US2720753A - Combustion apparatus - Google Patents

Combustion apparatus Download PDF

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Publication number
US2720753A
US2720753A US237375A US23737551A US2720753A US 2720753 A US2720753 A US 2720753A US 237375 A US237375 A US 237375A US 23737551 A US23737551 A US 23737551A US 2720753 A US2720753 A US 2720753A
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Prior art keywords
duct
combustion
fuel
combustion chamber
main
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Expired - Lifetime
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US237375A
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English (en)
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Sharpe Alan
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Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • 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

Definitions

  • This invention relates to combustion apparatus in which combustion of liquid fuel is required to be supported by a stream of air or other gas (hereinafter referred to as air) owing through a duct with a flame-extinguishing velocity and its primary object, stated in general terms, is the provision of such an apparatus which will oder the possibility of eiective and eilicient combustion over a wide range of operating conditions.
  • the invention has particular application to the supporting of continuous combustion by means of such a fast moving air current involving a large mass flow, as for example, in gas turbine or other jet propulsion power units and in gas turbines for other purposes.
  • flame-extinguishing velocity is used here to indicate that the mean speed of the stream in its general direction of flow through the duct, calculated from the ratio of the air volume passing in unit time to the cross-sectional area of flow path, is substantially higher than the speed of ame propagation in the fuel-air mixture concerned.
  • the speed of llame propagation is considered as being of the order of one foot per second at atmosphere temperature; the invention, on the other hand, is especially applicable to combustion apparatus for so-called ram-jet propulsion power units, as well as to other jet propulsion units and to gas turbine power units in general, in which the general velocity of the air stream calculated on the basis indicated, might be of an order as low as l or as high as 500 feet per second or even more, depending on the design.
  • a common practice in gas turbine and similar combustion systems is to inject liquid fuel droplets into an almost stagnant region which is protected by a bave from the full blast eiect of the air ow, specially designed atomizing injection nozzles, or impact surfaces arranged in the path of the fuel jet, being provided to achieve satisfactory atomization of the fuel; fuel once ignited in this stable zone will continue to burn and ignite further incoming fuel.
  • a combustion apparatus in which combustion has to be supported by a ducted air ow of flame-extinguishing velocity and in which means are provided for forming in the flow a stabilized llame wherein fuel droplets and a 2,720,753 Patented Oct.
  • the mixing duct is co-axial with and occupies a central region of the main duct carrying the main airstream and is in the form of a diffuser whereby the velocity of the primary air is reduced as it moves downstream through said mixing duct, fuel being injected (preferably downstream) into said mixing duct at the region of its upstream end, i. e. at a region of high velocity.
  • fuel being injected (preferably downstream) into said mixing duct at the region of its upstream end, i. e. at a region of high velocity.
  • the ow of unburnt fuel and primary air is reversed in direction to pass upstream through the vaporizing duct and may be accelerated on its path through this duct by the provision of swirl vanes therewithin.
  • the ow of the fuel-air mixture is again reversed in direction and led into a primary combustion zone in the combustion chamber around the vaporizing duct, and at this region the velocity of the fuel-air mixture is greatly reduced to assist flame stabilization.
  • the burning gases then ow downstream from the combustion zone towards the outlet to the main duct and are preferably accelerated so that they finally emerge into the main duct at high velocity. Downstream of this outlet the remainder of the main airstream mixes at high velocity with the burning gases to complete combustion and/ or to cool the gases.
  • FIG. 1 A detailed view of the combustion apparatus according to the invention, in axial section, is shown in Fig. 1 of the accompanying drawing While external views of a cylindrical combustion apparatus and an annular combustion apparatus respectively are shown in Figs. 2 and 3.
