US2901032A - Combustion apparatus - Google Patents

Combustion apparatus Download PDF

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Publication number
US2901032A
US2901032A US548491A US54849155A US2901032A US 2901032 A US2901032 A US 2901032A US 548491 A US548491 A US 548491A US 54849155 A US54849155 A US 54849155A US 2901032 A US2901032 A US 2901032A
Authority
US
United States
Prior art keywords
combustion
shell
air
fins
shell member
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
US548491A
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English (en)
Inventor
Brola Gabriel
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.)
GEN THERMIQUE PROCEDES BROLA S
GENERALE THERMIQUE-PROCEDES BROLA SA
Original Assignee
GEN THERMIQUE PROCEDES BROLA S
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 GEN THERMIQUE PROCEDES BROLA S filed Critical GEN THERMIQUE PROCEDES BROLA S
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Publication of US2901032A publication Critical patent/US2901032A/en
Anticipated expiration legal-status Critical
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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid

Definitions

  • An object of the invention is to provide an improved form of combustion chamber which will be capable of developing high amounts of heat for a given volume.
  • the quantity of heat developed per unit sectional area of a combustion chamber is substantially proportional to the volume of the combustion gases therein, or otherwise stated, to the product of the combustion rate and the total area of the flame front of the combustion gases.
  • Objects of the invention accordingly, are to increase both the rate of combustion and the flame front area in order to increase the amount of generated heat.
  • Further objects are to provide improved combustion apparatus in which the fuel injecting and ignition means are located outside the combustion chamber and are hence protected from the high temperatures prevailing therein. Further objects are to preheat the combustion air, increase the combustion temperature, and promote the cooling of the walls of the combustion apparatus, using forthis purpose the simultaneous effects of combustion airflow, radiation, and conductivity effects. Further objects will appear as the description proceeds.
  • .improved combustion apparatus comprises a concave shell member, means for discharging fuel and air into said shell member and for ignition of said fuel, means defining an annular wall coaxial with the shell member and spaced from the periphery thereof, and a plurality of angularly spaced finlike elements interconnecting the shell periphery with said annular wall and defining auxiliary air inlet passages between said elements.
  • the shell member may be formed with an axial main air inlet aperture having reentrant side walls defining a convergent inlet nozzle for imparting a high velocity of flow to the primary air entering the chamber through said inlet.
  • the fuel is injected axially of this inlet, and the rfuel injector nozzle and associated ignition device can thus be located outside the chamber due in particular to the high flow velocity, whereby the flame is prevented from moving back toward the injector nozzle outlet.
  • the shell is formed with space ports therein for supplying secondary air, and these ports are preferably likewise formed with an inwardly convergent shape.
  • the fin-like elements are preferably formed with concave base surfaces directed towards the common axis of .the shell member and the annular wall member to receive and partly reflect back heat radiated therefrom, and said elements taper outwards into the auxiliary airflow, which sweeps past the extensive side walls of said elements, there promoting eflicient withdrawal both of the part of said radiated heat absorbed by the fins, and of the heat transferred to said fins from the shell member by conductivity.
  • the tempera- 2 ture of the combustion gases is. increased by reflected radiation from the base surfaces of the fins, and simultaneously the fins and other wall portions of the apparatus are effectively cooled and the combustion air-flow is preheated.
  • the fin-like elements of the invention have another important function. When correctly shaped in a manner later describd in detail, they are found to create a number of vortices in alternate directions, which exert a stabilizing action on the flame front and impart to it a wavy or undulating configuration in cross section that serves greatly to increase its effective surface area, as compared to the usual cylindrical or flat or part-spherical flame front pattern obtained in conventional combustion chambers. Increasing the flame front area, as previously indicated herein, .acts to increase the quantity of heat evolved by a chamber of given size.
  • the rate of combustion is also increased as a result of the energetic pre-heating of the carburized mixture by the walls of the shell, which reduces the time required to vaporizethe fuel droplets and hence the time required for the entire mass of fuel in a given period to reach a state of ignition. Increase of the combustion rate decreases the length of the flame and thus again results in. a decrease in the longitudinal dimension of the chamber required to ensure complete combustion.
  • Fig. 1 is an axial cross sectional view of the improved combustion apparatus
  • Fig. 2 is a cross sectional developed view of the fins thereof;
  • Fig. 3 is an overhead perspective view of the apparatus
  • the improved combustion apparatus comprises a concave shell 1 made of any suitable highly-refractory material, and formed with an axial opening 2 around which the shell wall curves inwardly to provide a nozzle-like entrance.
  • the shell 1 may have anysuitable configuration in axial cross section e.g. it may be approximately hemi-spherical or paraboloidal.
  • a plurality of ports such as 3, 4, 5 which are preferably provided with flared or chamfered ends outwards of the shell.
