US2765621A - Combustion apparatus with toroidal eddy flame stabilizer - Google Patents

Combustion apparatus with toroidal eddy flame stabilizer Download PDF

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Publication number
US2765621A
US2765621A US404635A US40463554A US2765621A US 2765621 A US2765621 A US 2765621A US 404635 A US404635 A US 404635A US 40463554 A US40463554 A US 40463554A US 2765621 A US2765621 A US 2765621A
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United States
Prior art keywords
shrouds
combustion chamber
air
burner
combustion
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Expired - Lifetime
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US404635A
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English (en)
Inventor
Poulston Bernard Vincent
Shepheard Edmund Richard
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Shell Development Co
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Shell Development Co
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C99/00—Subject-matter not provided for in other groups of this subclass
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2700/00—Special arrangements for combustion apparatus using fluent fuel
    • F23C2700/02—Combustion apparatus using liquid fuel
    • F23C2700/023—Combustion apparatus using liquid fuel without pre-vaporising means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability

Definitions

  • This invention relates to apparatus for the combustion of fluent fuel, e. g., gaseous, liquid or finely divided solid fuels, in which the fuel is injected into a stream of air (or other combustion-supporting gas hereinafter referred to as air for the sake of brevity) and is particularly but not exclusively suitable for gas turbine combustion chambers.
  • fluent fuel e. g., gaseous, liquid or finely divided solid fuels
  • air or other combustion-supporting gas hereinafter referred to as air for the sake of brevity
  • a further object is to provide an improved combustion apparatus wherein the life of the combustion chamber wall is extended and/or wherein a thinner refractory lining may be used for such wall or, in some cases, omitted, by reducing the tendency of the flame to spread out and play against the wall.
  • apparatus for the combustion of gaseous, liquid or finely divided solid fuel comprises a combustion chamber (also known as a flame tube) having operatively associated therewith a burner or the like (also known as an atomizer in the case of liquid fuels) which delivers fuel into the combustion chamber in which air guide means are provided for causing two or more series of successive toroidal eddies to be formed in the main air stream substantially at the zone where this air stream meets the fuel issuing from the burner, and to travel longitudinally through the combustion chamber.
  • a combustion chamber also known as a flame tube
  • burner or the like also known as an atomizer in the case of liquid fuels
  • Preferably more than two series of successive substantially concentric toroidal eddies are formed at a number of positions around the axis of the burner and each travels along the combustion chamber; again preferably, in the case of finely divided liquid or solid fuel, such toroidal eddies are generated along the surface of a cone similar to the cone containing the spray of atomized fuel and coaxial therewith.
  • the main air stream means the preponderant proportion, at least 80%, of the air supporting combustion and does not include the auxiliary air stream which is sometimes but not always present immediately surrounding the burner and has for its object the prevention of a deposit .of combustion products on the burner tip.
  • a plurality of concentric shrouds are preferably employed, each of which is provided with an outwardly projecting or external lip which restricts the air flow in the space between any two shrouds and thereby produces a series of successive toroidal eddies.
  • the shrouds are also provided with inwardly projecting or internal lips; a preferred arrangement is that in which alternate shrouds only are provided with internal lips.
  • the arrangement is preferably such that the shroud of smallest radius terminates in a lipped edge only a short axial distance beyond the end of the burner, whereas the outermost shroud with the largest radius has its lipped edge in a plane at a greater axial distance from the end of the burner.
  • Intermediate shrouds are arranged with their ends in planes at intermediate distances from the end of the burner.
  • combustion apparatus of the present invention it is possible to secure flame stabilization, that is to say mixing of the fuel with sufficient air for its combustion, by producing turbulence without steady tangential or radial flow components in the turbulent air.
  • flame stabilization that is to say mixing of the fuel with sufficient air for its combustion
  • This tendency to spread outwards is always marked in combustion apparatus where the combustion air has a tangential or radial component of flow.
  • the walls of the flame tube or combustion chamber are, to a large extent, protected from overheating and hence have a longer life.
  • the protective lining of refractory material used in many combustion chambers may be omitted when using the apparatus of the present invention.
