EP2754963A1 - Chambre de combustion de turbine à gaz - Google Patents

Chambre de combustion de turbine à gaz Download PDF

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Publication number
EP2754963A1
EP2754963A1 EP20120829519 EP12829519A EP2754963A1 EP 2754963 A1 EP2754963 A1 EP 2754963A1 EP 20120829519 EP20120829519 EP 20120829519 EP 12829519 A EP12829519 A EP 12829519A EP 2754963 A1 EP2754963 A1 EP 2754963A1
Authority
EP
European Patent Office
Prior art keywords
fuel
passage
premixing
air
fuel mixture
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.)
Withdrawn
Application number
EP20120829519
Other languages
German (de)
English (en)
Other versions
EP2754963A4 (fr
Inventor
Kiyoshi Matsumoto
Takeo Oda
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.)
Kawasaki Heavy Industries Ltd
Kawasaki Motors Ltd
Original Assignee
Kawasaki Heavy Industries Ltd
Kawasaki Jukogyo KK
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 Kawasaki Heavy Industries Ltd, Kawasaki Jukogyo KK filed Critical Kawasaki Heavy Industries Ltd
Publication of EP2754963A1 publication Critical patent/EP2754963A1/fr
Publication of EP2754963A4 publication Critical patent/EP2754963A4/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing 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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00004—Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • the present invention relates to a gas turbine combustor capable of suppressing the emissions of nitrogen oxides (hereinafter referred to as NOx).
  • the gas turbine apparatuses are subjected to severe environmental standards regarding the composition of exhaust gases emitted from a turbine during the operation thereof.
  • reduction of the emissions of NOx contained in the exhaust gases is sought for.
  • a technique of injecting water or vapor into a combustion chamber to lower the temperature of combustion flames has hitherto been employed. It has, however, been found that according to the above described method, a injecting equipment for injecting water or vapor is required, which results in an increase of costs.
  • Patent Document 1 JP Laid-open Patent Publication No. 2011-21875
  • the present invention has for its object to provide a gas turbine combustor equipped with a pilot burner effective to accomplish a sufficient premixing of a compressed air and a fuel to realize the low NOx emission.
  • a gas turbine combustor in accordance with the present invention to mix a compressed air, fed from a compressor, with a fuel to burn a resultant air-fuel mixture to be supplied to a turbine, comprises: a pilot burner provided in a top portion of a combustion liner defining a combustion chamber therein, a main burner of a premixing type located on an outer periphery side thereof, the pilot burner including: an inflow passage provided in an upstream end portion to allow the compressed air to inflow from a radially outer area into a radially inner area; a plurality of fuel supply holes to inject the fuel into the inflow passage in a direction perpendicular to the flow of the compressed air; a premixing passage to mix the compressed air and the fuel inflowed through the inflow passage and to guide the air-fuel mixture towards an axially downstream side; and a plurality of premixed air-fuel mixture injection holes to inject the premixed air-fuel mixture from the premi
  • the compressed air and the fuel fed from the plurality of the fuel supply holes are supplied in a direction perpendicular to each other. Accordingly, by the action of a shearing force of the compressed air relative to the fuel, the mixing of the compressed air with the fuel is facilitated. Also, since the premixed air-fuel mixture is deflected 90° at the time it is introduced from the inflow passage into the premixing passage, a large turbulence occurs in the flow and the premixing is therefore facilitated. In addition, since the premixed air-fuel mixture is guided through the premixing passage in a direction axially upstream thereof, the premixing is further facilitated within this premixing passage.
  • the uniform premixed air-fuel mixture having a minimized variation in concentration of the fuel can be obtained. Since this premixed air-fuel mixture is injected into the combustion chamber through the plurality of the premixed air-fuel mixture injection holes, a bias of the premixed air-fuel mixture within the combustion chamber is suppressed.
