US3826078A - Combustion process with selective heating of combustion and quench air - Google Patents

Combustion process with selective heating of combustion and quench air Download PDF

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US3826078A
US3826078A US00238318A US23831872A US3826078A US 3826078 A US3826078 A US 3826078A US 00238318 A US00238318 A US 00238318A US 23831872 A US23831872 A US 23831872A US 3826078 A US3826078 A US 3826078A
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air
stream
combustion
region
primary
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US00238318A
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H Quigg
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Phillips Petroleum Co
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Phillips Petroleum Co
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Priority to US00238318A priority Critical patent/US3826078A/en
Priority to CA157,091A priority patent/CA964870A/en
Priority to ES409276A priority patent/ES409276A1/es
Priority to IT32792/72A priority patent/IT971769B/it
Priority to AU49979/72A priority patent/AU444390B2/en
Priority to SE7216324A priority patent/SE390444B/xx
Priority to JP47126066A priority patent/JPS5025088B2/ja
Priority to FR7244862A priority patent/FR2167065A5/fr
Priority to DE19722261591 priority patent/DE2261591A1/de
Priority to GB5813972A priority patent/GB1409788A/en
Priority to US459956A priority patent/US3865538A/en
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Publication of US3826078A publication Critical patent/US3826078A/en
Priority to CA209,758A priority patent/CA979231A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/36—Open cycles
    • 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 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • 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