  • a further advantage of combustion apparatus according to the present invention is that the air pressure drop involved in feed-ing the air to the combustion chamber or flame tube is substantially reduced in comparison with known types of combustion apparatus in which turbulence is imparted to the air by a swirling motion or by air streams injected into the combustion chamber at an angle to the longitudinal axis thereof.
  • Figure 1 is a diagrammatic longitudinal section of a preferred type of combustion apparatus according to the present invention, which is suitable for use with a gas turbine;
  • Figure '2 is a similar section of a modified arrangement
  • Figure 3 is cross section on the line 3'3 of Figure 2.
  • the combustion chamber or flame tube C shown in Figure l is of circular cross ssction and is of a known type of construction having an air inlet opening G for the admission of a primary air stream for supporting combustion of the fuel, said primary air being supplied, for example, from a blower (not shown) and flows longitu dinally through the combustion chamber.
  • a secondary air stream flows through an annular space between the chamber and an air casing D and is admitted into the combustion chamber through openings E to dilute the resulting combustion products.
  • the subsequent descriptron is concerned with the primary air stream.
  • a burner B Mounted concentrically within the com-bustion chamber C and arranged to inject atomized liquid fuel in the axial direction thereof is a burner B.
  • the function and construction of this burner does not form any part of the present invention; hence, any known burner may be employed.
  • the burner is advantageously an atomizer that emits atomized fuel as a spray cone S.
  • this burner B Closely surrounding this burner B is a concentric atomizer shroud A of known type, i. e., tubular-in form, open at front and back and having an inward flange F at the front.
  • the clearance between the outer wall of the burner B and the inner wall of this atomizer shroud A is about equal to the radius of the burner body.
  • the function of this atomizer shroud A is to define the auxiliary combustion air stream referred to above.
  • Concentric shrouds 4, 5, 6, 7 and 8 are disposed around the burner B outside the atomizer shroud A, each one of which is spaced from its neighbours by an equal distance (a distance which is advantageously between the radius and diameter of the burner body).
  • shrouds terminate in planes which are disposed downstream from the end of the burner by progressively increasing axial distances.
  • the number of shrouds is such as substantially to fill the cross-sectional area of the combustion chamber and need not be five as shown, but may be varied accord-Eng to the distance between neighbouring shrouds and the diameter of the combustion chamber.
  • the main air stream as defined above flows into the combustion chamber through the annular spaces between the shrouds.
  • the shrouds 4 to 8, inclusive are provided at their forward or downstream parts with external lips 45:, 5a, 6a, 7a and 8a, respectively, which project partly across the space between each shroud and its neighbor, or in the case of the largest shroud 8, between that shroud and the wall of the combustion chamber C.
  • shrouds 6 and 8 have internal lips 6b and 8b, respectively.
  • Each external lip extends substantially halfway across the corresponding space; however, a wider lip may be used as shown for example for the lip 7a, whereby the air emerging between this lip and the shroud 8 is directed wholly against the lip 8b for inward deflection.
  • the internal lips 6b and 812 project inwardly to about the same extent that the lips 6a and 8a project outwardly.
  • the shrouds 5 to 8 are supported in any known manner, for example by means of a cruciform bracing 9 placed across the combustion chamber C behind the shrouds. Since it is desirable to reduce the size of such supporting means to the minimum, in order to reduce interference with the air flow, it is desirable to reduce the axial length of the shrouds as much as possible, so that there is the minimum load on the supporting means.
  • the combustion air stream enters the combustion chamher through the inlet G substantially without rotation about the longitudinal axis of the combustion chamber.
  • straightening vanes may be provided either in the approach ducts or even within the combustion chamber, e. g., as radial vanes on the shrouds; such straightening vanes being well known, per se, they are not further described herein.
  • the air flowing through the spaces between the shrouds has its direction of flow changed by the lips of the various shrouds and each lip produces in the combustion chamber a series of successive toroidal eddies which are arranged, when generated, substantially along the surface of a cone similar to, and coaxial with, the fuel spray cone S, which eddies subsequently travel forwardly, longitudinally through the combustion chamber.
  • These eddies resemble smoke rings in general way and travel as entities.
  • Within each. torus the fluids travel with ring-like movements in directions that are influenced by the direction of the lip.
  • the flame is thereby stabilized without, however, recourse to centrifugal or radial movements that would impinge the flame against the combustion chamber wall.
