US2616257A - Combustion chamber with air inlet means providing a plurality of concentric strata of varying velocities - Google Patents

Combustion chamber with air inlet means providing a plurality of concentric strata of varying velocities Download PDF

Info

Publication number
US2616257A
US2616257A US640018A US64001846A US2616257A US 2616257 A US2616257 A US 2616257A US 640018 A US640018 A US 640018A US 64001846 A US64001846 A US 64001846A US 2616257 A US2616257 A US 2616257A
Authority
US
United States
Prior art keywords
air
burner
chamber
breech
fuel
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
Application number
US640018A
Other languages
English (en)
Inventor
Frank C Mock
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.)
Bendix Aviation Corp
Original Assignee
Bendix Aviation Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Bendix Aviation Corp filed Critical Bendix Aviation Corp
Priority to US640018A priority Critical patent/US2616257A/en
Priority to FR942149D priority patent/FR942149A/fr
Application granted granted Critical
Publication of US2616257A publication Critical patent/US2616257A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S116/00—Signals and indicators
    • Y10S116/22—Heated air

Definitions

  • the present invention relates to burners, and particularly to burners wherein a fuel, either gaseous, liquid or powdered solid fuel, is injected into and burned in a moving column of air.
  • a fuel either gaseous, liquid or powdered solid fuel
  • Such burners are particularly adapted for use in aircraft power plants or engines of the gas turbine and/or jet propulsion types wherein compressed air is supplied to a chamber constituting part of the burner, at which'point it is heated by the combustion of fuel and the expanded air and products of combustion discharge through a gas, turbine for driving an air compressor and/or a propeller, after which the gases may be dis charged through a reaction tube to propel the aircraft or to assist the propeller in propelling the aircraft.
  • a burner of the aforesaid type is ofttimes subjected to conditions which render it extremelydiificult to maintain stable operation of the burner, or to obtain proper flame propagation and an effective fuel/air ratio over.
  • flow of fuel to the burner may at timesbe suddenly reduced to reduce engine speed, resulting in a low flame at the burner nozzle while at the same time the momentum of the engine may momentarily produce a high air flow tending to blow out the flame.
  • it. is de-- sirable that the burner ignite or start quickly and easily under all conditions of ai-r flow, both at the start of a flight and during flight of an aircraft.
  • burner tube in communication with the main burner chamber and having a resonance fre-' quency tending to neutralize or dampen out the reverberations of the main burner chamber or tube.
  • An object of the invention is to provide a burner or generator of the type specified which will admit air under pressure into the burner chamber, and particularly the breech portion thereof in a manner such as to render the burner flame stable under widely varying conditions of airflow to the burner.
  • Another and more specific object is to provide a burner or generator for heating and expanding a'ir flowing thereto under pressure having calibrated air-inlet means which directs the air into the breech portion of the burner chamber in a plurality of concentric masses or strata of varying, velocities with the mass of lowest velocity in the immediate region of the burner nozzle.
  • Another object is to provide means in a burner whereby carbon formation on the fuel-delivery nozzle or nozzles as well as on the spark plugs or analogous ignition means is reduced to a minimum;
  • Another object is to provide an improved burner or generator unit particularly adapted for power plants of the gas turbine an/or j'et propulsion types, and wherein burner failure due to the foregoing and other causes is reduced to a minimum.
  • a further object is to improve and render more efficient burners or heat generators.
  • Figure 1' is a substantially central longitudinal" sectional view of a burner embodying the features of the invention
  • Figure 2 is a similar view of a modification structure
  • Figure 3 is an end view of Figure 2 taken" as spray nozzle adapted for use with the burners" illustrated inthe preceding. figures;
  • Figure 7 is'an' enlarged section of the'end por'- tion of the nozzle of Figure 6; and" at the breech end of the a rotary compressor, not shown, driven by a I turbine, also not shown, having blades subjected to the dynamic action of heated and expanded air and products of combustion generated in the burner.
  • the burner of Figure l is similar to that disclosed in my copending application above noted; it consists of an outer cylindrical shell or wall 8 provided with a plurality of air inlet ports 9, to which air is supplied under pressure through the chamber 5.
  • an outer cylindrical shell or wall 8 provided with a plurality of air inlet ports 9, to which air is supplied under pressure through the chamber 5.
  • another shorter cylinder or annulus it ⁇ having an outwardly tapered or inclined bafiie wall I i provided with a series of calibrated air inlet orifices !2.
  • Within the annulus I is a third, still shorter cylinder or annulus [3 provided with an end bafile wall l4 also formed with a series of air inlet orifices H3.
