US2632300A - Combustion stabilization means having igniter grill heated by pilotburner - Google Patents

Combustion stabilization means having igniter grill heated by pilotburner Download PDF

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Publication number
US2632300A
US2632300A US108316A US10831649A US2632300A US 2632300 A US2632300 A US 2632300A US 108316 A US108316 A US 108316A US 10831649 A US10831649 A US 10831649A US 2632300 A US2632300 A US 2632300A
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US
United States
Prior art keywords
fuel
flame
tube
air mixture
webs
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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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US108316A
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English (en)
Inventor
Brzozowski Witold
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.)
Thermal Research and Engineering Corp
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Thermal Research and Engineering Corp
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Priority to US108316A priority Critical patent/US2632300A/en
Priority to CH296445D priority patent/CH296445A/fr
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Publication of US2632300A publication Critical patent/US2632300A/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion

Definitions

  • This invention relates to a burner, and more particularly, aburnerwherein fuel in fluid form is. mixed with a column of air movingtthere -l through under pressure, and burned therein..
  • the invention is especially useful in its applica tion .to jet propulsion, to whieh use,. however, it
  • the igniter webs are heated to inoandescence by. the fuelair. mixture, and in turn, spreadthe.
  • the fuelsupply element- may. take the form of a stream-
  • lined conduit extending. across the chamber or tubein the path of the moving column of air
  • the maj or axis .of the, fuel supply. element; or, V the-flame. preserver shell may be annular in form and. disposed in the tubecoaxiallytherewith
  • the present invention contemplates an igniter grillformedby disposit ionof the igniterlf webs ina succession o f ranlgs each in line across the chamber or tube
  • Special designs of igniter" web 's may be, employed to advantage
  • Fig. 1 is a broken longitudinal mid-section hrou n r nstrup ed, n rra s d e cording to the invention;
  • Fig, 2 isa crossrsection' taken on the line II II of Fig'. 1, they section being shownonan'enlarged'. scale; big.
  • 3 is anenlargedseetion taken on the line mf l Q v. V
  • Fig. 4 is an enlarged perspective fragmental viewbf one of the igniter .we b s shown in 1;
  • Fig. 5 is a cross-section taken on the'line V .V v fFi ee ti in hqw Oe. n ree.d. scale;
  • Fig.' 6 is 4 a, a broken I longitudinal mid-section taken on thfi line VI-VI of Big, '5. showing ii n cross-section one type. of igniter grilland one arrangement ofv a plurality of igniter webs
  • Fig. 7 is a fragmental longitudinal mid-section through another burner v having I therein a diner ent typeof flame preserverj
  • Fig. 8 is" a cross section talgen on the line flnlf of ig
  • Fig. 9 is a cross section taken on, the line IXfIXY Fig.
  • Fig. 10 isajbroken longitudinal mid-section m lar to that 1 t @i. .d. h..F-i ei' cross-section I another type of ig n iter "grin" and one arrangement of n a plurality of jignite r web s" av n al fier nt o m';
  • Fig. 11 is a broken longitudinal mid-section similar to those illustra 'zed infFijg's. ef'andioj showing another type of V igniter grill I arrangment, the igniter webs which form the grill hayingthe form of those shqwnin Fig.
  • Fig 12 is a cross-seetion through Ta single, igniter web of a different type from those unis trated inFigs 6,, 10 and11.; and Fig, 13 is a cross-section through an igniter. web of still a different vtype.
  • prdyideda charnb er here.-v shown as a 1 tube I 5,, through ,which a column of airis moved athighwelocity. In order tol form ⁇ .
  • the fuel-supply element comprises a streamlined conduit extending transversely within the tube I5.
  • a pipe l9 suitably coupled, as at 20, to the fuel-supply element, carries thereto a fluid fuel which is discharged into the moving air column through a constricted opening 2
