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US3905192A - Combustor having staged premixing tubes - Google Patents

Combustor having staged premixing tubes Download PDF

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Publication number
US3905192A
US3905192A US501739A US50173974A US3905192A US 3905192 A US3905192 A US 3905192A US 501739 A US501739 A US 501739A US 50173974 A US50173974 A US 50173974A US 3905192 A US3905192 A US 3905192A
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US
United States
Prior art keywords
tube
burner
combination
movable
set forth
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
US501739A
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English (en)
Inventor
Robert M Pierce
Philip W Smith
Walter R Kaminski
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.)
RTX Corp
Original Assignee
United Aircraft Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to US501739A priority Critical patent/US3905192A/en
Priority to CA234,329A priority patent/CA1028511A/en
Priority to GB35665/75A priority patent/GB1489496A/en
Priority to IT26710/75A priority patent/IT1042151B/it
Priority to FR7526598A priority patent/FR2283321A1/fr
Priority to SE7509617A priority patent/SE7509617L/xx
Priority to JP50104875A priority patent/JPS5185033A/ja
Priority to DE19752538512 priority patent/DE2538512A1/de
Priority to IN1705/CAL/75A priority patent/IN142712B/en
Application granted granted Critical
Publication of US3905192A publication Critical patent/US3905192A/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F23R3/26—Controlling the air flow
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing

Definitions

  • a gas turbine engine having an annular burner with a plurality of staged premixing tubes extending from the forward end thereof. Each tube directs flow to the burner through two concentric flow passages. A movable tube section is arranged to direct all the air through both flow passages or just through one passage. Fuel is directed into the staged premixing tube for mixing with air flowing therethrough. Swirl vanes are provided in each of the flow passages to provide for rotation of air passing therethrough.
  • a centerbody is positioned within the inner flow passage providing a blufibody to promote recirculatory flow in the general region rearwardly of the centerbody. Cooling is provided around the primary zone of the burner so as to provide a minimum of cooling flow into the primary zone.
  • This invention relates to the controlled formation of objectionable or harmful exhaust emissions, such as unburned hydrocarbons, oxides of nitrogen, and carbon monoxide, from a gas turbine engine burner to maintain said objectionable or harmful exhaust emissions at an acceptable level.
  • a gas turbine engine burner ordinarily operates over a wide range of primary zone equivalence ratios while it is believed that the primary zone equivalence ratio should be maintained within a narrow range.
  • Prior devices have provided means for varying the distribution of airflow within a burner and means for providing atomization, premixing and substantial vaporization but these means have not been set forth such as the device described herein.
  • a primary object of the present invention is to provide a burner with staged premixing tubes to control the formation of objectionable or harmful exhaust emissions in a gas turbine engine burner.
  • a staged premixing tube which varies the distribution of airflow within the burner and provides fuel atomization. fuel-air premixing and substantial vaporization of the fuel prior to injection into the burner.
  • An object of this present invention is to provide a device which will vary the distribution of airflow, and provide atomization, premixing and substantial vaporization of the fuel with a minimum of mechanical complexity, a high degree of reliability and a high degree of premixing effectiveness.
  • all of the airflow entering the primary zone of the burner is intimately premixed with the fuel to entry into the burner over a range of different airflow rates and different burner airflow distributions.
  • Another object of this invention is to provide a staged premixing tube having two concentric annular flow passages which exit into the burner; under conditions of low airflow only the smaller diameter annular flow passage is used while under conditions of high airflow both the smaller and larger diameter annular passages are used.
  • Another object of the invention is to provide means for closing and opening the larger diameter annular passage and at the same time provide acceptable aerodynamic contours in both the inner and outer passages so that high mixture velocities can be maintained in all parts of the passages.
  • a further object of the invention is to provide a staged premixing tube that allows the dissemination of fuel into the two annular passages to be varied in terms of the relative portions of fuel entering the inner and outer passages.
  • Another object of the invention is to provide a movable inner tube of bellmouth cross section, said bell mouth piece. or tube, can direct the total airflow and fuel flow into the smaller diameter passage for low power engine operation and permit flow into both passages for high power engine operation.
  • a further object of the invention is to provide a device for variably apportioning the airflow entering a burner to the primary combustion zone and to a secondary dilution zone to allow the establishment of a plurality of engine burner airflow distribution design points.
  • Another object of this invention is to provide a de vice wherein at low power operation, a primary zone equivalence ratio is high enough to support efficient combustion and provide an adequate margin of operation above the lean blow out limit; and at high power operation, the primary zone equivalence ratio is as low as possible to avoid the formation of large concentration levels of NO,.
  • FIG. 1 is a view of a gas turbine engine showing the location of the burner having staged premixing tubes.
  • FIG. 2 is an enlarged sectional view of the combustion section showing the burner and a staged premixing tube.
  • FIG. 3 is an enlarged view of a staged premixing tube in a position for low power operation.
  • FIG. 4 is an enlarged view of a staged premixing tube in a position for high power operation.
  • FIG. 5 is a view taken along the line 5-5 of FIG. 4.
  • FIG. 1 gas turbine power plant is shown indicated generally by l.
  • the power plant has a compressor section 2, a combustion section 4, a turbine section 6 and an exhaust section 8.
  • the combustion section 4 is comprised of an annular burner casing I0 with an annular burner 12 therein.
  • a conventional fuel supply and metering control 9 provides the desired fuel flow to an annular manifold II. Separate conduits 13 extend inwardly for a purpose to be hereinafter described.
  • the annular burner 12 has a plurality of staged premixing tube 20 extending from the forward end thereof for delivering the combustion airflow and fuel into the primary zone 22 of the burner 12.
  • Annular flanges 24 and 26 extend from each side of the annular opening 27 at the rear end of the annular burner 12 for positioning the rear end of the burner 12 in the annular burner case I0. These flanges 24 and 26 engage mating flanges 36 and 38 respectively which project forwardly from the rear of the annular burner case 10 adjacent the turbine section 6. This positioning means places the exit of the burner 10 at the entrance to the turbine section for directing gas flow into turbine vanes 40.
  • the annular burner 12 is made having its forward portion which encloses the primary zone 22 formed of double-walled construction with a solid inner wall 25 and outer wall 29 having a plurality of cooling holes 44 to provide for impingement cooling of wall 25.