  • the air impact or breech end of the burner is provided with a baffle wall l6 formed with a series of annularlyarranged air-inlet orifices H, is and [9, which are preferably of progressively decreasing area or flow capacity as they approach the center of the said wall l6, said orifices ll, I8 and I9 opening into velocity-reducing chambers 20, 2
  • An ignitor 25 which may be of the electric sparking type supplied with current from a suitable source, not shown, is projected into the burner cylinder adjacent the tip of a burner nozzle 25.
  • the aggregate area of orifices I2 is greater than the aggregate area of orifices H, the aggregate area of orifices I is greater than the aggregate area of orifices l8, and the aggre-.
  • gate area of orifices 24 is greater than the aggregatearea of orifices l9.
  • a combustion chamber constructed in this manner coacts with the fuel feeding system which supplies fuel to the chamber through the burner nozzle to insure localized fuel/air proportioning and flame propagation throughout periods of low fuel feeds and permits low fuel feeds at low air fiows or low power conditions, and also at high air flows as on engine deceleration, without burner failure.
  • a spray of 1.2 pounds per hour will produce a rather sensitive flame which can be quickly snuffed out by the sudden injection of air above a certain velocity, or by an oversupply of air within the region of the flame.
  • the velocity of the air flowing into the combustion chamber may be adjusted with respect to a pl'urality of combustion zones to insure proper or eflicient flame propagation at all air flows or power conditions.
  • the velocity within the central burner zone in the immediate region of the nozzle 26 may be held within a relatively low wall at by means of a wall 5
  • bafiie material such as steel wool or the like, indicated at 21, may be disposed in the chambers 2i and 22, and also in the outer chamber 26 if desired.
  • FIGs 2 and 3 illustrate a burner of modified construction with respect to Figure l, the burner being illustrated as one of any number of similar burners mounted within the chamber 5 defined by the annular concentric walls 6 and "I in the same manner as in Figure 1.
  • the burner of Figures 2 and 3 comprises an outer shell 40 formed with a series of high velocity air inlet holes 4
  • a breech assembly comprising an outer, generally cylindrical member 43 formed with circumferential rings or bosses 44 and 45' by means of which it may be suitably secured to the shell 40 as by welding or in any other suitable manner.
  • An annular inwardly or convergingly curved wall 45 forms an extension of the member 43, and another substantially straight cylindrical wall 46 extends forwardly-from the wall 45 and is connected thereto by web portions or openwor structure defining openings 41.
  • the cylindrical wall 45 soon becomes heated to a high temperature after the burner starts, since it lies in the low flame area, and thereafter it furnishes a hot vaporizing surface against which spray from the nozzle 69 impinges.
  • this reduces the tendency toward collection of unburnt fuel in the breech area at low fuel delivery pressures and subsequent explosion and dangerously high heat conditions when the fuel delivery is increased.
  • the openings '47 facilitate access of hot gases to the exterior surface of the wall 46.
  • An inner breech unit generally indicated at 48, is provided and comprises an end wall 48 from the periphery of which a converging or radially-inwardly curved wall 49 projects and is joinedat its inner edge to a straight cylindrical
  • and adjacent part of the wall 48' form the boundary of a chamber 52; and the end wall 48' is formed with a plurality of calibrated air-inlet openings 53 for admitting controlled quantities of air to thechamber 52, and from this chamber air maypass into the nozzle area of the breech chamber at a reduced velocity through ca1i-' brated holes 54 and 55, the aggregate area of holes 54 and 55 being greater than the aggregate area of the holes 53.
  • the end wall 48' supports a spray nozzle 60 and a spark plug or other suitable ignition device 6I.
  • Airunder pressure moving in a direction from left to right as viewed in Figure 2 is directed into the outer chamber 5 and passes beyond the breech portion of the burner to the holes 4
  • the velocity of the air entering through the outer passage 51 might be forty feet per second, while the air entering through the inner pasage might have a velocity of fifteen feet per second.
  • the inlet slots 51, 58 and the chambers 51, 58' may be calibrated to provide the required amount of air at predeterminedvelocities to obtain the most efficient combustion and flame propagation within the breech area of the burner chamber without danger of blowing out the fiame at the burnernozzle during low fuelfeeds and high air flows.
  • the holes 53 admit air into the chamber 52 from which it passes at a reduced velocity through the calibrated holes 54 and 55 and is projected onto the tip of nozzle 60 and also on the exposed outer surface of the spark plug 6
  • This controlled supply of air tends to reduce carbon formation by furnishing sufficient oxygen to this region for admixture with the fine mist of oil, usually present in this area, to support combustion, or burn the oil without permitting it to cake on the surfaces of the nozzle and the plug.
  • the outer shell 40 may be of heat resistant sheet metal, refractory material or the like, while the outer and inner units 43 and 48 may be in the form of castings and the intermediate unit 56 of sheet metal, the parts being joined or bridged by connecting bosses and welded or otherwise secured together to form a complete assembly. Obviously other materials or methods of fabrication may be used.