  • the main duct may be a cylindrical tube 1 as in Fig. 2 or an annular duct 21 as shown in Fig. 3.
  • the device according to the invention is a pilot burner located in the duct upstream of the main fuel supply.
  • the pilot fuel supply connection is shown at 22, the main fuel supply connection at 23 and the terminals of an ignition sparking-plug at 24 in all iigures.
  • the inlet for the air (or other combustion-supporting gas) stream is at the left-hand end of each iigure and the outlet for combustion product gases at the right-hand end.
  • Figs. 2 and 3 are each partly broken away to show the interior; Fig. 1 is an enlarged sectional view showing how this revealed part looks in both cases.
  • the main airstream carried in the main duct 1 is divided into two parts by a tubular combustion chamber l1 mounted concentrically therein, part of the air flowing through an annulus 2 between duct 1 and the combustion chamber while another part of the air ows through the pilot burner device incorporated in the combustion chamber 11.
  • the main combustion zone is dened by the main duct 1 downstream of the main fuel injector 15, the upstream limit of this zone being indicated at 25.
  • Concentrically mounted within the combustion chamber 11 is a tubular mixing duct 3 which is a diffuser progressively increasing in diameter from the inlet at an upstream position in the main duct 1 to the outlet further downstream.
  • the combustion chamber is open at the downstream end; the mixing duct 3 is shown as con- 3 s stitutcd by a concentrirdivergent re-entrant portion of the combustion chamber 11, Yjoined to the outer Wall of chamber 11 by the smoothlj curved end wall 9 at the end ojf the inlet tothe mixing duct 3.
  • the injector 4 can be of the ordinaryswirl atomizer type, because the conical jet of swirling droplets which issues from this type gives a good distribution of the droplets Y across the cross-section; this good distribution is' important although with this invention a high degree of atomization is not necessary.
  • vanes ⁇ S are swirl vanes whereby the fuel-air mixture is rotated around the axis of the system on' its path upstream.
  • the ow of the fueleair mixture is again reversed by means of the curved walls 9 which define a primary combustion zone -10 in which the' velocity of new is reduced so that a stabilized llameV can beV formed, 'as explained below. From here the burning gases can travel downstream again through the space I2 in the cor'nbustionV chamber outside the vaporizing duct 7.
  • the Variation in cross-section of the space 12 isA such as to increase the velocity of the burning gases as Vthey move downstream towards the outlet 13 of the combustion chamber' 11 where the burning gases mix with the remainder of the airstream owing atY high speed through the spaceZ and combustion isY completed in the downstream portion of the main duct 1.
  • the vaporizing duct 7 is of Vsubstantially the same length as the mixing duct 3 so that the outlet from the vaporizing duct into space 10 is in theY same region as and disposed around the inlet vto the mixing duct 3; the combustion chamber 11 is also of about the same length, the outlet end of the mixing duct 3 and the closed end of the vaporizing duct 7 being both adjacent to the outlet end 13 of the combustion chamber.
  • the flame issuing from the'outlet 13 serves as a pilot flame for main fuel injected into the main duct 1, for example from a series of fuel nozzles provided symmetrically around the outlet 13 by the annular fuel tube 15 having the previously-mentioned fuel-supply connection 23 and shown with three sets of nozzle'apertures 15a, i5bv and 15c Y directing fuel jets perpendicularly across the duct,V upstream and downstream respectively; only such of these sets as are desired need be provided.
  • the combustion apparatus set forth may be used for various purposes. fit may be the essential part of a ram-jet evice, it may beV connected between the compressor Vand the turbine of a gasturbine plant or in a jetpropulsion gas-turbine plant it may be connected to the end of the exhaust p'ipe of a gas-turbine as a jet pipe, with re-heating by after burning'.
  • a combustion device for burning liquid fuel droplets carried in a gas stream comprising a combustion chamber, .Y a vaporising duct within and extending along said combus-V tion chamber and having an outlet into said chamber, and