  • the premixed air-fuel mixture is injected into the combustion chamber from the main burner of the premixing type disposed in an outer periphery of the pilot burner, the uniformly premixed air-fuel mixture having a minimized variation in concentration of the fuel, not the air-fuel mixture having an enriched concentration, is combusted within the combustion chamber over the entire operating region ranging from a low load operating region to a high load operating region. In view of this, the emissions of NOx may be reduced.
  • a fuel injection hole may be provided at a center portion of the pilot burner to inject a portion of a fuel for piloting purpose into the combustion chamber. According to this structural feature, since that portion of the fuel for the pilot burner can be injected into the combustion chamber through the fuel injection hole provided at the center portion of the pilot burner, the ignitability may be increased and a flame stability can be secured.
  • a carbon removal injection hole may be formed in the vicinity of a downstream side of the fuel injection hole to supply a portion of the premixed air-fuel mixture within the premixing passage.
  • the concentration of the fuel injected through the fuel injection hole into the combustion chamber may be made lower by means of the premixed air-fuel mixture from the carbon removal injection hole to there by avoid an undesirable generation of soot (carbon) which would be brought about by the excessive enrichment of the fuel. Accordingly, the fuel may be stably injected into the combustion chamber without allowing the fuel injection hole to be clogged with a deposition of carbon.
  • the premixing passage may include a speed increasing portion having a passage section that gradually reduces towards a downstream side. According to this structural feature, the flow through the speed increasing portion results in an increase of the flow velocity of the premixed air-fuel mixture and, therefore, it is possible to avoid an undesirable back fire from occurring from the side of the combustion chamber to the premixing passage.
  • a mixing facilitation member may be provided on an upstream side of the speed increasing portion in the premixing passage to facilitate a premixing by deflecting the premixed air-fuel mixture radially outwardly.
  • the premix made up of the compressed air and the fuel, which has been introduced into the premixing passage is deflected towards a radially outer side by the mixing facilitation member and, therefore, the premixing is facilitated by such deflection.
  • the mixing facilitation member is provided in a portion of the premixing passage, which has a large passage section and is positioned on the upstream side of the speed increasing portion, an undesirable increase of the passage resistance by the mixing facilitation member can be suppressed a quantity corresponding to that in which the flow velocity is not high.
  • the inflow passage may have an annular inflow opening, the inflow passage including a plurality of guide pieces positioned radially inwardly of the annular inflow opening to guide the compressed air towards a center of the inflow passage.
  • the fuel supply holes may be arranged at portions between the neighboring guide pieces. According to this structural feature, since the plurality of the fuel supply holes are arranged at portions between the neighboring guide pieces, the fuel may be injected at multiple points and, also, since the fuel divided in a circumferential direction by the guide pieces is supplied into the inflow passage, a uniformly premixed air-fuel mixture having a minimized variation in concentration distribution of the fuel may be obtained.
  • the gas turbine generator GT includes, as principal constituent elements thereof, a compressor 1, a combustor 2 and a turbine 3.
  • the combustor 2 is provided with a fuel supply device 5 and a fuel control device 6.
  • a compressed air A, fed from the compressor 1, and fuel F fed from the fuel supply device 5 through the fuel control device 6 are burned within the combustor 2 to produce a combustion gas G of high temperature and high pressure, which is in turn supplied to the turbine 3 to drive the turbine 3.
  • the compressor 1 is driven by the turbine 3 through a rotary shaft 7.
  • the turbine 3 also drives an electric generator 9 through a reduction gear unit 8.
  • the combustor 2 is of a reverse flow can type in which the compressed air A introduced into such combustor 2 and the combustion gas G flows in respective directions counter to each other within the combustor 2.
  • the combustor 2 includes a plurality of cylindrical housings H arranged circumferentially of a circle coaxial with the rotary shaft 7. Each of those housings H accommodates a substantially cylindrical combustion liner 10 therein, in which a combustion chamber 11 is formed.
  • Each of the housings H has a head end (a left end portion as viewed in Fig. 2 ), which is a tip end side thereof, and an end cover 12 is secured to such head end by means of a plurality of bolts 12a.