Definitions

  • This invention relates to improved combustion processes, improved combustors which can be employed in said processes, and an improved combination of combustion apparatus and heat utilization apparatus.
  • the present invention solves the above-described problems by heatexchanging the turbine exhaust gases with another air stream to the combustor, e.g., the dilution or quench air, instead of the primary inlet air.
  • the method of the invention thus provides for reducing the temperature of the primary inlet air to the combustor. This reduces the temperature in the combustor which results in reduced nitrogen oxides emissions.
  • the overall advantageous result of the invention includes (1) reduction of nitrogen oxide emissions from the combustor while (2) maintaining thermal efficiency by returning the recovered heat to the process at a point where it has no effect on nitrogen oxides production.
  • the invention also provides novel combustors, and a novel combination of combustion apparatus and heat utilization apparatus.
  • a stream of air and a stream of fuel are passed to a combustion zone, at least partially mixed to form a combustible mixture which is burned to produce hot combustion gases containing heat energy, and said hot combustion gases are passed to a heat energy utilization zone to utilize a portion of said heat energy
  • the improvement comprising: dividing said stream of air into a first stream of air and a second stream of air; passing at least a portion of said first stream of air to said combustion zone; passing said second stre/am of air in heat exchange relationship with an exhaust stream from said heat energy utilization zone to heat said second stream of air and thereby utilize an additional portion of said energy; and passing at least a portion of said heated second stream of air into a quench region of said combustion zone.
  • an'air supply conduit comprising, in combination: an'air supply conduit; a
  • combustion means for burning a fuel to produce hot combustion gases containing heat energy; a fuel inlet means for introducing a fuel into said combustion means; a primary air conduit means connected to said air supply conduit and said combustion means for introducing a stream of air comprising primary air into said combustion means; a heat exchange means; a quench air conduit means connected to said air supply conduit, said heat exchange means, and said combustion means for delivering a stream of air comprising quench air from said air supply conduit, through said heat exchange means, and into said combustion means; a heat energy utilization means for utilizing a portion of said heat energy; an effluent conduit means for passing said hot combustion gases from said combustion means to said heat energy utilization means; and an exhaust conduit means connecting said heat energy utilization means and said heat exchange means for passing said hot combustion gases from said heat utilization means and into heat exchange relationship with said stream of quench air to heat said quench air and thereby utilize an additional portion of said heat en- Still further according to the invention, there is provided a combustor comprising, in combination: an outer tubular casing
  • FIG. 1 is a diagrammatic flow sheet illustrating methods of producing and utilizing heat energy in accordance with the invention.
  • FIG. 2 is a diagrammatic illustration of methods and apparatus in accordance with the invention.
  • FIG. 3 is a view in cross section of a combustor in accordance with the invention.
  • FIG. 4, 5, 6, and 7 are views in cross section taken along the lines 4-4, 5-5, 6-6, and 77, respectively, of FIG. 3.
  • FIG. 8 is a fragmentary perspective view of a combustor flame tube illustrating another type of fin or extended surface which can be employed thereon.
  • FIG. 9 is a partial view in cross section of another combustor in accordance with the invention.
  • FIG. 10 is a front elevation view taken along the lines 10-10 of FIG. 9.
  • FIG. 11 is a cross section view in elevation of the swirl plate of the dome or closure member in the combustor of FIG. 9.
  • FIG. 12 is a diagrammatic view, partially in cross section of another combustor in accordance with the invention.
  • FIG. 1 a stream of air from an air supply conduit 10 is divided into a first stream of air in conduit 12 and a second stream of air in conduit 14.
  • at least a portion of said first stream of air 12 is passed into combustion zone 16.
  • a stream of fuel is introduced into said combustion zone via conduit 18.
  • Said combustion zone can comprise any suitable type of combustion zone for burning a mixture of fuel and air to produce hot combustion gases containing heat energy.
  • said combustion zone can be a combustor in a gas turbine engine, a combustor in an aircraft jet engine, a combustor or other furnace employed in a boiler for generating steam, or other types of stationary power plant, etc.
  • Said fuel and said first stream of air are at least partially mixed to form a combustible mixture which is burned to produce hot combustion gases containing heat energy.
  • Said hot combustion gases are passed via conduit to heat energy utilization zone 22 so as to utilize a portion of the heat energy in said gases.
  • Said heat energy utilization zone can comprise any suitable method and/or means for utilizing or putting to use the heat energy contained in said hot combustion gases. For example, a turbine in a gas turbine engine wherein heat energy is converted to mechanical energy, or the heat exchange tubes in a boiler where water is connected to steam, etc.
  • Said second stream of air in conduit 14 is passed through heat exchange zone 24 in heat exchange relationship with an exhaust stream in conduit 26 from heat energy utilization zone 22 so as to heat said air and thereby utilize an additional portion of said heat energy.
  • Said heat exchange zone can comprise any suitable method and/or means for effecting heat exchange between two separate streams of fluids, e.g., indirect heat exchange.