  • the flame preserver 11 Within the chamber, or tube l5, downstream from the fuel-supply element It and extending transversely of the tube, is positioned the flame preserver 11. Because the velocity of the fuel-air mixture may be greater than the rate of flame propagation, the flame preserver I! is designed to emit a flame continuously for constantly igniting combustion of the fuel-air mixture therein, unless special provision were made for spreading the flame at a point near the burner.
  • the edges 25 of the longitudinal exit opening 23 may be spread apart to reduce the velocity of the fuel-air mixture immediately adjacent the downstream openin 23, and thus to widen the ignition wedge at the flame preserver.
  • Such arrangement is shown in Fig. 1.
  • the igniter grill i8 is positioned in the path of the ignition wedge to receive heat from the burning fuel-air mixture and to transfer such heat outwardly in the igniter webs 26, positioned in the tube [5 at right.
  • the heads 21 of the T-shaped igniter webs 26 are shown as being continuous, such is not necessarilythe case.
  • the igniter webs here shown are positioned in successive ranks, each rank comprising a plurality of webs in parallel spaced relationship across the tube. Three such ranks are illustrated in Fig. 6, although more or fewer may be employed. Accordingly, when the ignited fuel-air mixture 7 meets the first rank of igniter webs, it impinges taposed holes or orifices.
  • the fuel-air mixture passing through the longitudinal opening 22 in the flame preserver has its velocity materially decreased as it enters the protected and comparatively quiet area within the unit,
  • the longitudinal opening 23 on the downstream side of the flame preserver permit the ignited fuel-air mixture to leave the burner and to enter the moving unignited fuel-air mixture column beyond the burner.
  • the cross-section of the longitudinal opening 22 is so related to the volume within the burner that the flame will not be blown out by the rapidly moving mixture external to the flame preserver.
  • Igniting means is provided within the unit.
  • a spark plug 24 projects through the tube l5'and into one end of the flame preserver I! for igniting the fuel-air mixture therein.
  • the ignited fuel-air mixture which leaves the flame preserver through its downstream longitudinal exit opening or slot 23 mixes with the unignited fuel-air mixture and constantly serves to ignite it across the diameter of the tube.
  • the flame issuing in a ribbon from the downstream longitudinal opening 23 across the width of the burner, expands in wedge formation as the fuelupon the heads of the T-shaped webs, heating the webs to incandescence.
  • the heat received by each head is conducted outwardly from the central portion of the head into the path of the unignited fuel-air mixture, which it ignites.
  • the tail 28 of the T-shaped web 26 is protected by its head 21 from the cooling action of the unignited fuel-air mixture which strikes the web. The tail, therefore, acts efficiently to conduct heat away from the center of the web and to ignite the unair mixture is progressively ignited. Because of g ignited mixture which comes in contact with it. The successive ranks of webs act similarly.
  • the T-shaped igniter web increases the boundary layer of both ignited and unignited fuel-air mixture in contact with the web. In other words, a
  • the entire fuel-air mixture may be ignited considerably nearer to the flame preserver [1 than would otherwise be the case, and a shorter tube I 5 suffices to effect complete combustion of the mixture.
  • Applicant's invention is not limited to a flame preserver comprising a cylindrical shell and extending diametrically across the tube I5.
  • a flame preserver comprising a cylindrical shell and extending diametrically across the tube I5.
  • Another type of flame preserver which has been operated successfully is illustrated in Figs. '7, 8 and 9.
  • This unit Ha is constructed in the form of a hollow annulus, and is disposed concentrically within the tube 15 where it is supported as by fins 2 9.
  • the flame preserver Ila has a narrow circular entrance opening or slot 22a in its upstream side and a similar circular exit opening or slot 23a in its downstream side, and spacers 30 within the unit may serve to hold its two annular parts to a gether;
  • the edges '25wof the exit opening or'slot 23a are preferably spread apart in the same manner and for thesame-purpose as the edges 25 illustrated in Fig; 1.
  • an expanding ring of burning fuel-air mixture leaves the annular flame preserver m1 and tends to ignite a large propor-" tion of the unignited fuel-air mixture in the im-- mediate vicinity of the unit.