  • each fin 6 is illustrated in developed cross sectional view in Fig. 2, from which it will be seen that each fin has a generally triangular cross sectional shape in planes generally parallel with the outer conical surface of the rim 7.
  • the apices 8 of the fins i.e. their upper ends as seen in Fig. 1, are rounded, while their bases 24 i.e. their lower ends according to Fig. 1,. are concave and are defined by sharp edges or apices 9 and 10.
  • the assembly comprising the shell 1, fins 6 and rim 7 is mounted in the end of a tubular member 12 made of refractory material, with the frustoconical outer surface of the rim 7 seated against a complementary frusto conical surface formed in a thickened end portion 13 of the tubularmember, which defines a throat or restriction substantially on a level with the base of the fins.
  • tubular member 12 is inserted in an aperture formed in one wall of a conduit or casing 25 and is secured therein by any suitable means, so that the outer convex side of the shell 1 projects into the inner space defined between the walls of the member 25, which is arranged for delivery of primary combustion air to the apparatus.
  • a fuel injector nozzle 14 mounted in the opposite wall of the member 25 is a fuel injector nozzle 14 projecting axially towards the entrance aperture 2 into the shell 1, but extending short of said aperture.
  • an ignition member or sparking plug 15 mounted in said wall next to the injection nozzle is an ignition member or sparking plug 15 connected to a suitable source of voltage, and projecting to a point adjacent the outlet of injection nozzle 14 forwardly thereof.
  • the combustion apparatus operates as follows:
  • Combustion air enters the shell 1 partly through the wide central entrance nozzle 2 and through the ports 3, 4 and 5 to provide the primary and secondary airflow, respectively, and partly through the spaces 11 between thefins 6, as indicated by an arrow in Fig. 1, to provide a tertiary airflow.
  • the primary air drawn in through the central aperture 2 becomes mixed with the pulverized fuel from injection nozzle 14 and immediately forms a combustible charge therewith which is ignited by ignition device 15 before the charge has even penetrated the combustion chamber, in the area of nonturbulent, high-velocity flow determined by the entrance nozzle 2. Owing to the high flow velocity of the combustible charge in this area, the flame front istprevented from moving ba k towards the outlet of the injector nozzle 14. It will be observed that in this arrangement the injection nozzle and ignition device are mounted outside the combustion chamber and are not subjected to the high temperatures developed therein, so that their service life is considerably lengthened. V
  • the partially or wholly ignited charge entering the chamber forms a plurality of high-velocity vortices disposed in an annular array Within the shell 1, somewhat in the manner indicated by the lines 16, thereby promoting an intimate mixing of the burning mixture with any non ignited fuel droplets that may be present, and with the secondary air entering the lateral ports 3, 4, 5.
  • the inner space of the shell 1 becomes filled with a body of gas in substantially uniform combustion which tends to project therefrom into the tubular member 12, where the combustion continues with the additional or tertiary air delivered through the spaces 11 between the fins.
  • the flame front becomes stabilized in the area adjacent the bases of the radial fins 6. This is explained by the fact that the air-flow entering through the spaces 11 divides into a plurality of vortices such as 17 (Fig. 2) alternately directed in opposite directions, which act so to speak to catch the flame and bond or stabilize the periphery of the flame front in that area.
  • combustion continues at a high rate within the tube 12 so that its side walls are carried by radiation to a high temperature thereby further accelerating the rate of combustion within it, the combustion being completely terminated as the gases issue from the opposite end of the comparatively short tube.
  • the array of fins 6 shaped as disclosed above perform an important heat exchange function. This is because the comparatively large laterial areas such as 18 and 19 (Fig. 2) of the fins are swept by the cool airflow from the space 25, while the smaller base areas 20 thereof are directly exposed to the radiation from the burning mass, and this radiation effect is enhanced by the concave form imparted to said base areas as stated earlier.
  • the heat supplied to the shell 1 and transferred to the fins by conduction is effectively removed by the cool air sweeping across the sides of the fins, together with the heat transferred to the inner fin surfaces by radiation as mentioned above.
  • An extremely efiicient cooling effect is obtained by the tertiary airflow supplied between the fins. At the same time the airflow is preheated, and the temperature within the space 12 is further increased by reflection from the concave base surfaces of the fins.
  • a concave-convex shell member having a centrally located axial air-inlet aperture, an injector nozzle located outside of said shell member at the convex side of the latter and aligned axially with said air-inlet aperture for injecting divided fuel into said shell member through said air inlet aperture, ignition means for igniting the divided fuel issuing from said injector nozzle, said shell member further having openings therein for the admission of secondary air, a finsto-conical annular wall extending coaxially around said shell member and spaced radially from the latter with said annular wall converging in the direction in which said shell member is concave, and a plurality of angularly spaced fin elements extending radially between said shell member and said annular wall to define air-inlet passages for tertiary air between the successive elements, each of said elements being symmetrical about a plane which includes at least one line extending radially with respect to the axis of said shell member, each of said elements