  • a cylindrical support 13 positioned inside of the housing H has its base end portion connected with an upstream side of the housing H.
  • This cylindrical support 13 has a tip end portion (a right end portion as viewed in Fig. 2 ) to which a top portion 10a of the combustion liner 10 is secured and, hence, the combustion liner 10 is supported by the housing H through the cylindrical support 13.
  • an annular air passage 15 is defined for introducing the compressed air A fed from the compressor 1 (shown in Fig. 1 ) in a direction towards the top portion 10a of the combustion liner 10, that is, in a direction towards an upstream side.
  • An air introduction chamber 16 is defined inside of the cylindrical support 13 and the support barrel is provided with a plurality of air introduction holes 18 through which the compressed air A is introduced into the air introduction chamber 16.
  • a single pilot burner 20 of a premixing type is provided within the combustion chamber 11 at a center area of the top portion 10a of the combustion liner 10 for injecting a portion of the fuel F directly into the combustion chamber 11 and, also, injecting a premixed air-fuel mixture M1 formed by mixing the fuel F and the compressed air A together.
  • This pilot burner 20 has a base end fluid connected with a pilot fuel introduction port 28 provided in the end cover 12.
  • a single main burner 21 of a premixing type for injecting a premixed air-fuel mixture M2, formed by mixing the fuel F and the compressed air A together, from a premixing passage 29 into the combustion chamber 11 is provided so as to encircle an outer periphery of the pilot burner 20.
  • the main burner 21 includes a main inner peripheral wall 21 a and a main outer peripheral wall 21b, which cooperatively define therebetween the premixing passage 29 of a longitudinally L-sectioned configuration.
  • This premixing passage 29 has an upstream end opening in a direction radially outwardly thereof to define an annular air intake opening 29a, and a plurality of main fuel nozzles 23 are aranged at respective locations radially outwardly of the annular air intake opening 29a and spaced equidistantly from each other in a direction circumferentially of the main burner 21.
  • a plurality of main fuel injecting ports 23a are defined in a portion of the main fuel nozzle 23 that faces the annular air intake opening 29a.
  • the main fuel nozzle 23 has a base end connected with a main fuel introduction port 25 defined in the end cover 12.
  • the annular air intake opening 29a has a swirler 26 disposed therein.
  • the fuel F supplied from the main fuel introduction port 25, together with the compressed air A inflowing from the air intake opening 29a, is swirled by the swirler 26 and is, after having been premixed within the annular premixing passage 29, injected from an annular premix injection opening 29b into the combustion chamber 11 as a premixed air-fuel mixture M2.
  • the fuel F from the fuel supply device 5 shown in Fig. 1 is supplied through the fuel control device 6 to both of the pilot fuel introduction port 28 and the main fuel introduction port 25.
  • An ignition plug 30 is provided in an upstream portion of the peripheral wall 10b of the combustion liner 10 with its tip end positioned inside of the combustion chamber 11.
  • the ignition plug 30 extends through the housing H so as to be fixed to the housing H.
  • the premixed air-fuel mixture M1 injected into the combustion chamber 11 through the pilot burner 20 of the premixing type is ignited by such ignition plug 30.
  • the pilot burner 20 of the premixing type is activated.
  • the premixed air-fuel mixture M2 injected into the combustion chamber 11 through the main burner 21 and the premixed air-fuel mixture M1 injected into the combustion chamber 11 through the pilot burner 20 of the premixing type are simultaneously burned so that a first combustion region S1 consequently is defined in an upstream portion of the combustion liner 10 and on a downstream side of the main burner 21.
  • a plurality of, for example, four, air holes 31 are provided having been spaced an equal distance from each other in a circumferential direction of the combustion liner 10. Respective portions of the housings H facing the air holes 31 have supplemental burners 40 of a premixing type fitted thereto. A tip end portion of each of the supplemental burners 40 is positioned inside of the combustion chamber 11 through the corresponding air hole 31.