  • FIGS 4 and 5 illustrate a further modification in burner structure for carrying out the objects of the present invention.
  • the burner as shown in Figures 4 and 5. is mounted in a chamber'5 similar to the burners of Figures 1 and 2; it comprises an outer shell 10 formed with a series of holes 1
  • the breech portion of the burner comprises a unit having anend wall 12, which as shown is of radially outwardly stepped construction, and projecting forwardly from theend wall are a series of concentric cylindrical walls 13, 14 and 15 which define a plurality of chambers 16 and 11, a main breech chamber '18 and a supplemental breech chamber 18'.
  • a wall 13' surrounds the breech chamber forwardly of the nozzle, to provide .a vaporizing surface in a manner similar to the wall 46 of Fig. 2.
  • the outer face walls of the chambers 16 and 11 are supplied with air through a plurality of openings 19 and 19', preferably arranged tangentially in order to produce a baffle effect by causing the airto pass into the chambers 1'6 and 11 to be broken up or have its velocity reduced-by circulation and frictionless This obviates the need for ber 82 which is supplied with. air through ann-ular slots 83. and holes 83'.' V
  • the end wall 12 may be bored or cast with holes or. suitable openings to receive a spray nozzle 84 and a spark plug 85.
  • Air at highvelocity entering the chamber 5 from left toright as viewed in Figure 4 is directed into. the holes 1
  • the air entering the breech chamber through the holes 89 may be at a velocity of forty' feet per second; while the air entering the breech chamber through the holes BI may be at a velocity of fifteen feet per second.
  • the whirling motion imparted to the air entering chambers 16 and 11 also tends to distribute the air equally through out the area of the said chambers before passing into the breech chamber 18.
  • additional holes may be formed in the wall 15 to direct air against the tip of the nozzle 84 and the spark plug and furnish sufiicient oxygen to support combustion in the immediate region of the nozzle tip and the spark plug and thereby reduce the tendency toward carbon formation on thes parts.
  • any suitable type of fuel spray nozzle '25, 60 or 84 may be used, it is preferred to use a nozzle which will operate to discharge a coneshaped spray of fuel when the latter is under low pressures in the area of lowest velocity of the incoming air, and as the fuel delivery pressure increases, the fuel spray cone will progressively lengthen and intersect the respective masses or strata of incoming air.
  • a nozzle suitable foruse with burners of the type herein disclosed is shown in Figures 6, '1 and 8.
  • the nozzle illustrated in Figures 6, 7 and 8 consists of a flanged body 90 having therein av spray head 9
  • a cap 95 is threaded on the rear extremity of the body 99, and between this cap and the body flange is a fitting 96 having a tubular portion 91 to which a fuel supply tube 98 is connected.
  • Fuel passes into nozzle chamber 99 through ports I00; and at low pressures flows through small bores I 0 I formedin the spray head, note Figure '7, at a tangent to a central cavity or recess I02 having therein a member I03 provided with a small lowpressure discharge orifice I94.
  • the seating tension of spring 93 is adjustable by means of thrust nut I95 and lock nut I96.
  • the tangential arrangement of the bores I0l causes the spray to swirl as it leaves the low pressure orifice at an angle determined by the relative areas of bores or passages NH and I04.
  • the tension of spring 93 may be adjusted to Between the outerv
  • remains seated and discharge is by way of small bores NH and low pressure discharge orifice I04, but as pressure builds up, discharge is principally through the high pressure discharge orifice 94 with a certain additional discharge through orifice I04, the spray issuing at high pressures in a cone-shaped fog, the spray cone angle being determined by the angle of the cone-shaped head 9!.
  • remains seated and discharge is by way of small bores NH and low pressure discharge orifice I04, but as pressure builds up, discharge is principally through the high pressure discharge orifice 94 with a certain additional discharge through orifice I04, the spray issuing at high pressures in a cone-shaped fog, the spray cone angle being determined by the angle of the cone-shaped head 9!.
  • the velocity of the fuel is steppedup by the small bores l0! and small jet I04, while at higher pressures, the outer cone-shaped discharge orifice takes over,
  • burners of the type with which the present invention is primarily concerned are subject to a building up of reverberations, particularly at high air flows and rich fuel air ratios, which may reach an intensity such as to cause the burner flame to become extremely unstable and finally fail entirely; it is characterized by an irregular exhaust sound accompanied by an irregular flame length and a strong odor of unburnt fuel.
  • and 22 of Figure 1, 52 of Figure 2, or 16 and 11 of Figure 4 may have an individual resonance frequency which is variable in direct relation to the volume of the resonance chamber and the area of its air-inlet and discharge ports,
  • Such resonance chamber while preferably having air-inlet and discharge ports, need only have the latter ports, or need only be in communication with the breech or main burner chamber to function as a reverberation dampener.