  • the heated second stream of air is passed from said heat exchange zone via conduit 15 and returned to said combustion zone 16, preferably at a downstream location therein, to serve as a diluent or quench medium to lower the temperature of the effluent gases in conduit 20 before they are passed to the heat energy utilization zone 22.
  • said combustion zone 16 can comprise a primary combustion region, a secondary combustion region located downstream from said primary combustion region, and a quench or dilution region located downstream from said secondary combustion region.
  • said first stream of air in conduit 12 is further divided into a stream comprising primary air and another stream comprising secondary air. Said primary air is introduced into said primary combustion region and said secondary air is introduced into said secondary region via conduit 30. At least a portion of said heated second stream of air is introduced into said quench or dilution region via conduit 15, as before.
  • a portion of said heated second stream of air in conduit 15 can be passed via conduit 31 into conduit 30 for mixing with and increasing the temperature of the secondary air therein.
  • the valves in said conduits 30 and 31 can be employed to regulate the relative proportions of the two streams of air.
  • FIG. 2 illustrates one embodiment of the invention wherein the effluent gases from combustor 16 are passed via conduit 20 to a turbine 25.
  • turbine 25 a portion of the heat energy in said gases is converted to mechanical energy to drive shaft 28 which can be connected to any suitable load.
  • Exhaust gases from turbine 25 are passed via conduit 26 to heat exchanger 24 and exhausted therefrom via conduit 27.
  • FIG. 3 there is illustrated a combustor in accordance with the invention, denoted generally by the reference numeral 40, which comprises an elongated flame tube 42.
  • Said flame tube 42 is open at its downstream end, as shown, for communication with a conduit leading to a turbine or other utilization of the combustion gases.
  • a closure or dome member designated generally by the reference numeral 44, is provided for closing the upstream end of said flame tube, except for the openings in said dome member.
  • An outer housing or casing 46 is disposed concentrically around said flame tube 42 and spaced apart therefrom to form a first annular chamber 48 around said flame tube and said dome or closure member 44.
  • Said annular chamber 48 is closed at its downstream end by any suitable means such as that illustrated.
  • Suitable flange members are provided at the downstream end of said flame tube 42 and outer housing 46 for mounting same and connecting same to a conduit leading to a turbine or other utilization of the combustion gases from the combustor.
  • suitable flange members 50 and 52 are provided at the upstream end of said flame tube 42 and said outer housing 46 for mounting same and connecting same to a suitable conduit means which leads from a compressor or other source of air.
  • said upstream flange members comprise a portion of said outer housing or casing 46 which encloses dome member 44 and forms the upstream end portion of said first annular chamber 48.
  • outer housing or casing 46 can be extended, if desired, to enclose dome 44 and said upstream flanges then relocated on the upstream end thereof. While not shown in the drawing, it will be understood” that suitable support members are employed for supporting-said flame tube 42 and said closure member 44 in the outer housing 46 and said flange members. Said supporting members have been omitted so as to simplify the drawing.
  • An air inlet means is provided for introducing a swirling mass or stream of air into the upstream end portion of flame tube 42.
  • said air inlet means comprises a generally cylindrical swirl chamber 54 formed in said dome member 44.
  • the downstream end 'of swirl chamber 54 is in open communication with the upstream end of flame tube 42.
  • A; plurality of air conduits 56 extend from said first annular chamber 48, or other suitable source of air, into, swirl chamber 54 tangentially with respect to the inner? wall thereof.
  • a fuel inlet means is provided for introducing a stream of fuel into the upstream end portion of flame tube 42.
  • said fuel inlet. means comprises a hollow conduit 58 for introducing a stream of fuel into the upstream end of swirl chamber 54 and;
  • a flared expansion passageway 60 is formed in the downstream end portion of dome or closure member 44. Saidflared passageway flares outwardly from the downstream end of swirl chamber 54 to a point on the inner wall of flame tube 42. 4
  • An imperforate sleeve 62 surrounds an upstream portion of said flame tube 42.
  • the outer wall of said sleeve can be insulated, if desired and thus increase its effectiveness'as a heat shield.
  • Said sleeve 62 is spaced apartfrom flame tube 42.so as to longitudinally enclose an upstream portion 48 of said first annular chamber 48 and define a second annular chamber 64 between said sleeve 62 and outer casing 46.
  • An annular wall member 66 secured to the inner periphery of casing 46, is pro-l vided for closing'the downstream end of said second annular chamber 64.
  • An annular baffle member 68 secured to the outer wall of flame tube 42 and the inner wall of sleeve 62, is provided for closing the upstream end of said enclosed portion 48' of first annular space 48.
  • At least one opening is provided in the wall of. flame tube 42 at a first station located intermediate the ends of said flame tube. In most instances, it will be preferred to provide a plurality of openings 70, as illus trated.
  • a generally tubular conduit means 72 extends; from said second annular chamber 64 into communica-- tion with said opening 70 for admitting a second stream of air from said second annular chamber 64 into the in-v terior of flame tube 42.
  • FIG. 8 illustrates another type of fin which can be employed.
  • the fins 80 extend longitudinally of flametube 42. Said fins 76,
  • FIG. 7 illustrates one type of structure, which can be employed to provide tubular conduits 72'.
  • a plurality of boss members 82 spaced apart circumferentially in a rowaround the periphery of flame tube 42, is provided downstream from the last row of fins 78.
