US3295318A - Burner devices and combustion chambers therefor - Google Patents

Burner devices and combustion chambers therefor Download PDF

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Publication number
US3295318A
US3295318A US462015A US46201565A US3295318A US 3295318 A US3295318 A US 3295318A US 462015 A US462015 A US 462015A US 46201565 A US46201565 A US 46201565A US 3295318 A US3295318 A US 3295318A
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US
United States
Prior art keywords
rings
struts
radial
fuel
combustion
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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US462015A
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English (en)
Inventor
Bauger Louis Jules
Gambet Bernard Paul Emile
Lacroix Armand Jean Baptiste
Negre Pierre Jean Victor
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants

Definitions

  • combustion chambers of aeronautical turbo-engines are subject to high thermal loads and, so as not to require too large over-all dimensions, it is necessary to make the fullest possible use of the cross-section of the combustion chamber for the installation of ilameholders, while avoiding excessive loss of static pressure.
  • the device provided by the invention of the type comprising two or more concentric rings of V-shaped radial cross-section which are open in the downstream direction and perform the function of ame stabilizers, the means for mounting these rings in a oombustion chamber being devised so as not to disturb ap preciably, the flow in the combustion chamber.
  • the rings are linked by a rigid interconnection system constituted by a series of profiled hollow radial arms or struts which are distributed transversely in the combustion chamber and each of which opens at its opposite ends into the internal space of the respective rings, the assembly comprising the rings and the hollow radial arms or struts forming a rigid unitary assembly.
  • one or more fuel injectors are housed inside each hollow proled strut, air inlet orifices being formed in the leading or upstream edges of the respective struts in the proximity of the said injectors.
  • air and fuel can enter the flame-holder rings by way of the hollow struts, together with, in the case where one -or more of the struts Contains a sparking plug or other ignition device, an ignition ame.
  • Openings may also be formed in the trailing edges of the hollow profiled struts for the discharge of carburetted mixture directly into the combustion charnber.
  • a screen in the form of an annular plate for example, is advantageously disposed opposite the said outlet openings, in the path of the air-fuel mixture which is generated thereby.
  • FIGURE l is a fragmentary diagrammatical view of the burner device
  • FIGURE 2 is a fragmentary sectional view through the upstream portion of a combustion chamber in which the burner device is arranged, the burner device being shown in radial section on the line II-II of FIGURE l;
  • FIGURE 3 is a radial section on the line III- III of FIGURE 1;
  • FIGURES 4 and 5 are fragmentary sections on the line IV-IV of FIGURE 3 and the line V-V of FIG- URE 2, respectively.
  • the burner device is mounted in the combustion chamber 1 of a jet propulsion unit, the combustion chamber being dened by two annular sleeves 2;, 3.
  • the burner device is constituted primarily by two concentric and ooplanar rings 4, 5 of generally Vshaped cross-section, arranged with their open sides in the downstream direction, and by a fuel manifold 6 extending around the circumference of a circle whose radius is intermediate between the radii of the rings 4 and 5 and concentric with the latter.
  • the two burner rings 4 and 5 are connected by a number of tubular radial interconnecting arms or struts 7 distributed around the combustion chamber ll and profiled so as to reduce the drag which they present to the ow of air passing through the chamber (the aerodynamic profile of the struts 7 can be clearly seen in FIG- URE 4.
  • the struts 7 are tubular or hollow and are seccured in radial positions by welding them to the opposed ⁇ faces of the V-shaped rings 4 and 5.
  • the walls of the faces are apertured at 4a and 5a at the places where they are intersected by the tubular struts 7, so that the latter communicate with the interior of the rings at each end.
  • the manifold 6 which is disposed upstream of the struts 7 carries injection nozzles or heads 8 which are welded thereto and which extend into the interior of the struts 7 through orifices 9 formed for this purpose (see FIGURES 3 and 4).
  • the diameter of the said orifices 9 is sufficient to permit a flow of air around the injectors 8 so as to obtain a suitable mixture of air and fuel.
  • Further orifices 10 are formed in the struts 7, at the downstream sides thereof, so as to allow the carburetted mixture to pass out.
  • a narrow annular plate 11 is ar ranged coaxially between and somewhat downstream of the burner rings 4 and 5, at equal radial distances from them; the plate 11 is held by spacers 12 fixed to the downstream sides of the respective struts 7.
  • This arrangement enables the fuel to be injected under high pressure, by reason of the smaller number of injection holes which are provided.
  • the fuel is atomized when the jet of fuel issuing from each injector 8 comes into contact with the downstream part of the associated hollow strut 7 and further, when the fuel passes out through the hole 10 and strikes against the annular plate 11 which acts as a screen. It is sprayed finely into the surrounding air and the mixture is distributed in the two wakes formed by the burner rings 4 and 5, where it can burn.
  • the sides of the two rings which face one another are preferably inclined to a greater extent with respect to the general axis of the chamber than the sides which are remote from one another (as can be seen in the drawings), so as to bring the wakes closer to the median space.
  • each injector 8 instead of each injector 8 producing one or more jets directed towards the annular plate 11 in the same general direction as the direction of the flow of air, it can emit jets which are oblique with respect to the air flow, being directed towards the openings 4a, 5a by way of which the corresponding strut 7 communicates with the internal space of the rings 4 and 5. Atomization of the fuel will then take place on the outer lips of the rings 4 and 5 instead of occurring on the annular place 11 as before. Moreover, the two methods of injection may be employed simultaneously.
  • a supply of hot air can be provided by taking the air from, for example, the turbine of the jet engine.
  • the arrangement comprises a set of linking bars 13 which are pivotally connected at their ends, by means of axes 14 and 15 and securing pins 16, to T-section supports 17 and 18 which are welded to the rings 4 and 5 the leading edge shape of which they take.
  • Each linking bar 13 is also articulated at its centre by means of an axis 19, likewise provided with securing pins 16, to a support 20 fast with the fuel manifold 6.
  • the suspension arrangement comprises a number of articulated connecting rods 21 distributed around the cross-section of the combustion chamber so as to support the burner device as a Whole at the correct position.
  • the device which has just been described has many advantages, among which the following may be mentioned.
  • An improvement in combustion equipments for combustion chambers designed to be traversed by a highvelocity air flow and of the kind comprising at least two annular flame-holder rings of V-shaped radial cross-section defining an inner space closed upstream at the apex of said V cross-section and open downstream, said rings being of different radii and arranged concentrically of each other, and a plurality of generally radial hollow struts extending between said concentric rings and cornmunicating with said inner space thereof, said concentric rings and said radial struts forming a rigid unitary assembly, wherein said improvement comprises an annular fuel manifold having a radius intermediate the radii of said rings and arranged coaxially with respect thereto and upstream of said assembly, an inlet passage formed in the leading edge of said hollow struts at substantially the same radial distance as the radius of said fuel manifold, said inlet passage facing upstream toward said fuel manifold, and a fuel jet nozzle projecting from said manifold and through said in
  • a combustion equipment as claimed in claim 1, comprising further an ignition means housed in at least one of said hollow struts, for igniting the mixture formed therein of fuel discharged by said fuel jet nozzle and of air admitted through said inlet passage.
  • a combustion equipment as claimed in claim 1, comprising further an outlet passage formed in the trailing edge of said hollow struts and facing downstream, and deecting means positioned downstream of said struts and opposite the outlet passage thereof, to deflect uid issuing from said outlet passage radially outward and inward toward the inner space of the flame-holder rings.
  • a combustion equipment as claimed in claim 3, wherein said deecting means comprises an annular plate having substantially the same radius as the radial distance of said outlet passage.