  • a mixing duct within and extending along said vaporising duct having at one end an inlet openV to receive the liquid carrying gas stream and at the other end an outletintoV said vaporising duet, said' chamber and ducts together defining a now path for the gas stream which passes along the interior of said mixing duct to the outlet thereof, reverses direction to pass along said vaporising duct outside the mixing duct to said outletof the vaporising duct, and then reverses again into and along said combustion chamber outside said vaporising duct, and ignition means in said combustion chamber for initiating combustion therein and accordingly, by heat transfer to the gas stream nowing through said vaporising duct, vaporising thefuel carried therein, wherein said combustion chamber and ducts are so dimensioned that the part of said flow path defined withinV said vaporising duct outsidesaid mixing duct has in any transverse section plane a ow area less-than either the transverse ow area of said mixing ducty at the outlet' thereof or the flow area of said combustion chamber in a transverse plane
  • a combustion device for burning liquid fuel droplets carriedin a gas stream comprising a combustion chamber, a vaporising duct'rwithin and extending along said combustion chamber and having an outlet intosaid chamber, and a mixing duct within and extending along said vaporising duct having at one end an inletV open to receive the liquid carrying .gas stream and at the other end an outlet into said Vaporising duct, said chamber and duct together delining a now path for the gas stream which passes along the interior of said mixing duct to the outlet thereof, re- Verses directed onto pass along said vaporising ⁇ duct out-4 side the mixing duct to said outlet of the vaporising duct, and then reverses again into and along said combustion chamber outside said vaporising duct, and ignition means in said combustion chamber for initiating combustion therein and accordingly, by heat transfer to the gas stream flowing through said vaporising duct, vaporising the fuel carried therein, wherein said combustion chamber and ducts are so dimensioned that the part of said ow path defined within said vaporising
  • a combustion apparatus wherein liquid fuel is to be burnt in a high-velocity stream of combustion-supporting gas comprising, in combination, of a main duct for the gas stream, a burner device connected to receive part of said stream from one region of the main duct and to discharge said part into the rest of the ow in a region of said main duct lower down stream, and an injector located in said main duct for injecting fuel droplets into said part of the stream, wherein the burner device is made up of a combustion chamber with an outlet end discharging into the main duct at said last mentioned region, a vaporizing duct within and extending along the combustion chamber, and a mixing duct Within and extending along the vaporizing duct with an inlet end open to receive gas from the main duct at said rst mentioned region, the whole burner device defining a ow path which passes along the interior of the mixing duct, reverses direction to pass along the vaporizing duct, outside the mixing duct, and then reverses again into and along the combustion chamber outside the vapor
  • a combustion apparatus in which said burner device is a pilot burner and there is a main injector located to inject fuel droplets into the main duct in the path of the gas rejoined by gas from the said pilot burner.
  • a combustion apparatus having the said burner device located within and extending along the main duct, the inlet end of the mixing duct directed upstream and the outlet end of the combustion chamber directed downstream, with clearance space around the outside of the burner for the passage of that part of the gas stream which does not go through the burner.
  • a combustion apparatus in which combustion of liquid fuel is to be supported by a high-velocity gas stream, comprising, in combination, of a main duct for the gas stream, a cylindrical burner device lying centrally along the said main duct to afford one path for part of the gas through the burner device and another path for the rest of the gas over the outside of the burner device, and a fueldroplet injector within the main duct in the region of the upstream end of the burner device, the burner device being made up of a tubular combustion chamber open at the downstream end, a tubular mixing duct, open at the downstream and upstream ends, constituted by a concentric, divergent, re-entrant tubular portion of the combustion chamber, and a vaporizing tube, closed at the end thereof downstream with respect to the direction of ow of the gas stream in said main duct but open at the upstream end, concentrically within the combustion chamber enveloping the mixing duct but with said closed downstream end spaced from the mixing duct, the interior of the burner device thus defining a flow path from the