  • the cooling air after it has completed its cooling function flows from between the double-walled construction over the inner wall of the remainder of the burner 12 so as not to enter the primary zone 22.
  • the rear part of the burner 12 which encloses the dilution zone has its walls formed on conventional louver construction with dilution openings 46 located adjacent the rear of the double-walled construction and dilution holes 48 located rearwardly thereof towards the annular openings 27 at the rear of the burner.
  • a cylindrical receptor 100 is mounted on the front of the annular burner 12 where each staged premixing tube 20 is desired. While the cylindrical receptor 100 is shown welded to the double-walled construction of the annular burner l2, it is to be understood the cylindrical receptor 100 may be connected by any other means.
  • the cylindrical receptor 100 has an annular flange 102 mounted therearound for a purpose to be hereinafter described.
  • Each staged premixing tube 20 comprises three main parts, these are (l) and outer tube 52, (2) a shorter inner tube 54 having a centerbody 55, and (3) a movable bellmouth piece 56.
  • the outer tube 52 has an enlarged inlet section 58 which is tapered inwardly as it extends rearwardly to a reduced area center section 59. This inlet section 58 directs incoming airflow from a forward opening 50 into the premixing tube 20.
  • the inner tube 54 is located in the rear end portion of the outer tube 52 and with the centerbody S divides the tube into two concentric flow passages 60 and 62.
  • the inner tube 54 is supported within the outer tube 52 by swirl vanes 64.
  • the centerbody 55 is positioned in the inner tube 54 by swirl vanes 68.
  • the centerbody 55 while spacing the inner ends of the vanes 68, also serve as an aerodynamic bluff-body. promoting recirculatory flow in the general region just rearwardly of the centerbody.
  • An opening 57 extends through the center of the centerbody S5 to aid in purging the region immediately adjacent to the centerbody of combusting flow.
  • the swirl vanes 64 and swirl vanes 68 are placed in a manner so that airflow leaves the concentric flow passages 60 and 62 swirling in different directions. If desired, these vanes can also be placed in a manner so that airflow leaves the flow passages swirling in the same direc' tion.
  • the inner tube 54 extends in length from the rear end of the outer tube 52 forwardly to the reduced area center section 59.
  • This inner tube 54 tapers outwardly from its forward end to its rearward end where it is attached by the swirl vanes 64 to the outer tube 52.
  • the center body 55 also tapers outwardly from its forward end to its rearward end where it is supported within the inner tube 54 by the swirl vanes 68.
  • the cross-sectional area of the flow passages 60 and 62 remains substantially constant throughout their length.
  • the movable bellmouth piece 56 is shaped so that its rearward end 70 has a slidable engagement within the forward end of the inner tube 54 when the bellmouth piece 56 is in its rearward position and the forward edge contacts the inner surface of the outer tube 52 where it tapers inwardly to the reduced area center section 59 (see FIG. 3).
  • the bellmouth piece 56 When the bellmouth piece 56 is in its forward position, it is located so as to present as little interference as possible with airflow passing thereby.
  • the contour of the bellmouth piece 56 is such that in its rearward position the forward edge coacts with the inner wall of the inlet section 58 and the rearward end 70 coacts with the forward end of the inner tube 54 to provide an acceptable aerodynamic contour to direct inlet flow into only the smaller diameter annular passage 62, and in its forward position it is positioned within the forward part of the outer tube 52 so that flow is directed smoothly into both of the concentric flow passages 60 and 62.
  • the slidable engagement of the rearward end of the bellmouth piece 56 with the forward end of the inner tube 54 is of such a length that a small gap is permitted at A to permit airflow there through before the bellmouth piece 56 disengages the inner tube 54 as it moves forwardly.
  • Each staged premixing tube 20 has an annular flange 104 extending outwardly from the midportion of the outer tube 52. This flange 104 is positioned on the outer tube 52 so that when the rearward end of the staged premixing tube 20 reaches the end of the cylindrical receptor 100 adjacent the inner part of the burner 12, it will engage the cylindrical flange 102 of the cylindrical receptor 100. These flanges are fixed together to retain the staged premixing tube 20 in its proper operating position.
  • the rearward end of the staged premixing tube 20 has a plurality of radial projections 106 extending therefrom which guide the end of the staged premixing tube 20 when it is being inserted in the cylindrical receptor 100 and provides for any flow of cooling air which may pass thereby. If necessary, openings 108 can be provided in flange 104 to allow a minimum of cooling air to enter the space between the outer tube 52 and cylindrical receptor 100.
  • fuel is delivered to an annular manifold 11 which distributes the fuel to separate conduits 13, each conduit leading to a fuel atomizer or nozzle, 72 ofa staged premixing tube.
  • Each fuel nozzle is mounted in the inlet section 58 of the outer tube 52, by means of three struts 74.
  • the outer ends of the struts 74 are fixed to the inner surface of the inlet section 58 of the outer tube 52 and the inner ends are fixed to a cylindrical housing 76 of the fuel nozzle 72.
  • Each conduit 13 extends through the wall of the discharge passage 42 of the compressor section 2 into a hollow strut 79.
  • the conduit 13 then is angled in the strut 79 so that it extends to the front of the housing 76 of the nozzle 72 in an aligned manner which will be hereinafter described.
  • the conduit 13 is connected within the housing 76 to direct the flow of fuel exit openings in the face of the nozzle 72.
  • the conduit 13 can be located in other positions to direct fuel to the nozzles 72.