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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)
US462015A 1964-06-09 1965-06-07 Burner devices and combustion chambers therefor Expired - Lifetime US3295318A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR977635A FR1406603A (fr) 1964-06-09 1964-06-09 Dispositif de brûleur et son montage dans une chambre de combustion

Publications (1)

Publication Number Publication Date
US3295318A true US3295318A (en) 1967-01-03

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ID=8831986

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Application Number Title Priority Date Filing Date
US462015A Expired - Lifetime US3295318A (en) 1964-06-09 1965-06-07 Burner devices and combustion chambers therefor

Country Status (5)

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US (1) US3295318A (fr)
DE (1) DE1281213B (fr)
FR (1) FR1406603A (fr)
GB (1) GB1089493A (fr)
SE (1) SE304643B (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3775975A (en) * 1972-09-05 1973-12-04 Gen Electric Fuel distribution system

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3646763A (en) * 1970-05-25 1972-03-07 Gen Electric Gas turbine engine with improved afterburner
US4064691A (en) * 1975-11-04 1977-12-27 General Electric Company Cooling of fastener means for a removable flameholder

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3046731A (en) * 1955-10-07 1962-07-31 Edward Pohlmann Flame stabilization in jet engines
US3196614A (en) * 1961-07-11 1965-07-27 Rolls Royce Ignition device for combustion equipment

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB821286A (en) * 1956-06-05 1959-10-07 Rolls Royce Improvements in or relating to reheat combustion equipment of jet-propulsion engines
US2979900A (en) * 1957-11-12 1961-04-18 United Aircraft Corp Ducted fan flameholder
US2935847A (en) * 1957-11-18 1960-05-10 United Aircraft Corp Flow control means for use with flameholders and flamespreaders
DE1133185B (de) * 1959-04-21 1962-07-12 Snecma Verbrennungseinrichtung an Rueckstosstrieb-werken, insbesondere zur Nachverbrennung
US3035410A (en) * 1959-04-29 1962-05-22 Nord Aviation Monobloc assembly for the various parts of a ram-jet combustion device
FR1245920A (fr) * 1960-01-19 1960-11-10 Le Ministre De La Defense Nati Collecteur de distribution de combustible isolé

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3046731A (en) * 1955-10-07 1962-07-31 Edward Pohlmann Flame stabilization in jet engines
US3196614A (en) * 1961-07-11 1965-07-27 Rolls Royce Ignition device for combustion equipment

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3775975A (en) * 1972-09-05 1973-12-04 Gen Electric Fuel distribution system

Also Published As

Publication number Publication date
SE304643B (fr) 1968-09-30
DE1281213B (de) 1968-10-24
GB1089493A (en) 1967-11-01
FR1406603A (fr) 1965-07-23

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