  • an outer shell defining an elongated combustion chamber provided with a fuel-discharge nozzle at one nd thereof, an end wall mounting said nozzl and having a series of calibrated air-inlet orifices of varying flow capacity arranged in generally annular formation with the orifices of lowest flow capacity located centrally of said wall and the remaining orifices progressively increasing in capacity as they approach the periphery of the wall, a plurality of spaced annuli projecting forwardly from said end Wall to provide flow passages for the air admitted through said orifices and at their inner ends terminating in spaced stepped relation with the shortest annulus surrounding said nozzle, and bafiles coacting with said annuli and adapted to reduce the velocity of the air flowing into the combustion chamber in the region of the nozzle through said calibrated air-inlet orifices.
  • an outer shell defining an elongated generally cylindrical combustion chamber provided with an end wall mounting a fuel-discharge nozzle, said end wall being provided with a series of calibrated airinlet orifices of varying area or flow capacity with the orifices of lowest flow capacity surrounding the nozzle and the remaining orifices progressively increasing in area as they approach the periphery of the wall, a plurality of substantially cylindrical walls projecting from said end wall and arranged in spaced substantially concentric formation and at their inner ends terminating in stepped relation with the shortest annulus surrounding the nozzle, said annuli separating the inlet or breech end of the combustion chamber into a plurality of sub-chambers which tend to equalize the air flowin in through said air-inlet orifices, and baflie means coactlng with said latter chambers constructed and arranged to direct the air into the combustion chamber in masses of reduced and varying velocities with the mass of lowest velocity in the immediate leg of the
  • an outer shell defining a combustion chamber having a breech portion at one extremity thereof, a breech unit at the air-inlet end of said breech portion provided with an end wall formed with a plurality of radially spaced air-inlet openings, a series of radially-inwardly converging substantially cylindrical radially-spaced walls projecting forwardly from said openings and defining a plurality of air passages of gradually increasing cross-sectional area adapted to direct air into the breech portion of the combustion chamber, said passages receiving air from said inlet openings and producing an expansion efiect on the air as it flows therethrough to 'reduce the velocity thereof and diffuse the air as it passes into the said breech portion.
  • an outer substantially cylindrical shell defining a combustion chamber having an air inlet or breech portion at one extremity thereof, a breech unit at the air inlet end of said chamber made up of a series of outer substantially concentric cylinders and a central member having an end wall mounting a fuel spray nozzle, said outer I cylinders having their rear edges lying in the plane of said end wall and arranged in radiallyspaced relation to provide air-inlet openings, the walls of said cylinders projecting forwardly from said openings in axially converging formation and in progressively-increasing radially-spaced relation to define air inlet passages tending to expand the air entering the breech portion of the combustion chamber and reduce the velocity 5.
  • an outer substantially cylindrical shell defining a main combustion chamber having a breech portion at the air-inlet extremity thereof, a breech unit for controlling the supply of air to said chamber including an outer substantially cylindrical wall projecting forwardly in radiallyinwardly-curved formation into said breech portion, another substantially similarly shaped cylindrical wall arranged concentrically within said first-named cylindrical wall, said walls projecting forwardly in progressively radially-spaced relation to define a series of air-inlet passages of gradually increasing cross-sectional area which tend to expand the air and reduce the velocity thereof as it flows into the breech portion of the combustion chamber.
  • an outer shell defining a main combustion chamber having a breech portion at one extremity thereof, an end wall overlying the air-inlet end of said breech portion, a fuel spray nozzle located in said breech portion, a plurality of radially-spaced walls projecting forwardly from said end wall into said breech portion and defining a plurality of air chambers therebetween in restricted communication with said breech portion, a series of tangentially-disposed air-inlet passages for admitting air to said air chambers in a manner such as to produce a baflle effect on the air and at the same time facilitate distribution of the air in said latter chambers.
  • an outer substantially cylindrical shell defining a main combustion chamber having a breech portion at one extremity thereof, a breech unit mounted in the air inlet end of said shell and comprising an end wall lying in a plane generally normal to the axis of said combustion 10 chamber and a plurality of substantially cylindrical radially-spaced walls projecting forwardly from said end wall into said breech portion, said cylindrical walls defining a plurality of air chambers surrounding said breech portion and in restricted flow communication therewith, said end wall being provided with a series of tangentiallydisposed air-inlet holes for communicating air to said air chambers and at the same time produce a bave effect on the air and facilitate distribution thereof in said latter chambers, said shell being formed with a series of air inlet openings forwardly of said breech portion.