  • the invention contemplates" igniter grills which are formed of webs differ ing from the T-shaped igniter websillustrated in Figs. 1, 4, 5 and 6.
  • the individual webs are positioned with edges thereof directed'toward the oncoming fuel-air mixture:
  • the webs maybe formed in'two parts as 'illustr'atedini Fig; 12.
  • Such webs are'formed with their heads '2': completely separated'from their tails 280, the headand' tail of eachweb being positioned in T'-formation within the tube IS'in'the manner illustrated'in Fig. 6.
  • the advantage-of this arrangement is that the tailsare not cooled'by the heads which'are in contact withthe' unignited fuel-airmixture'.
  • the sep arate tails 28c' may, therefore, attain and conduct'to" the unignited mixture a higher'degree of heat than ispossible in the webs 25.
  • the head 210 of such a web is alone cooled by the unignited' fuel-air 'mixture' which impinges upon it, and the tail 28c'is completely'heated by the burning mixture with which it comes in" contact. Moreefficien't operation of theitail in spreading the flame is accordingly effected.
  • theboundary layer of both ignited and unignited fuel-air mixture in contact with the web is increasedb'y'this construction'as explained above.
  • thermore thermore
  • a burner for burning a column of a-"fuel-air An igniter web of this form increases 6? mixture moving at high velocity, zsaidiiburner comprising a tube through: whichra: column: 01:1 air passes; a fuel-supply-relementin saidsitubee for diffusingfuel :intothe column .of 1 airtstocproay.
  • a burner for burning a column of a fuelair mixture moving at high velocity comprising a tube through which a column of air passes; a fuel-supply element in said tube for diffusing fuel into the column of air to provide a fuel-air mixture; a flame preserver within said tube downstream from said fuel-supply element for continuously igniting the fuel-air mixture, said flame preserver comprising a hollow substantially annular unit disposed within said tube concentrically therewith having a narrow circular slot on its upstream side and a similar slot on its downstream side, and a spark plug extending through said tube into said flame preserver for igniting therein the fuel-air mixture entering said flame preserver through its upstream slot; and a plurality of parallel igniter webs disposed downstream from said flame preserver, each web extending transversely completely across said tube, said webs being disposed in a succession of ranks each in line across said tube, said webs acting to receive heat from the burning fuel-air mixture and to give up heat to
  • a burner for burning a column of a fuel-air mixture moving at high velocity comprising a tube through which a column of air passes; a fuel-supply element in said tube for diffusing fuel into the column of air to providea fuel-air mixture; a flame preserver within said tube downstream from said fuel-supply element for continuously igniting the fuel-air mixture, said flame preserver comprising a hollow substantially annular unit disposed within said tube concentrically therewith having a narrow circular slot on its upstream side and a similar slot on its downstream side, and a spark plug extending through said tube and into said flame preserver for igniting therein the fuel-air mixture entering said flame preserver through its narrow upstream slot; and aplurality of T- shaped igniter webs disposed downstream from said.
  • said T- shaped Webs being positioned with their heads upstream to protect their tails from being cooled by the unignited fuel-air mixture, and said webs acting to receive heat from the burning fuel-air mixture and to give up heat to ignite the unignited fuel-air mixture adjacent said webs.
  • a burner for burning a column of fuel-air mixture moving at high velocity comprising a chamber through which a column of air passes; a fuel-supply element in said chamber for diffusing fuel into the column of air to provide a fuel-air mixture; a flame preserver within said chamber downstream from said fuelsupply element for continuously igniting the fuelair mixture, said flame preserver comprising a hollow substantially annular unit disposed within said chamber in the path of the unignited fuelair mixture having a narrow circular slot on its upstream side and a similar slot on its downstream side; and a plurality of T-shaped igniter webs disposed downstream from said flame preserver in substantially parallel relationship across said chamber in the path of the ignited and unignited fuel-air mixture, said webs being positioned with their heads upstream to protect their tails from being cooled by the unignited fuel-air mixture, the tails of said T-shaped igniter webs being separated from the heads thereof to prevent direct conduction of heat from the tails by the heads of said webs, and said web