  • the combustion products after dilution by secondary air admitted through the openings E, continue through the part C of the combustion chamber, which has the usual outlet (not shown) which may be connected to a gas turbine or other device.
  • the concentric shrouds may be arranged so that they can be axially displaced in relation to one another and can thus provide toroidal eddies along the surface of fuel spray cones having different cone angles.
  • the concentric shrouds may be given a slightly frusto-conical, forwardly divergent form so that relative axial movement of the shrouds in relation to each other provides a means for controlling the amount of air supplied to the combustion chamber as well as providing the succession of toroidal eddies.
  • concentric shrouds need not be arranged to produce toroidal eddies over substantially the entire cross-section of the combustion chamber as indicated above, but only a part thereof, for example two or more series of successive toroidal eddies near the combustion chamber wall, or again, closely adjacent to the burner.
  • the planes in which the concentric shrouds terminate, downstream from the burner may be regularly or irregularly spaced from each other to conform to the characteristics of the fuel spray.
  • radial distance between the shrouds may be varied, and the projection of the external and/or internal lips into the intershroud space may also be varied from that stated.
  • the clearance between the burner and the atomizer shroud may also be varied to produce the most suitable air velocity for controlling the spray.
  • double-lipped and single-lipped shrouds are not essential; there may be, for example, pairs of double-lipped shrouds alternating with single-lipped shrouds.
  • burner and shrouds need not be coaxial with the combustion chamber; thus one or more burners may be located between the shrouds, with or without the central burner.
  • This arrangement is particularly suitable for gas fuel and is shown in Figures 2 and 3.
  • FIG. 2 there is shown a combustion chamber that may be provided with an air casing as shown in Figure 1, having four gas burners 11 supported by a support ring 12 and arranged symmetrically about the longitudinal axis of the chamber.
  • An igniting device 13 is arranged substantially centrally of these burners, and concentric with this device 13 are arranged shrouds 14, 15, 16, 17, 18, 19, 20, 21 and 22 having radial lips at their forward or downstream ends;
  • shrouds 14, 16 and 17 have internal lips only
  • shrouds 18, 19 and 21 have external lips only
  • shrouds 15, 20, and 22 have both internal and external lips. It is thus seen that all shrouds have lips extending away from the burners while the last three enumerated shrouds additionally have lips toward the burners.
  • shrouds 17 and i8 terminate in a plane nearest the burners and the other shrouds, situated progressively farther from the burners, terminate in planes that are axially progressively farther forward.
  • the several shrouds, plate 12 and and the igniter 13 are mounted on a cruciform support including radial members 12a.
  • Air holes 23 are provided in the ring 12 in order to admit as much air as possible to the combustion chamber.
  • Another alternative is to have two or more burners, each with associated concentric shrouds arranged in one combustion chamber.
  • a certain deviation from concentricity of the shrouds can be tolerated according to the air flow and fuel spray characteristics.
  • shrouds 58 and 14-22 terminating in one plane at their ends remote from their lips; this means that the outermost shrouds 8 and 22 are the longest ones in the axial direction; such shrouds can conveniently be supported by a single frame or spider situated behind the burner as indicated above.
  • the shroud length may be reduced to such an extent that the axially overlapping shroud portions are only about five or less times as long as the radial distance across the gap between a given shroud and the associated lip of the next innermost shroud.
  • the length of the shroud is reduced greatly, e. g., so that the axial overlap vanishes, the lips become less effective.
  • Such extremely short shrouds, as well as the omission of the tubular shrouds and the use of merely a series of rings, while included in the broadest aspect of the invention, are not preferred.
  • toroidal eddyproducing means of the present invention may be constructed as a separate assembly for fitting to existing combustion chambers.
  • Apparatus for combustion of fluent fuel comprising a combustion chamber having an air inlet at one end thereof for the admission of a combustion air stream, a fuel burner which delivers fuel into said air stream within the combustion chamber, and a plurality of generally annular air deflectors of progressively different diameters situated in the path of at least the preponderant part of said air stream in the vicinity of and at different distances from the said burner so as to provide a plurality of intervening, annular openings for the passage of said air stream as a corresponding plurality of annular fractional air streams, said deflectors having deflecting surfaces disposed transversely to the direction of said air stream for imparting transverse velocity components to said fractional streams and thereby forming at least two series of successive toroidal eddies in said preponderant part of the air stream substantially at the zone wherein this part of the air stream meets the fuel issuing from the burner, whereby the toroidal eddies contain air and fuel and travel in succession through the combustion chamber in the said direction of the air stream.