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
US237375A 1950-07-27 1951-07-18 Combustion apparatus Expired - Lifetime US2720753A (en)

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Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2878790A (en) * 1954-11-10 1959-03-24 Snecma Intermittent combustion boiler
US2922279A (en) * 1956-02-02 1960-01-26 Power Jets Res & Dev Ltd Combustion apparatus and ignitor employing vaporized fuel
US2927427A (en) * 1955-05-10 1960-03-08 Onera (Off Nat Aerospatiale) Continuous flow thermal machines and in particular in ram-jets and turbojets
US2949012A (en) * 1957-03-01 1960-08-16 Snecma Vaporisation burner device
US2952126A (en) * 1955-05-10 1960-09-13 Midland Ross Corp Combustion unit for supplying hot gas for jet aircraft
US2955420A (en) * 1955-09-12 1960-10-11 Phillips Petroleum Co Jet engine operation
US2958189A (en) * 1955-05-31 1960-11-01 Phillips Petroleum Co Method and apparatus for providing improved combustion in jet engines
US2974478A (en) * 1954-04-30 1961-03-14 Sweet Fluid flow energy transformer
US2997847A (en) * 1957-12-20 1961-08-29 Hollingsworth R Lee Combustion engines for rockets and aeroplanes
US3024606A (en) * 1958-07-10 1962-03-13 Curtiss Wright Corp Liquid cooling system for jet engines
DE1139330B (de) * 1957-12-20 1962-11-08 Snecma Brennervorrichtung fuer im Gleichstrom arbeitende Strahltriebwerke
US3066926A (en) * 1959-04-23 1962-12-04 Air Prod & Chem Air heating method
US3067582A (en) * 1955-08-11 1962-12-11 Phillips Petroleum Co Method and apparatus for burning fuel at shear interface between coaxial streams of fuel and air
US3073583A (en) * 1960-10-28 1963-01-15 John Wood Company Heater
US3079755A (en) * 1955-12-27 1963-03-05 Thompson Ramo Wooldridge Inc Propelling device and method
US3391535A (en) * 1966-08-31 1968-07-09 United Aircraft Corp Burner assemblies
US3398528A (en) * 1965-10-05 1968-08-27 Ishikawajima Harima Heavy Ind Evaporation type burner
US3407596A (en) * 1967-03-15 1968-10-29 Navy Usa Prevaporizing burner can
US4040252A (en) * 1976-01-30 1977-08-09 United Technologies Corporation Catalytic premixing combustor
US4541239A (en) * 1983-06-20 1985-09-17 Nissan Motor Company, Ltd. Exhaust purification apparatus
US5076061A (en) * 1989-12-15 1991-12-31 Sundstrand Corporation Stored energy combustor
US20040195397A1 (en) * 2003-03-20 2004-10-07 Ansis Upatnieks Ejector device for direct injection fuel jet
US20150033749A1 (en) * 2013-07-30 2015-02-05 General Electric Company System and method of controlling combustion and emissions in gas turbine engine with exhaust gas recirculation

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190426178A (en) * 1904-12-01 1906-03-01 Adolf Vogt Improvements in Apparatus for Producing Combustion Gases under Pressure for use as Motive Power for Driving Turbines and the like, and Means in Combination therewith for Producing a Liquid Jet.
US1052588A (en) * 1911-04-12 1913-02-11 John Janicki Hydrocarbon power-generator.
DE609403C (de) * 1932-02-09 1935-02-14 Julius Hermann Klemt Verfahren zur Kuehlung des Brennraumes fuer eine nur teilweise Verbrennung eines gasfoermigen oder fluessigen Brennstoffes, insbesondere fuer eine Anlage zur Erzeugung von Druckmittel fuer Expansionskraftmaschinen
GB603918A (en) * 1944-11-30 1948-06-25 Oerlikon Maschf Improvements in or relating to combustion chambers for gas turbine plants
US2520388A (en) * 1946-11-21 1950-08-29 Power Jets Res & Dev Ltd Apparatus for supporting combustion in fast-moving air streams
US2525206A (en) * 1944-12-13 1950-10-10 Lucas Ltd Joseph Multiple truncated conical element combustion chamber
US2565308A (en) * 1945-01-17 1951-08-21 Research Corp Combustion chamber with conical air diffuser
US2628475A (en) * 1946-06-26 1953-02-17 Socony Vacuum Oil Co Inc Jet combustion device embodying pretreatment of fuel before combustion