  • Said boss members 82 havethe general shape of fins 76 and 78 and'passageways 83 are provided therebetweemsimilarly as for passageways 77 and 79 in the rows of fins I 76 and 78.
  • Said imperforate sleeve62 extends over boss members 82, similarly as for fins 76 and 78, and
  • conduits 72 can be formed by cutting through said 'sleeve 62 and said boss members 80 into communication with openings 70 in flame tube 42. Said passage ways 77, 79 and 83 thus provide communication through enclosed portion 48, around tubular conduits 72, and into the downstream portion of first annular chamber 48.
  • FIG. 9 there is illustrated the upstream portion of another combustor in accordance with the invention.
  • the downstream portion of the combustor of FIG. 9 is like the combustor of FIG. 3.
  • a closure member or dome designated generally by the reference numeral 85, is mounted in the-upstream end of flame tube 42 so as to close the upstream end of said flame tube except for the openings'provided in said closure member.
  • Said closure member can befabricated integrally, i.e., as one element.
  • said closure member in a plurality of pieces, e.g., an upstream element86, a swirl plate 87 (see FIG. 11), and a downstream element or radiation shield 88.
  • An air inlet '10, and 11, said air inlet means comprises a plurality of air conduits 90 and 90' extending through said upstream member 86 and said swirl plate 87, respectively.
  • a plurality of angularly disposed baffles 91, one for each of said air conduits 90, are formed on the downstream side of said swirl plate adjacent the outlets of said air conduits.
  • a fuel inlet means is provided for introducing a stream of fuel into the upstream end of flame tube 42.
  • said fuel inlet means comprises nicating with a passageway 93 formed in upstream elea satifi his in m a ni lqa satesx tlt smbsr s4;'sisamaieaaeieihem's6; A spray nozzle 95 is.
  • any other suitable type of spray nozzle and fuel inlet means can be employed, including other air assist atomization nozzles.
  • it is within the scope of the invention to employ other nozzle types for atomizing normally liquid fuels such as nozzles wherein a stream of air is passed through the along with the fuel.
  • FIG. 12 is a diagrammatic illustration of another type of combustor which can be employed in the practice of the inventiQmThis combustor is similar to the combustor illustrated in FIG..3. In the combustor of FIG. 12
  • a stream of air from a compressor or other source is divided into a first stream of air and a second stream of air, said first stream of air'is passed, via a conduit connected to flange 52, into the? upstream end of annular space 48.
  • Said first stream of air is further divided into a stream comprising primary air and a stream comprising secondary air.
  • Said tangentialconduits impart a helical or swirling motion to the airentering said swirl chamber and exiting therefrom. This swirling motion creates a strong vortex action resulting in a reverse circulation of hot gases within flame tube 42.
  • a stream of fuel, preferably prevaporized, is admitted, via conduit 58, axially of said swirling stream of air. Controlled mixing of said fuel and said air occurs at the interface therebetween.
  • the fuel and air exit from swirl chamber 54 via expansion passageway 60 wherein they are expanded in a uniform and graduated manner, d ur-.
  • Said secondary air is passed from the upstream end of annular chamber 48 via second annular chamber 64,-,
  • the above-mentioned second stream of air after via openings 74 into a third region of the combustor which is located downstream from said second region.
  • Said second stream of air comprises and-can be referred to as quench or dilution air.
  • Conduit 15 can communicate with enclosed portion 48', 'or the downstream portion of first annular space or chamber 48, at any desired location.
  • the upstream end of ennozzle 8 closed portion 48' is a preferredlocatidfbi ause the air'flowing over the finned wall portion of flame tube 42 serves to cool said wall portion and remove heat from the interior of said flame tube, and thus cause the primary combustion region to operate at a lower temperature. This'aids further in reducing nitrogen oxide emissions.
  • the operation of the combustor of FIG. 9 is similar to the above-described operation of the combustor of FIG. 3, and reference is made thereto. The principal difference is in the operation of closure member (FIG. 9) and closure member 44 (FIG. 3).
  • closure member FIG. 9
  • primary air is passed through said :openings and 90, strikes said baffles 91, and has a swirlingmotion imparted thereto in chamber 89.
  • a swirling stream of air exits from swirl chamber 89 1 through the opening in radiation shield 88 which surrounds nozzle 95.
  • a stream of liquid fuel is passed through conduit 92, passageway 93, chamber 94, and exits from nozzle in a generally cone-shaped discharge. Said fuel contacts said stream of air, with said air stream assisting the action of nozzle 95 in atomizing said fuel.
  • the combustor of FIG. 12 is particularly adapted to be employed in those embodimerits of the invention wherein the stream of secondary air admitted through openings 70 can have a temperature greater than the temperature of the primary air ad mitted through dome orclosure member 44.
  • tubular conduits 72 are connected to the same source of air as is supplying chamber 48, the temperature of the secondary air can be substantially the same as the primary air.
  • the temperature of the secondary air can be increased to be greater than the temperature of the primary air by means of a connection between said combustors or combustion zones employed in the practice of the invention under any conditions which will give the improved results of the invention.
  • the temperature of the inlet primary air be within the range of from ambient to about 700 F., more preferably from ambient to about 500 F. In a preferred em- However, it is within the scope of the invention for the temperature of the secondary air to be greater, e.g.,
  • l carbon was measured by the technique described by Lee and Wimmer, SAE Paper 680769. Each pollutant measured is reported in terms of pounds per 1,000 pounds of fuel fed to the combustor.