  • said chamber has an elongate enclosing combustion chamber wall and said deflectors are situated at progressively different distances from said enclosing wall, said deflecting surfaces being oriented in substantially transverse relation to said chamber wall so as to impart to said annular fractional air streams velocity components that are radial with respect to the said chamber wall, said combustion chamber and deflectors being free from any air guide means that imparts to the air a movement of rotation about the axis of the combustion chamber, whereby spreading of the flame which results from the ignition of the said fuel and air against the said chamber wall is minimized.
  • Apparatus according to claim 2 including a generally annular air shroud extending longitudinally with respect to said direction of air flow in spaced relation to said chamber wall for dividing said air stream into fractional air streams flowing respectively within and without the shroud, at least one of said air deflectors being an annular lip extending laterally from the downstream portion of said shroud.
  • Apparatus according to claim 3 wherein at least that one of said air deflectors nearest the combustion chamber wall is a lip directed laterally outwardly from a shroud, whereby matter in the toroidal eddies nearest the wall will rotate in such a way that matter on the downstream faces thereof moves away from the combustion chamber wall.
  • Apparatus according to claim 1 wherein said air deflectors are situated at progressively different distances from the wall of said combustion chamber and are axially displaced from one another along said direction of air flow in such a way that the air deflector nearest the combustion chamber wall is farther downstream than an air deflector near the burner.
  • Apparatus for combustion of fluent fuel comprising an elongate combustion chamber having an air inlet at one end thereof for the admission 'of a combustion air stream and adapted for the passage of said air stream through the chamber substantially without rotation of the air about the longitudinal axis of the chamber, a fuel burner which delivers fuel into said air stream within the combustion chamber, said burner being spaced from the Wall of said combustion chamber, a plurality of radially spaced annular shrouds disposed in the path of at least the preponderant part of said air stream in advance of the zone whereat this part of the air stream meets the fuel issuing from the burner so as to divide the said air stream into a plurality of annular fractional streams, at least some of said shrouds being situated between the burner andthe said wall, and annular lips on the downstream parts of said shrouds extending laterally therefrom and situated in the vicinity of the said zone whereat the said part of the air stream meets the fuel for deflecting the said fractional air streams and forming a series of toroidal e
  • Apparatus according to claim 10 wherein the extent of said overlap is at least five times the radial distance between the shroud and the lip on the neighboring shroud.
  • Apparatus according to claim 9 wherein said burner is situated substantially at the central axis of the combustion chamber and the lip on the shroud of greatest radius is directed outwardly from the shroud toward the wall of the combustion chamber.
  • Apparatus according to claim 6 including a plurality of burners situated between the central axis of the combustion chamber and the combustion chamber wall, a plurality of said shrouds being inner shrouds situated between the said central axis and the burners for dividing the central part of the air stream into annular fractional streams, the lip on the inner shroud nearest the burners being situated in a transverse plane that lies at a shorter axial distance beyond the burner in the said direction of the air stream than the transverse plane containing the lip on the shroud nearest the said central axis.
  • Apparatus for combustion of fluent fuel comprising an elongate combustion chamber having an air inlet at one end thereof for the admission of a combustion air stream, a fuel burner which delivers fuel into said air stream as a forwardly diverging cone Within the combustion chamber, said burner being spaced from the wall of said combustion chamber, a plurality of tubular, axially overlapping, radially spaced shrouds substantially coaxial with the longitudinal axis of the combustion chamber situated in the path of at least the preponderant part of the air stream so as to divide the said air stream into a plurality of annular fractional streams, said shrouds terminating at their downstream ends in lipped edges that project laterally across the paths of said fractional streams, said lips being situated at different axial distances forwardly from the burner so as to lie close to but in rear of said cone for deflection of said fractional streams and forming a series of toroidal eddies in each of said streams, whereby the toroidal eddies contain air and fuel and travel in succession through the combustion