Landscapes

  • 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)
US640018A 1946-01-09 1946-01-09 Combustion chamber with air inlet means providing a plurality of concentric strata of varying velocities Expired - Lifetime US2616257A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US640018A US2616257A (en) 1946-01-09 1946-01-09 Combustion chamber with air inlet means providing a plurality of concentric strata of varying velocities
FR942149D FR942149A (fr) 1946-01-09 1947-01-09 Perfectionnements aux brûleurs

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US640018A US2616257A (en) 1946-01-09 1946-01-09 Combustion chamber with air inlet means providing a plurality of concentric strata of varying velocities

Publications (1)

Publication Number Publication Date
US2616257A true US2616257A (en) 1952-11-04

Family

ID=24566490

Family Applications (1)

Application Number Title Priority Date Filing Date
US640018A Expired - Lifetime US2616257A (en) 1946-01-09 1946-01-09 Combustion chamber with air inlet means providing a plurality of concentric strata of varying velocities

Country Status (2)

Country Link
US (1) US2616257A (fr)
FR (1) FR942149A (fr)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2712729A (en) * 1951-12-06 1955-07-12 Ruston & Hornsby Ltd Cooling systems of gas-turbines
US2729062A (en) * 1951-07-06 1956-01-03 Dresser Operations Inc Power plant combustion chamber
US2741090A (en) * 1949-06-30 1956-04-10 Rolls Royce Combustion equipment for gas-turbine engines with anticarbon wall portion
US2781756A (en) * 1952-04-26 1957-02-19 Kenneth A Kobe Apparatus for submerged combustion of liquid fuels
US2918118A (en) * 1954-08-30 1959-12-22 Phillips Petroleum Co Burner
US3045425A (en) * 1954-03-03 1962-07-24 Snecma Exhaust reheat equipment for gasturbine engines
US3075352A (en) * 1958-11-28 1963-01-29 Gen Motors Corp Combustion chamber fluid inlet construction
US3200589A (en) * 1961-11-03 1965-08-17 North American Aviation Inc Two stage baffled injector
US3601985A (en) * 1968-09-12 1971-08-31 Snecma Vibration damping device for a combustion chamber
US3643429A (en) * 1968-11-16 1972-02-22 Messerschmitt Boelkow Blohm Gas generator construction
US3707074A (en) * 1970-09-30 1972-12-26 Westinghouse Electric Corp Spontaneous ignition of fuel in a combustion chamber
US3726087A (en) * 1970-03-20 1973-04-10 Mini Of Aviat Supply Combustion systems
US3939653A (en) * 1974-03-29 1976-02-24 Phillips Petroleum Company Gas turbine combustors and method of operation
US4052844A (en) * 1975-06-02 1977-10-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Gas turbine combustion chambers
DE2730791A1 (de) * 1976-07-07 1978-01-19 Snecma Brennkammer fuer gasturbinentriebwerke
FR2406726A1 (fr) * 1977-10-21 1979-05-18 Rolls Royce Appareillage de combustion perfectionne pour moteur a turbine a gaz
US5163287A (en) * 1989-12-22 1992-11-17 Sundstrand Corporation Stored energy combustor with fuel injector containing igniter means for accommodating thermal expansion
WO1996004510A1 (fr) * 1994-08-01 1996-02-15 Bmw Rolls-Royce Gmbh Bouclier thermique pour chambre de combustion d'une turbine a gaz
US20140227142A1 (en) * 2012-05-04 2014-08-14 Institute For Advanced Engineering Non-melt and partial melt type entrained flow bed gasifier
US9228447B2 (en) 2012-02-14 2016-01-05 United Technologies Corporation Adjustable blade outer air seal apparatus