  • the results of flame tube wall or is heated by having a portion of the th r ns were as follow heated air in conduit 15 mixed therewith via conduit 31, see FIGS. 1 and 2.
  • the temperature of the dilution Test Conditions or quench air can be any suitable temperature depend- Combustor operating variames Idle Power i ing upon materials of construction in the equipment T 900 1100 employed downstream from the combustor, e.g., turg' f f a g 50 HO bme blades, and.
  • the combined volume of said primary air and said secondary air will usually be a minor proportion of the total air to the combustor, e.g., less than about 50 volume percent, with" said primary air being in the range of up to about volume percent and said secondary air being in the range of up to about 24 volume percent.
  • the volume of said quench or dilution air will usually be a major portion of the total air to the combustor, e.g., more than about 50 volume percent.
  • the relative volumes of said primary, secondary, and quench air streams can be controlled by varying the sizes of the openings, relative to each other, through which said streams of air are admitted to the flame tube. Any other suitable meansof controlling said air volumes can be employed, e. g., flow meters on each air stream.
  • air is employed generically herein and in the claims, for convenience, to include air and other combustion-supporting gases.
  • the combustor was a; straight-through can-type combustor employing fuel atomization by a single simplex-type nozzle.
  • the combustor liner (flame tube) was fabricated from 2-inch' pipe, with added internal deflector skirts for air film; cooling of surfaces exposed to the flame.
  • Exhaust emis-f sions from this combustor when operated at comparable conditions for combustion, are in general agree-i ment with measurements presently'available from scv-i eral different gas turbine engines.
  • a commercial Typei A jet fuel was employed in these test runs. Runs were made at operating conditions simulating idle conditions; and at operating conditions simulating maximum; power conditions.
  • Analyses for content of nitrogen oxides (reported as NO), carbon monoxide, and hydro-, carbons (reported as carbon) in-the combustor exhaust! gases were made at each test condition.
  • the method for measuring nitrogen oxides was based on the Saltzman ;;and a variable heat input rate, it was found that when the air inlet temperature was increased over a range from 400 F. to about l,l50 F., the nitrogen oxides emissions increased substantially uniformly from about ,3 to about 23.5 lbs. per 1,000 lbs. of fuel burned.
  • Hydrothe combustorfi third portion of said air was passed dary air via annular chamber 64 tubular conduits 72, and openings into a secondary combustion region of portion of afiFuEiF'EFafiiBer 4'8; iidbp h'i ggm into PHYSICAL AND CHEMICAL PROPERTIES OF TEST FUEI. the quench region of the combustor.
  • Like flows were a used in the combustor illustrated in FIG. 9. Using said flows, each of said combustors was operated at the test vummw I M d V A 0 points or conditions set forth in Table III below. Analyrm l d) (Cu n) ses for emissions content in the combustor exhaust smichiomemc Fuel/Air Ratio Mm 0.0676
  • a combustor [2 z: A 24 1 canbe operated with a low primaryair inlet tempera- 13 do. 6.40 0 9 17 0.1 ture, a controlled secondary arr inlet temperature 14 i 2 2 which can be the same as or greater than the temperature of the inlet primary air, and a heated quench air 15 76.6 1.85. 5.7 0 0.5 I h h th 16 H0 18 94 0'3 stream w 1c can ave a greater temperature an e1- 17 do. 3.70 1.4 108 0.2 ther said primary air or said secondary air.
  • the method 18 d0. I of the invention thus provides for a low primary inlet :3 g;- 2'23 8'; 2g 8'? air temperature to give low N0, emissions values, a 217 40 j (17 controlled secondary air inlet temperature to give de- 1 s1red CO emissions values, and a heated quench mlet 22 1- 3- 2 -3 air to conserve heatenergy and incr'easethe overall ef- 23 -f1ciency of the system. 24 do. 3.70 1.1 134 0.2 1 25 do, 456 109 In'general, said data also show that vN),,, em1ss1 or1s 26 do.
  • the primary combustion zone is preferably operated 1 8 443 L06 9.4 4 Q5 @fuel-rich with respect to the primary air admitted 9 do. -5 77 0.3 thereto.
  • the equivalence ratio in the primary 10 do. 2.14 1.4 53 0.1- U 163 L4 22 0.3 combustion zone is preferably greater than stoichio- 12 do. 3.20 1.5 7 0.2 metric.-
  • the equivalence ratio in said second g3 38: 3:28 f3 81% zone preferably is less than stoichiometric. This 21 do. 4.26 1.2 4 0.0 method of operation is preferred when it is desired to 22 442 L07 3'1 10 L4 obtain both low NO, and low CO emissions from a 23 57 14 ()5 combustor.
  • transition v24 g 8-; from the fuel-rich condition in the primary combustion g2 2: 33 5: zone to the fuel-lean condition in the secondary zone 27 do 3.70 1.0 50 0.6 be sharp or rapid, e.g., be effected as quickly as possi- .@EWEQQFBLQQPFBQWF? t thasscond 993.9!
  • Combustion zone be operatedfue l-rich as described, it is within the scope of the invention to operate the'primary combustion zone fuel-lean. Thus, it is withinthe scope of the invention to operate the primary combustion zone with any equivalence ratio which will give the improved results of the invention.
  • the equivalence ratio in the primary combustion zone can have any value such that the NO, emissions value in the exhaust gases from the combustor is not greater than about 5 pounds, preferably not greater than about 3.5 pounds, per 1,000 pounds of fuel burned in said combustor.
  • said equivalence ratio will be at least 1.5, more preferably at least 3.5, depending upon the other operating variables or parameters, e.g., temperature of the inlet air to theprimary combustionzone.
  • N 0, emission values referred to in the preceding paragraph can be greater than the values there given when operating high performance combustors.
  • combustors such as the intermediate compression ratio combustors having a compression ratio of about 5 to atmospheres and the high compression ratio combustors having a compression ratio of about 15 to about 40 atmospheres usedv in jet aircraft and other high performance engines.