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
US404635A 1953-01-23 1954-01-18 Combustion apparatus with toroidal eddy flame stabilizer Expired - Lifetime US2765621A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB324031X 1953-01-23
GB101253X 1953-12-10

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US2765621A true US2765621A (en) 1956-10-09

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US404635A Expired - Lifetime US2765621A (en) 1953-01-23 1954-01-18 Combustion apparatus with toroidal eddy flame stabilizer

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US (1) US2765621A (fr)
BE (1) BE525924A (fr)
CH (1) CH324031A (fr)
FR (1) FR1095893A (fr)
GB (1) GB743851A (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941364A (en) * 1955-04-05 1960-06-21 Armstrong Siddeley Motors Ltd Igniter chamber for a gas turbine engine
US3075352A (en) * 1958-11-28 1963-01-29 Gen Motors Corp Combustion chamber fluid inlet construction
US3132483A (en) * 1960-04-25 1964-05-12 Rolls Royce Gas turbine engine combustion chamber
US4171612A (en) * 1972-12-11 1979-10-23 Zwick Eugene B Low emission burner construction
US20090280442A1 (en) * 2008-05-05 2009-11-12 American Air Liquide Inc. Device And Method Of Combusting Solid Fuel With Oxygen
US9903585B1 (en) 2014-04-14 2018-02-27 Precision Combustion, Inc. Catalytic burner with utilization chamber

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1232693B (de) * 1960-03-04 1967-01-19 Babcock & Wilcox Dampfkessel Gas- und/oder OElbrenner
CH577627A5 (fr) * 1974-04-03 1976-07-15 Bbc Sulzer Turbomaschinen
AT351131B (de) * 1976-07-05 1979-07-10 Henkel Kgaa Textilwaschmittel
DE2949388A1 (de) * 1979-12-07 1981-06-11 Kraftwerk Union AG, 4330 Mülheim Brennkammer fuer gasturbinen und verfahren zum betrieb der brennkammer
US4523530A (en) * 1982-02-26 1985-06-18 Sumitomo Metal Industries, Ltd. Powdery coal burner
DE10048500C2 (de) * 2000-10-07 2003-04-30 Horst Ley Gasbrenner zur industriellen Verwendung

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1344029A (en) * 1912-01-24 1920-06-22 Alien Property Custodian Apparatus for burning oil
US1474867A (en) * 1920-03-22 1923-11-20 William P Ingersoll Hydrocarbon burner
CH229158A (de) * 1942-09-21 1943-10-15 Sulzer Ag Brennkammer, insbesondere für Druckfeuerung.
US2560207A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Annular combustion chamber with circumferentially spaced double air-swirl burners

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1344029A (en) * 1912-01-24 1920-06-22 Alien Property Custodian Apparatus for burning oil
US1474867A (en) * 1920-03-22 1923-11-20 William P Ingersoll Hydrocarbon burner
CH229158A (de) * 1942-09-21 1943-10-15 Sulzer Ag Brennkammer, insbesondere für Druckfeuerung.
US2560207A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Annular combustion chamber with circumferentially spaced double air-swirl burners

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941364A (en) * 1955-04-05 1960-06-21 Armstrong Siddeley Motors Ltd Igniter chamber for a gas turbine engine
US3075352A (en) * 1958-11-28 1963-01-29 Gen Motors Corp Combustion chamber fluid inlet construction
US3132483A (en) * 1960-04-25 1964-05-12 Rolls Royce Gas turbine engine combustion chamber
US4171612A (en) * 1972-12-11 1979-10-23 Zwick Eugene B Low emission burner construction
US20090280442A1 (en) * 2008-05-05 2009-11-12 American Air Liquide Inc. Device And Method Of Combusting Solid Fuel With Oxygen
US9903585B1 (en) 2014-04-14 2018-02-27 Precision Combustion, Inc. Catalytic burner with utilization chamber

Also Published As

Publication number Publication date
CH324031A (de) 1957-08-31
BE525924A (fr)
FR1095893A (fr) 1955-06-07
GB743851A (en) 1956-01-25

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