the junction between these two faces being formed as a weir by a. smoothly curved surface 13a.
  • the disc 11 and the sleeve 12 define within them an annular gallery 14 (see FIGURE 2), while clamped between them there is an annular swirler member 15.
  • the gallery communicates with the recess 13 by a series of ports 16 in the sleeve, an annular chamber 17 and a series of slots 15a in the swirler member, these slots being inclined to the radial direction as shown in FIG- URE 3.
  • the gallery 14 is provided with a series of circumferentially spaced vanes 18 disposed between ports 16.
  • the :fuel inlet to the combustion chamber is provided by a fuel pipe 20 which extends across the annular duct 2a and terminates in an annular gallery 21 which is defined between an annular channel member 22 and a partconical wall 23.
  • the wall 23 forms with a further partconical wall 24, a channel 25 which communicates with the gallery 21 by way of apertures 26 and with the annular gallery 14 by way of apertures 27.
  • the compressor 2 directs air under pressure through annular duct 2a substantially without diffusion and through flame stabilising means 30 (which may be of the type shown in either of the copending applications referred to), axially across the periphery of the disc into the combustion zone of combustion chamber 2.
  • Fuel passes through the fuel pipe 20 into the annular gallery 21 and into the annular channel 25 through the apertures 26. From the channel 25 the fuel passes through ports 27 into the gallery 14.
  • the disc is rotated at the speed of the shaft 4 and fuel trapped between vanes 18 is forced under centrifugal action at increased pressure through ports 16 and chamber 17 into the swirl slots 15a in member 15.
  • the inclined slots 15a impart to the fuel a radially outwands swirling motion in the same rotational sense as that of the disc 11.
  • the swirling fuel passes over the weir 13a, and on account of its swirling motion tends to adhere to [the face of the the disc 11 and accept the rotary motion thereof instead of being discharged axially into the combustion zone.
  • the rate of fuel supply is so related to the speed of rotation of the disc that the fuel is flung off the disc periphery as a coherent sheet (as opposed to an atomized spray) which is shattered by the flow of air into the combustion zone.
  • the required rotational component of motion may be imparted to the fuel in the manner described with reference to FIGURES 4 and 5 which show a part only of the fueldistributing disc 11 adjacent the recess 13 and weir 13a, the disc 11 in this case being integral with the supporting sleeve 12.
  • the fuel is supplied to the downstream side face of the disc by way of an annular gallery 31 to which it is led, as before, by an annular channel 25 and ports 27 disposed within the hub of the disc 11.
  • the peripheral wall of the gallery 31 is defined by an insert 32 in the fuel disc which carries a series of spaced vanes 33, the spaces bet-ween which communicate with a number of axially extending ducts 34 extending within the disc hub into the recess 13.
  • the ducts 34 communicate with a series of swirl channels 35a formed in the outer periphery of an annular member 35 secured to the disc within the recess. Between the member 35 and the weir 13a, the radially inwardly facing wall of the recess is formed with a shallow annular depression 36, for example, 0.02 inch in depth. As shown the channels 35a are inclined to the axial direction, and, for preference are made part helical.
  • the fuel is swirled in the direction of rotation of the disc 11.
  • the fuel may be caused to adhere to the disc by swirling it in the opposite sense to the direction or rotation, in which case the slots a or the channels 35a, as the case may be, will be inclined in the opposite sense to that shown in the drawings.
  • the flow path followed by the fuel across the disc face will be appreciably longer (possibly by a factor of 1.5) than the path followed by the fuel when swirled in the direction of rotation.
  • the rsidence time of the fuel on the disc face can be selected according to the degree of evaporation required from the disc face. This is important in keeping the running temperature of the disc down to an acceptable value.
  • the above-described embodiments of the invention incorporate the system of cooling the double walls, 8, 9 of the combustion chamber as described in patent application Serial No. 828,085, air being supplied to the passage 10 through conduit 28, and ports 29 in the sleeve 12.
  • the [fuel distributing disc itself is slightly coned to assist fuel distribution and carries paddles 19 to increase turbulence in the combustion zone.
  • the fuel supply system as described in the above example may be modified to accord with the arrangement disclosed in patnt application Serial No. 647,918 in which fuel is led to the disc by way of a fuel conduit provided within the hollow rotor shaft.
  • Combustion apparatus comprising an annular axially extending outer wall externally defining a combustion zone; a fuel-distributing disc mounted for rotation coaxially with respect to said wall at one end of the combustion zone, said disc having its periphery spaced inwardly from said wall :to define therewith a generally axially facing air inlet, and a side face extending generally transversely to the direction of fiow through said inlet and formed with a coaxial recess, the junction between the radially outer face of the recess and said side face being formed as a smoothly curved weir; a swirler mounted within said recess for rotation with the disc, said swirler being formed with helically-extending apertures inclined axially and means for supplying liquid fuel under pressure to flow through the swirler into the recess and over the weir on to the face of the disc at such a rate in relation to the speed of rotation of the disc that the fuel is thrown off the periphery of the disc across the inlet as a sheet of fuel.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
US37392A 1959-06-23 1960-06-20 Combustion apparatus Expired - Lifetime US3102393A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB21449/59A GB931105A (en) 1959-06-23 1959-06-23 Improvements in combustion apparatus