  • the NO, emissions from such high performance or high compression ratio combustors will naturally be higher than the NO, emissions from low compression ratio combustors.
  • greatly improved results in reducing N0, emissions from a high performance com bustor can be obtained without necessarily reducingsaid NO 'emissions to the same levels as would be obtained from a low performance combustor.
  • equivalence ratio for a particular zone is defined as the ratio of the fuel flow (fuel avail-5 able) to the fuel requiredfor stoichiometric combus-j tion with the air available. Stated another way, said; equivalence ratio is the ratio of the actual fuel-air mixture to the stoichiometric fuel-air mixture. For exam-' vention is not limited'to any particular range or value.
  • any primary air inlet temperature which will give the improved results of the invention, for example, from ambient or atmospheric temperatures or lower to about l,500 F. or higher.
  • l-low'ever considering presently available practical materials of construction, about l,200 F. to about l,500 F. is a practical upper limit for said primary air inlet temperature in most instances.
  • Considering other practical aspects such as not having to cool the compressor dis-? charge stream, about 200 to 400 F. is a practical lower limit for said primary air inlet temperature in' many instances.
  • primary air inlet temperatures lower than 200F. can be used, e.g., in low compression ratio combustors.
  • the combustor is'zsanaary'ad'rhtu's'iibfi a irYcan be 7 an 7 important operating variable or parameter, particularly when the lower primary air inlet temperatures are used, and it is desired to obtain low CO emission values as well as low NO, emission values.
  • Said data show that both low NO, emission values and low CO emission values can be obtained when the temperature of the inlet air to both the primary combustion zone and the second zone of the combustor are at least about 900 F. As the temperature of the inlet air to said zones decreases, increasingly improved (lower) values for NO, emissions are obtained,but it becomes more difficult to obtain desirably low CO emission values. It is preferred that the temperature of the inlet air to the primary .combustion zone not be greater than about 700 F.
  • the temperature of the secondary air admitted to the second zone of the combustor be greater than the temperature of the'primary air admitted to the primary combustion zone.
  • the temperature of the inlet secondary air be in the range of from about to about 500 F. greater than the temperature of
  • the' presently preferred operating ranges for other variables or parameters arerheat input, from 30m 500 Btu per lb. of total air to the combustor; combustor pressure, from 3 to 10 atmospheres; and reference air velocity, from 50 to 250 feet per second.
  • I would be in the order of, in lbs. per 1,000 lbs. of fuel ⁇ to values ofnot more t han about 2 5,pr'eferably not more than about 1.8, pounds per 1,000 pounds of fuel burned at idle conditions; and not more than about 5, preferably not more than about 3.5, pounds per 1,000 pounds of fuel burned at maximum power conditions, the invention is not limited to said values.
  • a stream of air and a stream. of fuel are passed to a combustion zonecomprising a; primary combustion region, a secondary combustiong region located downstream from said primary combus-l tion region, and a quench region located downstream; from said secondarycombustion region, said fuel and said air are at least partially mixed to form a combustiblemixture which is burned to produce hot combustionf gases containing heat energy, and said hot combustion;
  • a method according to claim 2 wherein the equivalence ratio in said primary combustion region is greater than stoichiometric and is adjusted to a value such that the N01, emissions value in the exhaust gases from said combustion zone is not greater than about pounds per 1,000 pounds of fuel burned in said combustion zone.
  • a method for forming and .buming a combustible mixture of a fuel and airin a combustion zone having a primary combustion region, a secondary combustion region located downstream from said primary combustion region, and a quench region located downstream from said secondary combustion region, to produce hot combustion gases containing heat energy which are lpassed to a heat energy utilization zone to utilize a portion of said heat energy comprises:
  • a method according to claim 7 wherein said equivalence ratio is adjusted to a value such that the NO, emissions value inthe exhaust gases from said combustion zone is not greater than about pounds per l,000 pounds of fuel burned in said combustion zone.
  • said equivalence ratio is at least about 1.5.
  • equivalence ratio is at least about 3.5.
  • a method'according to claim 7 wherein the greater than stoichiometric and is adjusted to a value equivalence ratio in said primary combustion region is 15.
  • a method for forming and burning a combustible mixture of a fuel and air in a combustion zone having' a primary combustion region, a secondary combustion region located downstream from said primary combustion region, and a quench region located downstream from said secondary combustion region, to produce hot combustion gases containing heat energy which are passed to a heat energy utilization zone to utilize a portion of said heat energy comprises:
  • said heated second stream of air is passed in a first annular stream surrounding an outer wall of said primary-combustion region and a portion of said secondary combustion region, and is then introduced into said quench region;
  • said secondary air is passed in a second annular stream surrounding but separated from said first annular stream, and is then introduced into said secondary combustion region.
  • a method for forming and burning a combustible mixture of a fuel and air in a combustion zone having a primary combustion region, a secondary combustion region located downstream from said primary combustion region, and a quench region located downstream from said secondary combustion region, to produce hot combustion gases containing heat energy which are passed to a heat energy utilization zone to utilize a portion of said heat energy comprises:

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Incineration Of Waste (AREA)
US00238318A 1971-12-15 1972-03-27 Combustion process with selective heating of combustion and quench air Expired - Lifetime US3826078A (en)

Priority Applications (12)

Application Number Priority Date Filing Date Title
US00238318A US3826078A (en) 1971-12-15 1972-03-27 Combustion process with selective heating of combustion and quench air
CA157,091A CA964870A (en) 1971-12-15 1972-11-21 Gas turbine combustion process
ES409276A ES409276A1 (es) 1971-12-15 1972-12-04 Procedimiento de combustion y aparato para su aplicacion.
IT32792/72A IT971769B (it) 1971-12-15 1972-12-12 Processo di combustione e camera di combustione
AU49979/72A AU444390B2 (en) 1972-12-13 Combustion process and combustor
SE7216324A SE390444B (sv) 1971-12-15 1972-12-14 Sett att alstra och forbrenna en forbrennbar blandning av brensle och luft samt apparat for genomforande av settet
JP47126066A JPS5025088B2 (enrdf_load_stackoverflow) 1971-12-15 1972-12-15
FR7244862A FR2167065A5 (enrdf_load_stackoverflow) 1971-12-15 1972-12-15
DE19722261591 DE2261591A1 (de) 1971-12-15 1972-12-15 Verbrennungsverfahren und brenner zur durchfuehrung des verfahrens
GB5813972A GB1409788A (en) 1971-12-15 1972-12-15 Method of producing and utilizing heat energy and apparatus therefor
US459956A US3865538A (en) 1972-03-27 1974-04-11 Combustor and combustion apparatus
CA209,758A CA979231A (en) 1971-12-15 1974-09-23 Combustion apparatus for a gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US20824571A 1971-12-15 1971-12-15
US00238318A US3826078A (en) 1971-12-15 1972-03-27 Combustion process with selective heating of combustion and quench air

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US3826078A true US3826078A (en) 1974-07-30

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US (1) US3826078A (enrdf_load_stackoverflow)
JP (1) JPS5025088B2 (enrdf_load_stackoverflow)
CA (1) CA964870A (enrdf_load_stackoverflow)
DE (1) DE2261591A1 (enrdf_load_stackoverflow)
ES (1) ES409276A1 (enrdf_load_stackoverflow)
FR (1) FR2167065A5 (enrdf_load_stackoverflow)
GB (1) GB1409788A (enrdf_load_stackoverflow)
IT (1) IT971769B (enrdf_load_stackoverflow)
SE (1) SE390444B (enrdf_load_stackoverflow)

Cited By (19)

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US3939653A (en) * 1974-03-29 1976-02-24 Phillips Petroleum Company Gas turbine combustors and method of operation
US3986347A (en) * 1973-12-06 1976-10-19 Phillips Petroleum Company Combustor process for low-level NOx and CO emissions
US4004414A (en) * 1973-12-04 1977-01-25 The Franch State Combustion chamber for supercharged internal combustion engine
US4012902A (en) * 1974-03-29 1977-03-22 Phillips Petroleum Company Method of operating a gas turbine combustor having an independent airstream to remove heat from the primary combustion zone
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
US4050239A (en) * 1974-09-11 1977-09-27 Motoren- Und Turbinen-Union Munchen Gmbh Thermodynamic prime mover with heat exchanger
US4067681A (en) * 1975-03-10 1978-01-10 Columbia Gas System Service Corporation Gas-fired smooth top range
US4081958A (en) * 1973-11-01 1978-04-04 The Garrett Corporation Low nitric oxide emission combustion system for gas turbines
US4087963A (en) * 1974-03-29 1978-05-09 Phillips Petroleum Company Combustor for low-level NOx and CO emissions
US4179880A (en) * 1973-12-06 1979-12-25 Phillips Petroleum Company Combustion process and apparatus therefor
US4205524A (en) * 1974-03-29 1980-06-03 Phillips Petroleum Company Methods of operating combustors
US4255927A (en) * 1978-06-29 1981-03-17 General Electric Company Combustion control system
US5819540A (en) * 1995-03-24 1998-10-13 Massarani; Madhat Rich-quench-lean combustor for use with a fuel having a high vanadium content and jet engine or gas turbine system having such combustors
US20070037105A1 (en) * 2005-05-23 2007-02-15 Pfefferle William C Method for low NOx combustion of syngas/high hydrogen fuels
US20100330510A1 (en) * 2005-05-23 2010-12-30 Pfefferle William C METHOD FOR LOW NOx COMBUSTION OF SYNGAS / HUGH HYDROGEN FUELS
EP2071234A3 (en) * 2007-12-12 2014-02-19 Precision Combustion, Inc. Direct injection method and apparatus for low NOx combustion of high hydrogen fuels
EP2639507A3 (en) * 2012-03-12 2015-10-21 General Electric Company System for supplying a working fluid to a combustor
US20160201617A1 (en) * 2015-01-13 2016-07-14 Caterpillar Inc. Engine Intake System and Method for Operating Same
RU2613764C2 (ru) * 2012-03-15 2017-03-21 Дженерал Электрик Компани Система для подачи рабочей текучей среды в камеру сгорания (варианты)