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1595224A (en) * 1977-02-04 1981-08-12 Rolls Royce Combustion equipment for gas turbine engines

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1370486A (en) * 1920-05-05 1921-03-01 Reid John Oil-burning-furnace front
US1458378A (en) * 1921-01-21 1923-06-12 Mckneat Mfg Company Oil burner
US1654403A (en) * 1926-08-04 1927-12-27 Harold S Blake Flame deflector for oil burners
US1990695A (en) * 1930-04-05 1935-02-12 U S Pressed Steel Company Oil-burning heater
US2000733A (en) * 1933-04-13 1935-05-07 Edgar T Avery Burner installation for domestic boilers
US2117270A (en) * 1935-06-29 1938-05-17 Fred S Bloom Apparatus for producing progressively delayed combustion
US2167183A (en) * 1936-11-14 1939-07-25 North American Mfg Gas burner
US2194081A (en) * 1938-07-28 1940-03-19 Bock Corp Ignition device
US2240161A (en) * 1938-11-05 1941-04-29 Borg Warner Oil burner
US2242797A (en) * 1938-02-26 1941-05-20 Babcock & Wilcox Co Method of and apparatus for burning fluid fuel
US2247768A (en) * 1936-08-06 1941-07-01 Huwyler Eugen Firing equipment for the combustion of liquid fuels
US2404395A (en) * 1942-12-14 1946-07-23 Milliken Humphreys Apparatus for converting heat energy into useful work
US2411181A (en) * 1943-04-10 1946-11-19 Allis Chalmers Mfg Co Combustion turbine burner
US2488218A (en) * 1943-01-15 1949-11-15 Thelma Mccollum Aircraft heater with plenum chamber acoustical damping means

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1370486A (en) * 1920-05-05 1921-03-01 Reid John Oil-burning-furnace front
US1458378A (en) * 1921-01-21 1923-06-12 Mckneat Mfg Company Oil burner
US1654403A (en) * 1926-08-04 1927-12-27 Harold S Blake Flame deflector for oil burners
US1990695A (en) * 1930-04-05 1935-02-12 U S Pressed Steel Company Oil-burning heater
US2000733A (en) * 1933-04-13 1935-05-07 Edgar T Avery Burner installation for domestic boilers
US2117270A (en) * 1935-06-29 1938-05-17 Fred S Bloom Apparatus for producing progressively delayed combustion
US2247768A (en) * 1936-08-06 1941-07-01 Huwyler Eugen Firing equipment for the combustion of liquid fuels
US2167183A (en) * 1936-11-14 1939-07-25 North American Mfg Gas burner
US2242797A (en) * 1938-02-26 1941-05-20 Babcock & Wilcox Co Method of and apparatus for burning fluid fuel
US2194081A (en) * 1938-07-28 1940-03-19 Bock Corp Ignition device
US2240161A (en) * 1938-11-05 1941-04-29 Borg Warner Oil burner
US2404395A (en) * 1942-12-14 1946-07-23 Milliken Humphreys Apparatus for converting heat energy into useful work
US2488218A (en) * 1943-01-15 1949-11-15 Thelma Mccollum Aircraft heater with plenum chamber acoustical damping means
US2411181A (en) * 1943-04-10 1946-11-19 Allis Chalmers Mfg Co Combustion turbine burner