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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)
US548491A 1954-11-24 1955-11-22 Combustion apparatus Expired - Lifetime US2901032A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1115481T 1954-11-24

Publications (1)

Publication Number Publication Date
US2901032A true US2901032A (en) 1959-08-25

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Family Applications (1)

Application Number Title Priority Date Filing Date
US548491A Expired - Lifetime US2901032A (en) 1954-11-24 1955-11-22 Combustion apparatus

Country Status (4)

Country Link
US (1) US2901032A (en(2012))
FR (1) FR1115481A (en(2012))
GB (1) GB793325A (en(2012))
NL (1) NL98183C (en(2012))

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3026675A (en) * 1958-08-22 1962-03-27 Snecma Device for the air intake into the primary zone of a combustion chamber in a turbo-machine
US3080715A (en) * 1959-04-28 1963-03-12 Rolls Royce Combustion chamber
US3130773A (en) * 1959-05-04 1964-04-28 Drake Block Co Inc Air-cooled burner ring
US3169369A (en) * 1963-06-19 1965-02-16 Gen Electric Combustion system
US3273343A (en) * 1965-03-08 1966-09-20 Dickens Inc Combustion chamber construction in gas turbine power plant
US3304982A (en) * 1964-07-09 1967-02-21 H B Smith Company Inc Windbox for furnace
US3414362A (en) * 1966-04-15 1968-12-03 F Schoppe Dr Ing Burner for firing a combustion chamber
US3700173A (en) * 1970-12-30 1972-10-24 Combustion Eng Diffuser
US3792581A (en) * 1970-12-22 1974-02-19 Nissan Motor System and method used in a gas turbine engine for minimizing nitrogen oxide emission
US5149261A (en) * 1985-11-15 1992-09-22 Nippon Sanso Kabushiki Kaisha Oxygen heater and oxygen lance using oxygen heater
US20030152878A1 (en) * 1997-11-10 2003-08-14 Staffler Franz Josef Streamlined body and combustion apparatus
US20050026096A1 (en) * 2001-11-23 2005-02-03 Staffler Franz Josef Streamlined body and combustion apparatus having such a streamlined body
US20060174626A1 (en) * 2005-02-09 2006-08-10 Snecma Shroud for a turbomachine combustion chamber
US20100015562A1 (en) * 2008-07-16 2010-01-21 Babington Robert S Perforated flame tube for a liquid fuel burner
US20120085420A1 (en) * 2010-10-07 2012-04-12 Carrier Corporation Inshot burner flame retainer
US20130089826A1 (en) * 2011-10-11 2013-04-11 Keisuke Mori Tubular burner

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1166664A (fr) * 1957-02-05 1958-11-13 Perfectionnements aux chambres de combustion utilisables, notamment, dans les réacteurs
GB2043868B (en) * 1979-03-08 1982-12-15 Rolls Royce Gas turbine
US5267851A (en) * 1992-03-16 1993-12-07 General Electric Company Swirl gutters for isolating flow fields for combustion enhancement at non-baseload operating conditions
CA2089272C (en) * 1992-03-23 2002-09-03 James Norman Reinhold, Jr. Impact resistant combustor
US5256352A (en) * 1992-09-02 1993-10-26 United Technologies Corporation Air-liquid mixer
CH687832A5 (de) * 1993-04-08 1997-02-28 Asea Brown Boveri Brennstoffzufuehreinrichtung fuer Brennkammer.

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1665786A (en) * 1924-06-16 1928-04-10 Morse Dry Dock & Repair Co Furnace front
DE547338C (de) * 1932-03-31 Babcock & Wilcox Dampfkessel W Kohlenstaubbrenner
CH178351A (de) * 1934-07-02 1935-07-15 Brevo A G Fuer Explosions Und Zerstäubungsbrenner für flüssigen Brennstoff.
US2411181A (en) * 1943-04-10 1946-11-19 Allis Chalmers Mfg Co Combustion turbine burner
US2689457A (en) * 1949-03-15 1954-09-21 Hermann Oestrich Burner, particularly for gas turbines
US2693083A (en) * 1951-03-26 1954-11-02 Roy W Abbott Combination flame-holder and fuel nozzle
US2701608A (en) * 1951-02-03 1955-02-08 Thermal Res And Engineering Co Burner
CA510584A (en) * 1955-03-01 C. Benedict Marcus Adjustable flame holder for jet power plant
US2725718A (en) * 1950-04-10 1955-12-06 Goodyear Aircraft Corp Ignition systems for jet motors and the like