  • a burner for burning a column of a fuelair mixture moving at high velocity comprising a tube through which the air passes; a fuel-supply element in said tube for diffusing fuel into the column of air to provide a fuel-air mixture; a flame preserver within said tube downstream from said fuel-supply element for continuously igniting the fuel-air mixture, said flame preserver comprising a hollow substantially annular unit disposed within said tube concentrically therewith having a narrow circular slot on its upstream side and a similar slot on its downstream side; and a plurality of T-shaped igniter webs disposed downstream from said burner in substantially parallel spaced relationship across said tube, said webs being positioned with their heads upstream to protect their tails from being cooled by the unignited fuel-air mixture, the tails of said T-shaped igniter webs being separated from the heads thereof to prevent direct conduction of heat from the tails by the heads of said webs, and said webs acting to receive heat from the burning fuel-air mixture and to give up heat to ignite the unigni
  • a burner for burning a column of a fuelair mixture moving at high velocity comprising a tube through which a column of air passes; a fuel-supply element in said tube for difiusing fuel into the column of air to provide a fuel-air mixture; a flame preserver within said tube downstream from said fuel-supply element for continuously igniting the fuel-air mixture, said flame preserver comprising a hollow substantially annular unit disposed within said tube concentrically therewith having a narrow circular entrance slot on its upstream side and a similar exit slot on its downstream side, the exit slot of said flame preserver having its edges spread apart outwardly, and a spark plug extending through said tube and into said flame preserver for igniting therein the fuel-air mixture entering said flame preserver through its upstream slot; and a plurality of T-shaped igniter webs disposed downstream from said flame preserver in substantially parallel spaced relationship across said tube in the path of the ignited and unignited fuel-air mixture, said T- shaped webs being positioned with their
  • a plurality of T-shaped igniter webs disposed downstream from the flame preserver across the chamber in the path of the ignited and unignited iuel-air mixture, said webs acting to receive heat from the burning fuel-air mixture and to give up heat to ignite the unignited fuel-air mixture adjacent said webs.
  • a burner for burning a column of a fuelair mixture moving at high velocity which comprises a chamber through which the air passes, a fuel-supply element in the chamber for difiusing fuel within the column of air to provide a fuel-air mixture, and a flame preserver within the chamber downstream-from the fuel-supply element for continuously igniting the fuel-air mixture: a plurality of T-shaped igniter webs disposed downstream from the flame preserver in a succession of ranks each in line across the chamber in the path of the ignited and unignited fuel-air mixture, said webs acting to receive heat from the burning fuel-air mixture and to give up heat to ignite the unignited fuel-air mixture adjacent said webs.
  • a burner for burning a column of fuel-air mixture moving at high velocity comprising a chamber through which a column of air passes; a fuel-supply element in said chamber for diffusing fuel into the column of air to provide a fuel-air mixture; a flame preserver within said chamber downstream from said fuelsupply element for continuously igniting the fuelair mixture; and a plurality of separate parallel igniter webs disposed downstream from said preserver in a succession of ranks each in line extending transversely completely across said chamber, said Webs being positioned with their 10 major cross-sectional dimensions extending in substantial alignment with the direction of the combustion stream to receive heat from the burning fuel-air mixture and to give up heat to ignite the unignited fuel-air mixture adjacent said webs.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
US108316A 1949-08-03 1949-08-03 Combustion stabilization means having igniter grill heated by pilotburner Expired - Lifetime US2632300A (en)