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2741090A (en) * 1949-06-30 1956-04-10 Rolls Royce Combustion equipment for gas-turbine engines with anticarbon wall portion
US2729062A (en) * 1951-07-06 1956-01-03 Dresser Operations Inc Power plant combustion chamber
US2712729A (en) * 1951-12-06 1955-07-12 Ruston & Hornsby Ltd Cooling systems of gas-turbines
US2781756A (en) * 1952-04-26 1957-02-19 Kenneth A Kobe Apparatus for submerged combustion of liquid fuels
US3045425A (en) * 1954-03-03 1962-07-24 Snecma Exhaust reheat equipment for gasturbine engines
US2918118A (en) * 1954-08-30 1959-12-22 Phillips Petroleum Co Burner
US3075352A (en) * 1958-11-28 1963-01-29 Gen Motors Corp Combustion chamber fluid inlet construction
US3200589A (en) * 1961-11-03 1965-08-17 North American Aviation Inc Two stage baffled injector
US3601985A (en) * 1968-09-12 1971-08-31 Snecma Vibration damping device for a combustion chamber
US3643429A (en) * 1968-11-16 1972-02-22 Messerschmitt Boelkow Blohm Gas generator construction
US3726087A (en) * 1970-03-20 1973-04-10 Mini Of Aviat Supply Combustion systems
US3707074A (en) * 1970-09-30 1972-12-26 Westinghouse Electric Corp Spontaneous ignition of fuel in a combustion chamber
US3939653A (en) * 1974-03-29 1976-02-24 Phillips Petroleum Company Gas turbine combustors and method of operation
US4052844A (en) * 1975-06-02 1977-10-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Gas turbine combustion chambers
DE2730791A1 (de) * 1976-07-07 1978-01-19 Snecma Brennkammer fuer gasturbinentriebwerke
FR2406726A1 (fr) * 1977-10-21 1979-05-18 Rolls Royce Appareillage de combustion perfectionne pour moteur a turbine a gaz
US4271675A (en) * 1977-10-21 1981-06-09 Rolls-Royce Limited Combustion apparatus for gas turbine engines
US5163287A (en) * 1989-12-22 1992-11-17 Sundstrand Corporation Stored energy combustor with fuel injector containing igniter means for accommodating thermal expansion
WO1996004510A1 (fr) * 1994-08-01 1996-02-15 Bmw Rolls-Royce Gmbh Bouclier thermique pour chambre de combustion d'une turbine a gaz
US5956955A (en) * 1994-08-01 1999-09-28 Bmw Rolls-Royce Gmbh Heat shield for a gas turbine combustion chamber
US9228447B2 (en) 2012-02-14 2016-01-05 United Technologies Corporation Adjustable blade outer air seal apparatus
US10280784B2 (en) 2012-02-14 2019-05-07 United Technologies Corporation Adjustable blade outer air seal apparatus
US10822989B2 (en) 2012-02-14 2020-11-03 Raytheon Technologies Corporation Adjustable blade outer air seal apparatus
US20140227142A1 (en) * 2012-05-04 2014-08-14 Institute For Advanced Engineering Non-melt and partial melt type entrained flow bed gasifier
US9610557B2 (en) * 2012-05-04 2017-04-04 Institute For Advanced Engineering Non-melt and partial melt type entrained flow bed gasifier

Also Published As

Publication number Publication date
FR942149A (fr) 1949-01-31

Similar Documents

Publication Publication Date Title
US2616257A (en) Combustion chamber with air inlet means providing a plurality of concentric strata of varying velocities
US2517015A (en) Combustion chamber with shielded fuel nozzle
US2398654A (en) Combustion burner
US2541900A (en) Multiple fuel jet burner and torch igniter unit with fuel vaporizing tubes
US3030773A (en) Vortex type combustion with means for supplying secondary air
US2602292A (en) Fuel-air mixing device
US3998581A (en) Gaseous fuel burners
US2864234A (en) Igniter for gas turbine engines
USRE23149E (en) Combustion burner
US3194295A (en) Hot gas generating installation
US2958196A (en) Flame igniter for gas turbine combustor
US5491972A (en) Combination igniter and fuel atomizer nozzle assembly for a gas turbine engine
US3847534A (en) Combustion apparatus
US3007310A (en) Combustion chamber with vorticity of the combustible mixture
US2482394A (en) Gas turbine
US2720754A (en) Flameholder for ram jet engine
US2548087A (en) Vaporizer system for combustion chambers
US2659195A (en) Flame holder and fuel distributing mechanism for ram-jet engines
US2480147A (en) Firing device for combustion apparatus
US2685168A (en) Combustion chamber
US3320744A (en) Gas turbine engine burner
CN108757220A (zh) 一种后端点火的脉冲爆震燃烧发动机
GB723010A (en) Improvements in or relating to combustion apparatus
GB624779A (en) An improved burner for gaseous, liquid or powdered solid fuel
US5115637A (en) External cartridge gas combustor ignitor