  • the face of the fuel nozzle 72 is positioned adjacent the rear end of the bellmouth piece 56, when the bellmouth piece 56 is in its forward position so that fuel will be injected into both concentric flow passages 60 and 62.
  • the fuel atomizer or nozzle 72 can have its design varied as long as basic requirements for atomization and dispersion are met. While one fuel nozzle 72 has been shown, dual nozzles can be used if desired.
  • Actuating means 78 are provided for actuating the bellmouth piece 56 and include a sleeve 80 which has axial movement over the cylindrical housing 76 of the nozzle 72. Slots 81 are provided for the struts 74 which extend between the outer tube 52 and the fuel nozzle 72. The forward end of the bellmouth piece 56 is connected to the rearward end of the sleeve 80 by arms 82.
  • a rack 84 is located along the side of the sleeve 80 and V is engaged by a pinion gear 86 which is mounted on the end of a shaft 88 which extends to the exterior of the annular burner case 10.
  • a control device 90 is connected to each shaft 88 for rotating its associated pinion gear 86 to translate its associated sleeve 80 and bellmouth piece 56. It can be seen that rotation of the pinion gear 86 will axially move the bellmouth piece 56 between its forward and rearward positions. If additional means are desired to additionally support the sleeve 80 at its forward end, an arm can extend rearwardly from the rear of a strut 79.
  • This arm could be formed around a conduit 13 extending from a strut since the conduit 13 is positioned so that the cylindrical sleeve 80 will be permitted axial movement thereover. It is to be recognized that other known actuating means can be used to translate the bellmouth piece 56.
  • control devices 90 can be operated, for example, in any of the following manners: (1) all of the control devices 90 can be interconnected so that the bcllmouth piece 56 of each staged premixer tube 20 directs flow only into passage 62 for low power engine operation until a predetermined higher power setting is reached and then the bellmouth pieces 56 of all of the staged premixing tubes 20 can be moved directly to an open position permitting flow to both flow passages 60 and 62; (2) all of the control devices 90 can be interconnected so that the bellmouth piece 56 of each staged premixing tube will move from a low power setting by a predetermined schedule until it reaches a predetermined higher power setting and at that time the bellmouth pieces 56 can all move directly to an open position; (3) all of the control devices 90 can be interconnected so that the bellmouth pieces 56 of individual staged premixing tubes 20 will be actuated in a predetermined sequence around the circumference of the annular burner 12, when one tube
  • each tube can be operated such as set forth in manner (1) or in manner (2 It is to be understood other types of operation can be used depending on power requirements for any specific engine.
  • a staged premixing tube for directing a mixed fuel-air flow into a burner
  • said staged premixing tube having an outer tube for receiving fuel and air
  • said outer tube having an inner tube located therein adjacent its rear end forming a first inner passage and a second annular passage therearound
  • said outer tube having a movable tube located therein forwardly of said inner tube, said movable tube being movable between a first position where it directs all of the flow in said outer tube through said first inner passage to a second position where all of the flow is directed through both of said first and second passages.
  • said outer tube is formed having an inlet connected to a smaller center section by a first inwardly tapered section, the forward end of said inner tube being positioned adjacent said smaller center section, said movable tube being formed having a large forward end with a second inwardly tapered section and a smaller rear end, when said movable tube is in its first position its rear end contacts the forward end of the inner tube while its forward end contacts the first inwardly tapered section of the outer tube.
  • first swirl vanes are positioned in said first inner passage and second swirl vanes are positioned in said second annular passage
  • first swirl vanes are positioned in said first inner annular passage and second swirl vanes are positioned in said second annular passage.
  • each staged premixing tube having an outer tube for receiving fuel and air
  • each outer tube having an inner tube located therein forming a first inner passage and a second annular passage thercaround
  • each outer tube having a movable tube located therein forwardly of said inner tube, each movable tube being movable between a first position where it directs all of the flow entering its outer tube through the first inner passage to a second position where all of the flow is directed through both of said first and second passages.
  • annular burner has a plurality of receptors extending forwardly thereof, each receptor being positioned to receive a staged premixing tube, each prernixing tube being positioned in a receptor so that the rear end thereof is positioned adjacent the forward end of the burner.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Incineration Of Waste (AREA)
US501739A 1974-08-29 1974-08-29 Combustor having staged premixing tubes Expired - Lifetime US3905192A (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
US501739A US3905192A (en) 1974-08-29 1974-08-29 Combustor having staged premixing tubes
CA234,329A CA1028511A (en) 1974-08-29 1975-08-26 Gas turbine engine combustor having staged premixing tubes
IT26710/75A IT1042151B (it) 1974-08-29 1975-08-29 Combustore per motori a turbina a gas con tubi premiscelatori a stadi
FR7526598A FR2283321A1 (fr) 1974-08-29 1975-08-29 Chambre de combustion ayant des tubes de premelange etage
GB35665/75A GB1489496A (en) 1974-08-29 1975-08-29 Gas turbine engines and premixing tubes therefor
SE7509617A SE7509617L (sv) 1974-08-29 1975-08-29 Brennare med delade forblandarror
JP50104875A JPS5185033A (it) 1974-08-29 1975-08-29
DE19752538512 DE2538512A1 (de) 1974-08-29 1975-08-29 Brennkammer mit abgestuften vormischungsrohren
IN1705/CAL/75A IN142712B (it) 1974-08-29 1975-09-03