  • each of the supplemental burner 40 is disposed having extended through the peripheral wall 10b of the combustion liner 10 at a position downstream side of the main burner 21 in the combustion liner 10 so that a premixed air-fuel mixture M3 for use by the respective supplemental burner 40 can be injected into the combustion liner 10 to form a second combustion region S2 on a downstream side of the first combustion region S1 within the combustion chamber 11.
  • Figs. 3A to 3D illustrate the details of the pilot burner 20.
  • the pilot burner 20 has a straight burner axis C1 coaxial with a longitudinal axis C, shown in Fig. 2 , of the combustion liner 10 and includes an inflow passage 41 for the compressed air A, a premixing passage 43 and a plurality of first and second mixture injection holes 44A and 44B defined in a downstream end portion.
  • the inflow passage 41 is provided at an upstream end portion (left end side as viewed in Fig. 3A ) so as to allow the compressed air A to flow thereinto from a radially outer area to a radially inner area.
  • the premixing passage 43 is operable to mix the compressed air A and the fuel F inflowed through the inflow passage 41 and to guide the air-fuel mixture towards an axially downstream side (a right end side shown in Fig. 3A ).
  • the resultant air-fuel mixture M1 within the premixing passage 43 are injected through the premixed air-fuel mixture injection holes 44A and 44B into the combustion chamber 11 (shown in Fig. 2 ).
  • the inflow passage 41 has an outer periphery formed with an annular inflow opening 41 a defined therein.
  • a plurality of fuel supply holes 42 are provided radially inwardly of the inflow opening 41a for injecting the fuel F in a direction perpendicular to the direction of flow of the compressed air A in the inflow passage 41.
  • the premixing passage 43 referred to above has a speed increasing portion 45 having a passage sectional area that gradually decreases towards a downstream side.
  • the premixed air-fuel mixture M1 is injected through the premixed air-fuel mixture injection holes 44A and 44B after the flow velocity thereof has been increased as it pass through the speed increasing portion 45.
  • a mixing facilitation member 46 for facilitating mixing by deflecting the premixed air-fuel mixture M1 in a direction radially outwardly thereof is provided on an upstream side of the speed increasing portion 45 of the premixing passage 43.
  • a flame holding fuel passage 48 extending in a direction along the axis C1 is provided in a center portion of the pilot burner 20 with its downstream tip end communicated with a fuel injection hole 49. A portion of the fuel F for the pilot burner is injected into the combustion chamber (shown in Fig. 2 ) through the fuel injection hole 49.
  • the flame holding fuel passage 48 is defined by the hollow of a center tube P1.
  • the premixing passage 43 is an annular passage that is defined between a cylindrical body 20a forming a part of an outer wall of the premixing passage 43, closed at one end thereof and having a constricted portion (the speed increasing portion) 45, and the fuel tube P1 forming the flame holding fuel passage 48 at a center portion.
  • the fuel injection hole 49 is defined in a center portion of a tip end wall 20b of the pilot nozzle 20 and is in the form of a round hole of a diameter smaller than that of the flame holding fuel passage 48.
  • the cylindrical body 20a and the tip end wall 20b are formed integrally with each other.
  • the annular inflow opening 41a is provided with a plurality of, for example, twelve guide pieces 50 for guiding the compressed air A from the inflow opening 41a in a direction towards the center portion and those guide pieces 50 are spaced an equal distance from each other in a circumferential direction thereof.
  • Those guide pieces 50 are disposed between a disc-shaped nozzle plate 54 and an upstream end portion of the cylindrical body 20a and are fixed to the nozzle plate 54 and to the cylindrical body 20a by means of, for example, welding.
  • the plurality of the fuel supply holes 42 are arranged in a fashion coaxial with the nozzle plate 54.
  • the fuel supply holes 42 referred to above are so opened in a direction towards a radially inner area of the combustion liner 10 while communicated with a fuel reservoir space 55.