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Application Number Priority Date Filing Date Title
US108316A US2632300A (en) 1949-08-03 1949-08-03 Combustion stabilization means having igniter grill heated by pilotburner
CH296445D CH296445A (fr) 1949-08-03 1950-08-03 Brûleur.

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US108316A US2632300A (en) 1949-08-03 1949-08-03 Combustion stabilization means having igniter grill heated by pilotburner

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Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2660859A (en) * 1952-06-18 1953-12-01 United Aircraft Corp Combined flameholder and turning vane
US2682747A (en) * 1953-03-10 1954-07-06 Us Navy Combined fuel injector and flame stabilizer
US2711070A (en) * 1952-07-31 1955-06-21 Westinghouse Electric Corp Gas turbine apparatus
US2726511A (en) * 1950-05-18 1955-12-13 Solar Aircraft Co Afterburners
US2760339A (en) * 1952-06-02 1956-08-28 Douglas Aircraft Co Inc Flameholder
US2760340A (en) * 1954-08-30 1956-08-28 Clifford E Seglem Igniter and combustion apparatus
US2777508A (en) * 1952-04-26 1957-01-15 Douglas Aircraft Co Inc Pilot burner for combustion heater
US2780424A (en) * 1951-10-19 1957-02-05 Lockheed Aircraft Corp Airplane for vertical take-off in horizontal attitude
US2784553A (en) * 1954-06-10 1957-03-12 Corso Serafino M De Combustion conduit and igniter structure
US2806356A (en) * 1952-08-27 1957-09-17 Theodore Raymond R Bocchio Combustion initiator
US2832402A (en) * 1952-04-14 1958-04-29 Douglas Aircraft Co Inc Annular pilot burner for combustion heaters
US2835109A (en) * 1952-07-17 1958-05-20 John P Longwell Igniter for ram-jet
US2839128A (en) * 1953-03-25 1958-06-17 Thermal Res And Engineering Co Burner
US2859588A (en) * 1953-12-16 1958-11-11 Texas Co Flame holder structure for ram jet combustor
US2861424A (en) * 1954-04-09 1958-11-25 Douglas Aircraft Co Inc Fuel supply means for combustion apparatus
US2872785A (en) * 1951-06-06 1959-02-10 Curtiss Wright Corp Jet engine burner apparatus having means for spreading the pilot flame
US2972231A (en) * 1954-09-23 1961-02-21 Ii James W Mullen Rod-igniters for ramjet burners
US2988878A (en) * 1958-07-14 1961-06-20 United Aircraft Corp Fuel nozzle for bypass engine
US3037351A (en) * 1956-05-14 1962-06-05 Paul O Tobeler Combustion turbine
DE1193734B (de) * 1960-07-13 1965-05-26 United Aircraft Corp Brennstoffeinspritzvorrichtung fuer Gasturbinen-Strahltriebwerke
US3572030A (en) * 1968-12-26 1971-03-23 James D Cuff Rotary engine assembly
US3683215A (en) * 1970-03-16 1972-08-08 Dan Fire Energy Ved Mita Gudma Method and an apparatus for the production of heat and pressure energy
US3727409A (en) * 1961-03-30 1973-04-17 Garrett Corp Hypersonic aircraft engine and fuel injection system therefor
US4239482A (en) * 1978-04-12 1980-12-16 Durfee Edward P Fuel burner with air-deflecting object and method therefor
EP0473371A1 (fr) * 1990-08-28 1992-03-04 General Electric Company Dispositif d'injection du carburant mélangeur
EP2261566A1 (fr) * 2009-05-28 2010-12-15 Siemens AG Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur
US20130133329A1 (en) * 2011-11-25 2013-05-30 Institute Of Engineering Thermophysics, Chinese Academy Of Sciences Air fuel premixer having arrayed mixing vanes for gas turbine combustor

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR384939A (fr) *
US1574545A (en) * 1924-04-11 1926-02-23 Bear Comb Company Oil heater
US1839880A (en) * 1927-12-23 1932-01-05 Cons Car Heating Co Inc Burner
US2142601A (en) * 1935-04-19 1939-01-03 Maitland B Bleecker Reaction propulsion device
US2410881A (en) * 1942-07-29 1946-11-12 Robert H Hunter Heating apparatus

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR384939A (fr) *
US1574545A (en) * 1924-04-11 1926-02-23 Bear Comb Company Oil heater
US1839880A (en) * 1927-12-23 1932-01-05 Cons Car Heating Co Inc Burner
US2142601A (en) * 1935-04-19 1939-01-03 Maitland B Bleecker Reaction propulsion device
US2410881A (en) * 1942-07-29 1946-11-12 Robert H Hunter Heating apparatus