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US501739A US3905192A (en) 1974-08-29 1974-08-29 Combustor having staged premixing tubes

Publications (1)

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US3905192A true US3905192A (en) 1975-09-16

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US501739A Expired - Lifetime US3905192A (en) 1974-08-29 1974-08-29 Combustor having staged premixing tubes

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US (1) US3905192A (it)
JP (1) JPS5185033A (it)
CA (1) CA1028511A (it)
DE (1) DE2538512A1 (it)
FR (1) FR2283321A1 (it)
GB (1) GB1489496A (it)
IN (1) IN142712B (it)
IT (1) IT1042151B (it)
SE (1) SE7509617L (it)

Cited By (40)

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US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
US4180974A (en) * 1977-10-31 1980-01-01 General Electric Company Combustor dome sleeve
FR2465080A1 (fr) * 1979-09-17 1981-03-20 Snecma Dispositif de suspension aval de chambre de combustion pour turbomachines
US4321794A (en) * 1979-03-20 1982-03-30 Rolls-Royce Limited Gas turbine engine fuel burners
US4362021A (en) * 1979-08-01 1982-12-07 Rolls-Royce Limited Gas turbine engine fuel injectors
FR2516169A1 (fr) * 1981-11-07 1983-05-13 Rolls Royce Injecteur de carburant pour moteurs a turbines a gaz
US4497170A (en) * 1982-07-22 1985-02-05 The Garrett Corporation Actuation system for a variable geometry combustor
US4532762A (en) * 1982-07-22 1985-08-06 The Garrett Corporation Gas turbine engine variable geometry combustor apparatus
US4589260A (en) * 1982-11-08 1986-05-20 Kraftwerk Union Aktiengesellschaft Pre-mixing burner with integrated diffusion burner
US4606190A (en) * 1982-07-22 1986-08-19 United Technologies Corporation Variable area inlet guide vanes
US4984429A (en) * 1986-11-25 1991-01-15 General Electric Company Impingement cooled liner for dry low NOx venturi combustor
EP0441542A1 (en) * 1990-02-05 1991-08-14 General Electric Company Combustor and method of combusting fuel
US5207064A (en) * 1990-11-21 1993-05-04 General Electric Company Staged, mixed combustor assembly having low emissions
US5377483A (en) * 1993-07-07 1995-01-03 Mowill; R. Jan Process for single stage premixed constant fuel/air ratio combustion
US5572862A (en) * 1993-07-07 1996-11-12 Mowill Rolf Jan Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules
US5613357A (en) * 1993-07-07 1997-03-25 Mowill; R. Jan Star-shaped single stage low emission combustor system
US5628182A (en) * 1993-07-07 1997-05-13 Mowill; R. Jan Star combustor with dilution ports in can portions
US5638674A (en) * 1993-07-07 1997-06-17 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
EP0831275A2 (en) * 1996-09-24 1998-03-25 Mitsubishi Heavy Industries, Ltd. Annular type gas turbine combustor
US5737921A (en) * 1994-04-20 1998-04-14 Rolls-Royce Plc Gas turbine engine fuel injector
US5924276A (en) * 1996-07-17 1999-07-20 Mowill; R. Jan Premixer with dilution air bypass valve assembly
WO2001023807A1 (en) 1999-09-27 2001-04-05 Pratt & Whitney Canada Corp. Variable premix-lean burn combustor
US6220034B1 (en) 1993-07-07 2001-04-24 R. Jan Mowill Convectively cooled, single stage, fully premixed controllable fuel/air combustor
US6272842B1 (en) * 1999-02-16 2001-08-14 General Electric Company Combustor tuning
US6286300B1 (en) 2000-01-27 2001-09-11 Honeywell International Inc. Combustor with fuel preparation chambers
US6508061B2 (en) * 2001-04-25 2003-01-21 Pratt & Whitney Canada Corp Diffuser combustor
US6925809B2 (en) 1999-02-26 2005-08-09 R. Jan Mowill Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities
US20100024427A1 (en) * 2008-07-30 2010-02-04 Rolls-Royce Corporation Precision counter-swirl combustor
US20100162713A1 (en) * 2008-12-31 2010-07-01 Shui-Chi Li Cooled flameholder swirl cup
US20140305128A1 (en) * 2013-04-10 2014-10-16 Alstom Technology Ltd Method for operating a combustion chamber and combustion chamber
US20140311151A1 (en) * 2011-11-16 2014-10-23 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
WO2014204449A1 (en) * 2013-06-18 2014-12-24 Woodward, Inc. Gas turbine engine flow regulating
US20150338101A1 (en) * 2014-05-21 2015-11-26 General Electric Company Turbomachine combustor including a combustor sleeve baffle
US20160010866A1 (en) * 2013-02-19 2016-01-14 United Technologies Corporation Aerating fuel injector system for a gas turbine engine
US20160097535A1 (en) * 2013-03-12 2016-04-07 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9482433B2 (en) 2013-11-11 2016-11-01 Woodward, Inc. Multi-swirler fuel/air mixer with centralized fuel injection
US9587833B2 (en) 2014-01-29 2017-03-07 Woodward, Inc. Combustor with staged, axially offset combustion
DE102017120370A1 (de) * 2017-09-05 2019-03-07 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) Brennerkopf, Brennersystem und Verfahren zum Betreiben des Brennersystems
US11339970B1 (en) 2020-12-07 2022-05-24 Rolls-Royce Plc Combustor with improved aerodynamics
US11353215B1 (en) * 2020-12-07 2022-06-07 Rolls-Royce Plc Lean burn combustor