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Publication number Priority date Publication date Assignee Title
JPS5718095B2 (enrdf_load_stackoverflow) * 1973-11-30 1982-04-14
JPS50111421A (enrdf_load_stackoverflow) * 1974-02-16 1975-09-02
JPS5121011A (ja) * 1974-08-16 1976-02-19 Mitsubishi Heavy Ind Ltd Nenshosochi
DE2538134C2 (de) * 1974-08-27 1984-11-08 Mitsubishi Jukogyo K.K., Tokio/Tokyo Ölbrenner
JPS5129726A (enrdf_load_stackoverflow) * 1974-09-06 1976-03-13 Mitsubishi Heavy Ind Ltd
JPS5217887U (enrdf_load_stackoverflow) * 1975-07-28 1977-02-08
DE2844095C2 (de) * 1978-10-10 1984-10-31 Ludwig Dipl.-Ing. Dr.-Ing. 7000 Stuttgart Huber Schwingfeuergerät
US5850732A (en) * 1997-05-13 1998-12-22 Capstone Turbine Corporation Low emissions combustion system for a gas turbine engine
US6105370A (en) * 1998-08-18 2000-08-22 Hamilton Sundstrand Corporation Method and apparatus for rejecting waste heat from a system including a combustion engine
US9709277B2 (en) * 2012-05-15 2017-07-18 General Electric Company Fuel plenum premixing tube with surface treatment

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US3608309A (en) * 1970-05-21 1971-09-28 Gen Electric Low smoke combustion system
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Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4081958A (en) * 1973-11-01 1978-04-04 The Garrett Corporation Low nitric oxide emission combustion system for gas turbines
US4004414A (en) * 1973-12-04 1977-01-25 The Franch State Combustion chamber for supercharged internal combustion engine
US3986347A (en) * 1973-12-06 1976-10-19 Phillips Petroleum Company Combustor process for low-level NOx and CO emissions
US4179880A (en) * 1973-12-06 1979-12-25 Phillips Petroleum Company Combustion process and apparatus therefor
US4087963A (en) * 1974-03-29 1978-05-09 Phillips Petroleum Company Combustor for low-level NOx and CO emissions
US4012902A (en) * 1974-03-29 1977-03-22 Phillips Petroleum Company Method of operating a gas turbine combustor having an independent airstream to remove heat from the primary combustion zone
US4205524A (en) * 1974-03-29 1980-06-03 Phillips Petroleum Company Methods of operating combustors
US3939653A (en) * 1974-03-29 1976-02-24 Phillips Petroleum Company Gas turbine combustors and method of operation
US4050239A (en) * 1974-09-11 1977-09-27 Motoren- Und Turbinen-Union Munchen Gmbh Thermodynamic prime mover with heat exchanger
US4067681A (en) * 1975-03-10 1978-01-10 Columbia Gas System Service Corporation Gas-fired smooth top range
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
US4255927A (en) * 1978-06-29 1981-03-17 General Electric Company Combustion control system
US5819540A (en) * 1995-03-24 1998-10-13 Massarani; Madhat Rich-quench-lean combustor for use with a fuel having a high vanadium content and jet engine or gas turbine system having such combustors
US20070037105A1 (en) * 2005-05-23 2007-02-15 Pfefferle William C Method for low NOx combustion of syngas/high hydrogen fuels
US20100330510A1 (en) * 2005-05-23 2010-12-30 Pfefferle William C METHOD FOR LOW NOx COMBUSTION OF SYNGAS / HUGH HYDROGEN FUELS
EP2071234A3 (en) * 2007-12-12 2014-02-19 Precision Combustion, Inc. Direct injection method and apparatus for low NOx combustion of high hydrogen fuels
US8864491B1 (en) * 2007-12-12 2014-10-21 Precision Combustion, Inc. Direct injection method and apparatus for low NOx combustion of high hydrogen fuels
EP2639507A3 (en) * 2012-03-12 2015-10-21 General Electric Company System for supplying a working fluid to a combustor
EP3514455A1 (en) * 2012-03-12 2019-07-24 General Electric Company System for supplying a working fluid to a combustor
RU2613764C2 (ru) * 2012-03-15 2017-03-21 Дженерал Электрик Компани Система для подачи рабочей текучей среды в камеру сгорания (варианты)
US20160201617A1 (en) * 2015-01-13 2016-07-14 Caterpillar Inc. Engine Intake System and Method for Operating Same
US9695786B2 (en) * 2015-01-13 2017-07-04 Caterpillar Inc. Engine intake system and method for operating same

Also Published As

Publication number Publication date
AU4997972A (en) 1974-01-24
IT971769B (it) 1974-05-10
SE390444B (sv) 1976-12-20
FR2167065A5 (enrdf_load_stackoverflow) 1973-08-17
GB1409788A (en) 1975-10-15
JPS4865315A (enrdf_load_stackoverflow) 1973-09-08
ES409276A1 (es) 1976-03-16
DE2261591A1 (de) 1973-06-28
JPS5025088B2 (enrdf_load_stackoverflow) 1975-08-21
CA964870A (en) 1975-03-25

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