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190426178A (en) * 1904-12-01 1906-03-01 Adolf Vogt Improvements in Apparatus for Producing Combustion Gases under Pressure for use as Motive Power for Driving Turbines and the like, and Means in Combination therewith for Producing a Liquid Jet.
US1052588A (en) * 1911-04-12 1913-02-11 John Janicki Hydrocarbon power-generator.
DE609403C (de) * 1932-02-09 1935-02-14 Julius Hermann Klemt Verfahren zur Kuehlung des Brennraumes fuer eine nur teilweise Verbrennung eines gasfoermigen oder fluessigen Brennstoffes, insbesondere fuer eine Anlage zur Erzeugung von Druckmittel fuer Expansionskraftmaschinen
GB603918A (en) * 1944-11-30 1948-06-25 Oerlikon Maschf Improvements in or relating to combustion chambers for gas turbine plants
US2525206A (en) * 1944-12-13 1950-10-10 Lucas Ltd Joseph Multiple truncated conical element combustion chamber
US2565308A (en) * 1945-01-17 1951-08-21 Research Corp Combustion chamber with conical air diffuser
US2628475A (en) * 1946-06-26 1953-02-17 Socony Vacuum Oil Co Inc Jet combustion device embodying pretreatment of fuel before combustion
US2520388A (en) * 1946-11-21 1950-08-29 Power Jets Res & Dev Ltd Apparatus for supporting combustion in fast-moving air streams

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2974478A (en) * 1954-04-30 1961-03-14 Sweet Fluid flow energy transformer
US2878790A (en) * 1954-11-10 1959-03-24 Snecma Intermittent combustion boiler
US2927427A (en) * 1955-05-10 1960-03-08 Onera (Off Nat Aerospatiale) Continuous flow thermal machines and in particular in ram-jets and turbojets
US2952126A (en) * 1955-05-10 1960-09-13 Midland Ross Corp Combustion unit for supplying hot gas for jet aircraft
US2958189A (en) * 1955-05-31 1960-11-01 Phillips Petroleum Co Method and apparatus for providing improved combustion in jet engines
US3067582A (en) * 1955-08-11 1962-12-11 Phillips Petroleum Co Method and apparatus for burning fuel at shear interface between coaxial streams of fuel and air
US2955420A (en) * 1955-09-12 1960-10-11 Phillips Petroleum Co Jet engine operation
US3079755A (en) * 1955-12-27 1963-03-05 Thompson Ramo Wooldridge Inc Propelling device and method
US2922279A (en) * 1956-02-02 1960-01-26 Power Jets Res & Dev Ltd Combustion apparatus and ignitor employing vaporized fuel
US2949012A (en) * 1957-03-01 1960-08-16 Snecma Vaporisation burner device
DE1139330B (de) * 1957-12-20 1962-11-08 Snecma Brennervorrichtung fuer im Gleichstrom arbeitende Strahltriebwerke
US2997847A (en) * 1957-12-20 1961-08-29 Hollingsworth R Lee Combustion engines for rockets and aeroplanes
US3024606A (en) * 1958-07-10 1962-03-13 Curtiss Wright Corp Liquid cooling system for jet engines
US3066926A (en) * 1959-04-23 1962-12-04 Air Prod & Chem Air heating method
US3073583A (en) * 1960-10-28 1963-01-15 John Wood Company Heater
US3398528A (en) * 1965-10-05 1968-08-27 Ishikawajima Harima Heavy Ind Evaporation type burner
US3391535A (en) * 1966-08-31 1968-07-09 United Aircraft Corp Burner assemblies
US3407596A (en) * 1967-03-15 1968-10-29 Navy Usa Prevaporizing burner can
US4040252A (en) * 1976-01-30 1977-08-09 United Technologies Corporation Catalytic premixing combustor
US4541239A (en) * 1983-06-20 1985-09-17 Nissan Motor Company, Ltd. Exhaust purification apparatus
US5076061A (en) * 1989-12-15 1991-12-31 Sundstrand Corporation Stored energy combustor
US20040195397A1 (en) * 2003-03-20 2004-10-07 Ansis Upatnieks Ejector device for direct injection fuel jet
US7051956B2 (en) * 2003-03-20 2006-05-30 Sandia Naitonal Laboratories Ejector device for direct injection fuel jet
US20150033749A1 (en) * 2013-07-30 2015-02-05 General Electric Company System and method of controlling combustion and emissions in gas turbine engine with exhaust gas recirculation
US9903588B2 (en) * 2013-07-30 2018-02-27 General Electric Company System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation

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