  • a fuel introduction passage 12a for introducing the fuel F into the fuel reservoir space 55 is formed between the nozzle plate 54 and an end plate 12. The fuel F flows into the fuel reservoir space 55 after having passed through the fuel introduction port 28 and then through the fuel introduction passage 12a. A portion of the fuel F is guided into the flame holding fuel passage 48 and the remaining portion of the fuel F is supplied into the inflow passage 41 through the fuel supply holes 42.
  • the nozzle plate 54 has a center portion thereof formed with a center projection 54a having its tip end representing an inverted conical shape.
  • This center projection 54a has a length somewhat greater than the height (length as measured along the axial direction) of any of the guide pieces 50.
  • the compressed air A having flowed through the inflow opening 41 a flows from a radially outer area in a direction radially inwardly thereof into gaps each delimited between the neighboring guide pieces 50, 50.
  • the number of the fuel supply holes 42 employed between the neighboring guide pieces 50 and 50 for injecting the fuel F in a direction perpendicular to the direction of flow of the compressed air A is chosen to be two and, therefore, the total number of the fuel supply holes 42 amounts to twenty four.
  • the fuel F is injected at multiple points and, also, since the fuel F divided in a circumferential direction by the guide pieces 50 is supplied into the inflow passage 41, a uniformly premixed air-fuel mixture having a minimized variation in concentration of the fuel F may be obtained.
  • the compressed air A is introduced towards a center side of the inflow opening 41a by means of the plurality of the guide pieces 50.
  • the compressed air A from the inflow opening 41a collides at the center portion of the inflow passage 41, resulting in a considerable turbulent flow.
  • mixing the compressed air A with the fuel F may be facilitated.
  • the premixed air-fuel mixture M1 obtained in this manner described above collides against the center projection 54a and is therefore smoothly deflected by 90° before it is introduced into the inner premixing passage 43.
  • the mixing facilitation member 46 As shown in Fig. 3C , the mixing facilitation member 46 referred to previously is of a structure in which an insertion hole 46a for receiving therein the center tube P1 of the flame holding fuel passage 48 is defined at a center portion thereof and a peripheral portion of the mixing facilitation member 46 has a plurality of, for example, four, radial projections 46b spaced an equal distance from each other in a direction circumferentially thereof.
  • This mixing facilitation member 46 may be made of, for example, a metallic plate by the use of any suitable punching work.
  • This mixture promoting member 46 when fixed to the center tube P1 at the insertion hole 46a thereof, is positioned upstream side of the speed increasing portion 45 in the premixing passage 43 and spaces 46c each delimited between the circumferentially neighboring projections 46b define respective flow paths for the premixed air-fuel mixture M2.
  • the plurality of, for example, twelve, first premixed air-fuel mixture injection holes 44A which are provided in the peripheral wall of the cylindrical body 20a.
  • Each of those first premixed air-fuel mixture injection holes 44A is so shaped as to be oriented in a direction slantwise radially outwardly, as shown in Fig. 3A . Accordingly, a portion of the premixed air-fuel mixture M1 injected from the premixed air-fuel mixture injection holes 44A flows towards the ignition plug 30 (shown in Fig. 2 ).
  • Fig. 4 illustrates the pilot burner 20 as viewed from a downstream side.
  • the pilot burner 20 has a tip end portion formed with the fuel injection hole 49 at a center portion which coincides with the axis C1 of the pilot burner 20, and the plurality of, for example, eight, second premixed air-fuel mixture injection holes 44B are provided around the fuel injection hole 49.
  • the plurality of, for example, eight, second premixed air-fuel mixture injection holes 44B are provided around the fuel injection hole 49.
  • a plurality of, for example, three, carbon removal injection holes 53 for supplying the premixed air-fuel mixture are provided on a radially outer side of the fuel injection hole 49 and a radially inner side of the circle depicted by the second premixed air-fuel mixture injection holes 44B.
  • Those carbon removal injection holes 53 are so formed as to be inclined inwardly so that as shown in Fig. 3A a portion of the premixed air-fuel mixture M1 within the premixing passage 43 may be injected towards a tip end of the fuel injection hole 49.