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2726511A (en) * 1950-05-18 1955-12-13 Solar Aircraft Co Afterburners
US2872785A (en) * 1951-06-06 1959-02-10 Curtiss Wright Corp Jet engine burner apparatus having means for spreading the pilot flame
US2780424A (en) * 1951-10-19 1957-02-05 Lockheed Aircraft Corp Airplane for vertical take-off in horizontal attitude
US2832402A (en) * 1952-04-14 1958-04-29 Douglas Aircraft Co Inc Annular pilot burner for combustion heaters
US2777508A (en) * 1952-04-26 1957-01-15 Douglas Aircraft Co Inc Pilot burner for combustion heater
US2760339A (en) * 1952-06-02 1956-08-28 Douglas Aircraft Co Inc Flameholder
US2660859A (en) * 1952-06-18 1953-12-01 United Aircraft Corp Combined flameholder and turning vane
US2835109A (en) * 1952-07-17 1958-05-20 John P Longwell Igniter for ram-jet
US2711070A (en) * 1952-07-31 1955-06-21 Westinghouse Electric Corp Gas turbine apparatus
US2806356A (en) * 1952-08-27 1957-09-17 Theodore Raymond R Bocchio Combustion initiator
US2682747A (en) * 1953-03-10 1954-07-06 Us Navy Combined fuel injector and flame stabilizer
US2839128A (en) * 1953-03-25 1958-06-17 Thermal Res And Engineering Co Burner
US2859588A (en) * 1953-12-16 1958-11-11 Texas Co Flame holder structure for ram jet combustor
US2861424A (en) * 1954-04-09 1958-11-25 Douglas Aircraft Co Inc Fuel supply means for combustion apparatus
US2784553A (en) * 1954-06-10 1957-03-12 Corso Serafino M De Combustion conduit and igniter structure
US2760340A (en) * 1954-08-30 1956-08-28 Clifford E Seglem Igniter and combustion apparatus
US2972231A (en) * 1954-09-23 1961-02-21 Ii James W Mullen Rod-igniters for ramjet burners
US3037351A (en) * 1956-05-14 1962-06-05 Paul O Tobeler Combustion turbine
US2988878A (en) * 1958-07-14 1961-06-20 United Aircraft Corp Fuel nozzle for bypass engine
DE1193734B (de) * 1960-07-13 1965-05-26 United Aircraft Corp Brennstoffeinspritzvorrichtung fuer Gasturbinen-Strahltriebwerke
US3727409A (en) * 1961-03-30 1973-04-17 Garrett Corp Hypersonic aircraft engine and fuel injection system therefor
US3572030A (en) * 1968-12-26 1971-03-23 James D Cuff Rotary engine assembly
US3683215A (en) * 1970-03-16 1972-08-08 Dan Fire Energy Ved Mita Gudma Method and an apparatus for the production of heat and pressure energy
US4239482A (en) * 1978-04-12 1980-12-16 Durfee Edward P Fuel burner with air-deflecting object and method therefor
EP0473371A1 (fr) * 1990-08-28 1992-03-04 General Electric Company Dispositif d'injection du carburant mélangeur
EP2261566A1 (fr) * 2009-05-28 2010-12-15 Siemens AG Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur
WO2010136300A3 (fr) * 2009-05-28 2011-01-27 Siemens Aktiengesellschaft Brûleur et procédé pour réduire des oscillations de flammes auto-induites dans un brûleur
US20130133329A1 (en) * 2011-11-25 2013-05-30 Institute Of Engineering Thermophysics, Chinese Academy Of Sciences Air fuel premixer having arrayed mixing vanes for gas turbine combustor
US9234662B2 (en) * 2011-11-25 2016-01-12 The Institute of Engineering Thermophysics, The Chinese Academy of Sciences Air fuel premixer having arrayed mixing vanes for gas turbine combustor

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CH296445A (fr) 1954-02-15

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