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE547338C (de) * 1932-03-31 Babcock & Wilcox Dampfkessel W Kohlenstaubbrenner
CA510584A (en) * 1955-03-01 C. Benedict Marcus Adjustable flame holder for jet power plant
US1665786A (en) * 1924-06-16 1928-04-10 Morse Dry Dock & Repair Co Furnace front
CH178351A (de) * 1934-07-02 1935-07-15 Brevo A G Fuer Explosions Und Zerstäubungsbrenner für flüssigen Brennstoff.
US2411181A (en) * 1943-04-10 1946-11-19 Allis Chalmers Mfg Co Combustion turbine burner
US2689457A (en) * 1949-03-15 1954-09-21 Hermann Oestrich Burner, particularly for gas turbines
US2725718A (en) * 1950-04-10 1955-12-06 Goodyear Aircraft Corp Ignition systems for jet motors and the like
US2701608A (en) * 1951-02-03 1955-02-08 Thermal Res And Engineering Co Burner
US2693083A (en) * 1951-03-26 1954-11-02 Roy W Abbott Combination flame-holder and fuel nozzle

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3026675A (en) * 1958-08-22 1962-03-27 Snecma Device for the air intake into the primary zone of a combustion chamber in a turbo-machine
US3080715A (en) * 1959-04-28 1963-03-12 Rolls Royce Combustion chamber
US3130773A (en) * 1959-05-04 1964-04-28 Drake Block Co Inc Air-cooled burner ring
US3169369A (en) * 1963-06-19 1965-02-16 Gen Electric Combustion system
US3304982A (en) * 1964-07-09 1967-02-21 H B Smith Company Inc Windbox for furnace
US3273343A (en) * 1965-03-08 1966-09-20 Dickens Inc Combustion chamber construction in gas turbine power plant
US3414362A (en) * 1966-04-15 1968-12-03 F Schoppe Dr Ing Burner for firing a combustion chamber
US3792581A (en) * 1970-12-22 1974-02-19 Nissan Motor System and method used in a gas turbine engine for minimizing nitrogen oxide emission
US3700173A (en) * 1970-12-30 1972-10-24 Combustion Eng Diffuser
US5149261A (en) * 1985-11-15 1992-09-22 Nippon Sanso Kabushiki Kaisha Oxygen heater and oxygen lance using oxygen heater
US20030152878A1 (en) * 1997-11-10 2003-08-14 Staffler Franz Josef Streamlined body and combustion apparatus
US8979525B2 (en) * 1997-11-10 2015-03-17 Brambel Trading Internacional LDS Streamlined body and combustion apparatus
US20050026096A1 (en) * 2001-11-23 2005-02-03 Staffler Franz Josef Streamlined body and combustion apparatus having such a streamlined body
US20060174626A1 (en) * 2005-02-09 2006-08-10 Snecma Shroud for a turbomachine combustion chamber
EP1703207A1 (fr) * 2005-02-09 2006-09-20 Snecma Carenage de chambre de combustion de turbomachine
US7805943B2 (en) 2005-02-09 2010-10-05 Snecma Shroud for a turbomachine combustion chamber
FR2881813A1 (fr) * 2005-02-09 2006-08-11 Snecma Moteurs Sa Carenage de chambre de combustion de turbomachine
US20100015562A1 (en) * 2008-07-16 2010-01-21 Babington Robert S Perforated flame tube for a liquid fuel burner
US8622737B2 (en) * 2008-07-16 2014-01-07 Robert S. Babington Perforated flame tube for a liquid fuel burner
US9234659B2 (en) 2008-07-16 2016-01-12 Robert S. Babington Perforated flame tube for liquid fuel burner
US20120085420A1 (en) * 2010-10-07 2012-04-12 Carrier Corporation Inshot burner flame retainer
US8998605B2 (en) * 2010-10-07 2015-04-07 Carrier Corporation Inshot burner flame retainer
US20130089826A1 (en) * 2011-10-11 2013-04-11 Keisuke Mori Tubular burner
US9410698B2 (en) * 2011-10-11 2016-08-09 Rinnai Corporation Tubular burner

Also Published As

Publication number Publication date
FR1115481A (fr) 1956-04-25
NL98183C (en(2012))
GB793325A (en) 1958-04-16

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