  • Each of the carbon removal injection holes 53 is so formed as to have an extremely small diameter that is comparable with that of the fuel injection hole 49.
  • a portion of the downstream end of the cylindrical body 20a of the pilot burner 20 is supported by the main inner peripheral wall 21a through an annular collar 57 of an L-sectioned configuration in a thermally deformable fashion.
  • the supplemental burner 40 has a structure substantially identical with that of the pilot burner 20 so far as a fuel injecting portion, which is positioned in an upstream area thereof, is concerned, and, therefore, the details thereof are not reiterated for the sake of brevity.
  • the fuel F supplied from the fuel supply device 5 through the fuel control device 6 shown in Fig. 1 is introduced from the fuel introduction port 28, shown in Fig. 3A , into the pilot burner 20.
  • a portion of the fuel F so introduced is guided by the fuel introduction passage 48 and is then injected from the fuel injection hole 49 into the combustion chamber 11 shown in Fig. 2 for flame holding purpose.
  • the flame stability and the ignitability may be improved.
  • the premix combustion accomplished by the pilot burner 20 is not adversely affected.
  • a major portion of the fuel F is introduced from the fuel supply holes 42 into the inflow passage 41.
  • the compressed air A from the compressor (shown in Fig. 1 ) is introduced into the inflow passage 41 in a radially inward direction from the radially outer area through guide gaps each delimited between the neighboring guide pieces 50 and 50.
  • the compressed air A and the fuel F are mixed crosswise and, therefore, the compressed air A and the fuel F are guided axially towards a downstream side through the inner premixing passage 43 while the mixing of the compressed air A and the fuel F is facilitated by a shearing force brought about by the compressed air A relative to the fuel F.
  • the compressed air A and the fuel F flow radially inwardly within the inflow passage 41 to collide each other, accompanied by the enhanced turbulent flow enough to facilitate the mixing.
  • the air-fuel mixture M1 is deflected by 90° when the air-fuel mixture M1 is guided from the inflow passage 41 into the premixing passage 43, a considerable turbulence occurs in the flow and, hence, the premixing is facilitated.
  • the premixed air-fuel mixture M1 is guided axially in a downstream direction through the premixing passage 43 that has a substantial length, the premixing is facilitated within this premixing passage 43.
  • the premixed air-fuel mixture M1 referred to above is injected into the combustion chamber 11 from the plurality of premixing air-fuel mixture injection holes 44A and 44B and, therefore, uneven distribution of the premixed air-fuel mixture within the combustion chamber 11 is suppressed.
  • the mixing facilitation member 46 Since the premixed air-fuel mixture M2 guided axially towards a downstream direction through the premixing passage 43 is deflected by the mixing facilitation member 46 radially outwardly, the turbulence becomes considerable and the premixing may be hence facilitated further. Also, since the mixing facilitation member 46 is provided in a portion of the premixing passage 43 upstream side of the speed increasing portion 45, where the passage section is larger, and, hence, the flow velocity there is not high, an undesirable increase of the flow resistance brought about by the mixing facilitation member 46 may be suppressed.
  • the premixed air-fuel mixture M2 which has passed through the mixing facilitation member 46, flows through the speed increasing portion 45 of a type having its passage section gradually decreasing in a downstream direction, accompanied by an increase of the flow velocity of the premixed air-fuel mixture M2. Therefore, an undesirable propagation of a back fire from the combustion chamber 11 (shown in Fig. 2 ) towards the premixing passage 43 may be avoided. With the back firing prevented in this way, damage to the pilot burner 20 may be avoided accordingly.