Publications (1)

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US3102393A true US3102393A (en) 1963-09-03

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ID=10163135

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Application Number Title Priority Date Filing Date
US37392A Expired - Lifetime US3102393A (en) 1959-06-23 1960-06-20 Combustion apparatus

Country Status (5)

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US (1) US3102393A (it)
CH (1) CH389995A (it)
DE (1) DE1162135B (it)
GB (1) GB931105A (it)
NL (1) NL252966A (it)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4038815A (en) * 1973-03-30 1977-08-02 Northern Research And Engineering Corporation Gas turbine
US4255935A (en) * 1978-03-20 1981-03-17 Toyoto Jidosha Kogyo Kabushiki Kaisha Liquid atomizing device
US4257236A (en) * 1978-10-30 1981-03-24 Toyota Jidosha Kogyo Kabushiki Kaisha Liquid atomizing device
US20050076650A1 (en) * 2003-10-08 2005-04-14 Rodolphe Dudebout Auxiliary power unit having a rotary fuel slinger
US20080171294A1 (en) * 2007-01-16 2008-07-17 Honeywell International, Inc. Combustion systems with rotary fuel slingers

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1626040B1 (de) * 1968-03-02 1971-06-24 Lucas Industries Ltd Ringbrennkammer für Gasturbinentiebwerke
US5042256A (en) * 1986-07-28 1991-08-27 Teledyne Industries, Inc. Turbine shaft fuel pump

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1418444A (en) * 1919-09-25 1922-06-06 Jr Lyman C Josephs Internal-combustion turbine
US1672064A (en) * 1926-12-09 1928-06-05 Holland W Claude Hydrocarbon burner
GB378309A (en) * 1931-01-08 1932-08-11 Hugo Junkers Improvements in and relating to oil fuel burners
US2280638A (en) * 1940-09-18 1942-04-21 York Oil Burner Co Inc Burner apparatus
US2547959A (en) * 1948-01-27 1951-04-10 Westinghouse Electric Corp Centrifugal fuel feeding system for annular combustion chambers
US2705401A (en) * 1950-12-02 1955-04-05 Armstrong Siddeley Motors Ltd Vaporising means for liquid fuel combustion chambers
US2938345A (en) * 1954-07-27 1960-05-31 Bendix Aviat Corp Combustion fuel atomizer
US2981066A (en) * 1956-04-12 1961-04-25 Elmer G Johnson Turbo machine
US3020718A (en) * 1958-07-31 1962-02-13 Power Jets Res & Dev Ltd Combustion chamber for a gas turbine power plant provided with a rotating fuel atomizer and a flame stabilizing inlet structure

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB686350A (en) * 1950-12-02 1953-01-21 Armstrong Siddeley Motors Limt Liquid fuel combustion chambers

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1418444A (en) * 1919-09-25 1922-06-06 Jr Lyman C Josephs Internal-combustion turbine
US1672064A (en) * 1926-12-09 1928-06-05 Holland W Claude Hydrocarbon burner
GB378309A (en) * 1931-01-08 1932-08-11 Hugo Junkers Improvements in and relating to oil fuel burners
US2280638A (en) * 1940-09-18 1942-04-21 York Oil Burner Co Inc Burner apparatus
US2547959A (en) * 1948-01-27 1951-04-10 Westinghouse Electric Corp Centrifugal fuel feeding system for annular combustion chambers
US2705401A (en) * 1950-12-02 1955-04-05 Armstrong Siddeley Motors Ltd Vaporising means for liquid fuel combustion chambers
US2938345A (en) * 1954-07-27 1960-05-31 Bendix Aviat Corp Combustion fuel atomizer
US2981066A (en) * 1956-04-12 1961-04-25 Elmer G Johnson Turbo machine
US3020718A (en) * 1958-07-31 1962-02-13 Power Jets Res & Dev Ltd Combustion chamber for a gas turbine power plant provided with a rotating fuel atomizer and a flame stabilizing inlet structure

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4038815A (en) * 1973-03-30 1977-08-02 Northern Research And Engineering Corporation Gas turbine
US4255935A (en) * 1978-03-20 1981-03-17 Toyoto Jidosha Kogyo Kabushiki Kaisha Liquid atomizing device
US4257236A (en) * 1978-10-30 1981-03-24 Toyota Jidosha Kogyo Kabushiki Kaisha Liquid atomizing device
US20050076650A1 (en) * 2003-10-08 2005-04-14 Rodolphe Dudebout Auxiliary power unit having a rotary fuel slinger
US7036321B2 (en) 2003-10-08 2006-05-02 Honeywell International, Inc. Auxiliary power unit having a rotary fuel slinger
US20080171294A1 (en) * 2007-01-16 2008-07-17 Honeywell International, Inc. Combustion systems with rotary fuel slingers
US7762072B2 (en) 2007-01-16 2010-07-27 Honeywell International Inc. Combustion systems with rotary fuel slingers
EP1947387A3 (en) * 2007-01-16 2012-06-27 Honeywell International Inc. Combustion systems with rotary fuel slingers

Also Published As

Publication number Publication date
CH389995A (de) 1965-03-31
NL252966A (it)
DE1162135B (de) 1964-01-30
GB931105A (en) 1963-07-10

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