  • a portion of the premixed air-fuel mixture M1 which has passed through the speed increasing portion 45, is injected from the first premixed air-fuel mixture injection holes 44A in a slantwise radially outward direction. Another portion of this premixed air-fuel mixture M1 is injected from the second premixed air-fuel mixture injection holes 44B into the combustion chamber 11 (shown in Fig. 2 ), substantially outwards the axis C1. Also, the remaining portion of the premixed air-fuel mixture M1 is injected from the carbon removal injection hole 53 in a slantwise direction towards the tip end of the fuel injection hole 49 to thereby lower the fuel concentration in the vicinity of an outlet of the fuel injection hole 49. By so doing, an undesirable clogging of the fuel injection hole 49, which would be brought about by soot resulting from an excessive enrichment of the fuel, may be prevented.
  • the compressed air A and the fuel F may be sufficiently mixed together and, therefore, the pilot premixed air-fuel mixture M1 of a uniform concentration may be obtained.
  • the main premixed air-fuel mixture M2 is also supplied from the main burner 21, shown in Fig. 2 , into the combustion chamber 11.
  • a first combustion region, which the premixed air-fuel mixture M1 and the premixed air-fuel mixture M2 in this case form, is indicated by S1.
  • the supplemental burner 40 is also of a premixing type and, even from this supplemental burner 40, an auxiliary firing premixed air-fuel mixture M3 is supplied into and combusted within the combustion chamber 11.
  • a second combustion region in this case is indicated by S2.
  • the supplemental burner 40 is also of the premixing type, generation of NOx in the second combustion region S2 is suppressed and the emissions thereof may be reduced.
  • the amount of NOx may be considerably reduced as compared with a diffusion type which tends to be of a high temperature during the combustion and generates a substantial amount of NOx.
  • a conventional pilot burner 70 shown in Fig. 5 is of a diffusion combustion type.
  • the fuel F introduced from the fuel introduction port 28 is guided into the introducing passage 72, then injected from a fuel injection hole 74 at a tip end and finally mixed with the compressed air A at an area outwardly downstream of the pilot burner 70.
  • the mixing of the compressed air A and the fuel F is insufficient and only an air-fuel mixture of a varying concentration can be obtained. Because of this, the combustion temperature tends to elevate, thus rendering the NOx to be easily formed.
  • the main burner and the supplemental burner are of a premixing type.
  • the supplemental burner was not operated, but at black triangle markings in the comparative example (b) the supplemental burner was operated.
  • First and second examples represent the results of tests conducted on the engines mounted with the combustor according to the foregoing embodiment. In this instance, all of the pilot burner, the main burner and the supplemental burner are of the premixing type and, in the first example, the supplemental burner was not operated, but at black round marking in the second example, the supplemental burner was operated.
  • the NOx concentration has increased considerably with an increase of the load factor.
  • the NOx concentration has markedly decreased in the region in which the load factor is high.
  • the NOx concentration has decreased much smaller than that in the comparative example (a) as indicated by the downward oriented arrow Y1.
  • the lowering of the NOx emission in a quantity greater than that in the comparative example (b) as indicated by the arrow Y2 has been accomplished even within a region in which the load factor is high.

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  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP12829519.3A 2011-09-05 2012-08-07 Chambre de combustion de turbine à gaz Withdrawn EP2754963A4 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2011192549A JP5393745B2 (ja) 2011-09-05 2011-09-05 ガスタービン燃焼器
PCT/JP2012/070061 WO2013035474A1 (fr) 2011-09-05 2012-08-07 Chambre de combustion de turbine à gaz

Publications (2)

Publication Number Publication Date
EP2754963A1 true EP2754963A1 (fr) 2014-07-16
EP2754963A4 EP2754963A4 (fr) 2015-05-27

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EP12829519.3A Withdrawn EP2754963A4 (fr) 2011-09-05 2012-08-07 Chambre de combustion de turbine à gaz

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US (1) US20140182294A1 (fr)
EP (1) EP2754963A4 (fr)
JP (1) JP5393745B2 (fr)
WO (1) WO2013035474A1 (fr)

Cited By (2)

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WO2013035474A1 (fr) 2013-03-14
JP2013053814A (ja) 2013-03-21
EP2754963A4 (fr) 2015-05-27
JP5393745B2 (ja) 2014-01-22

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