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US5257499A (en) * 1991-09-23 1993-11-02 General Electric Company Air staged premixed dry low NOx combustor with venturi modulated flow split
DE4408136A1 (de) * 1994-03-10 1995-09-14 Bmw Rolls Royce Gmbh Verfahren und Vorrichtung zur Kraftstoff-Aufbereitung für eine Gasturbinen-Brennkammer
DE19507088B4 (de) * 1995-03-01 2005-01-27 Alstom Vormischbrenner
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DE19516798A1 (de) * 1995-05-08 1996-11-14 Abb Management Ag Vormischbrenner mit axialer oder radialer Luftzuströmung
DE19527453B4 (de) * 1995-07-27 2009-05-07 Alstom Vormischbrenner
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DE19547913A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19547912A1 (de) * 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19649486A1 (de) * 1996-11-29 1998-06-04 Abb Research Ltd Brennkammer
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FR2516169A1 (fr) * 1981-11-07 1983-05-13 Rolls Royce Injecteur de carburant pour moteurs a turbines a gaz
US4497170A (en) * 1982-07-22 1985-02-05 The Garrett Corporation Actuation system for a variable geometry combustor
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US6220034B1 (en) 1993-07-07 2001-04-24 R. Jan Mowill Convectively cooled, single stage, fully premixed controllable fuel/air combustor
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US5918459A (en) * 1996-09-24 1999-07-06 Mitsubishi Heavy Industries, Ltd, Annular type gas turbine combustor
US6272842B1 (en) * 1999-02-16 2001-08-14 General Electric Company Combustor tuning
US6925809B2 (en) 1999-02-26 2005-08-09 R. Jan Mowill Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities
WO2001023807A1 (en) 1999-09-27 2001-04-05 Pratt & Whitney Canada Corp. Variable premix-lean burn combustor
US6253538B1 (en) 1999-09-27 2001-07-03 Pratt & Whitney Canada Corp. Variable premix-lean burn combustor
US6286300B1 (en) 2000-01-27 2001-09-11 Honeywell International Inc. Combustor with fuel preparation chambers
US6508061B2 (en) * 2001-04-25 2003-01-21 Pratt & Whitney Canada Corp Diffuser combustor
US20100024427A1 (en) * 2008-07-30 2010-02-04 Rolls-Royce Corporation Precision counter-swirl combustor
US8590313B2 (en) * 2008-07-30 2013-11-26 Rolls-Royce Corporation Precision counter-swirl combustor
US20100162713A1 (en) * 2008-12-31 2010-07-01 Shui-Chi Li Cooled flameholder swirl cup
US8281597B2 (en) 2008-12-31 2012-10-09 General Electric Company Cooled flameholder swirl cup
US20140311151A1 (en) * 2011-11-16 2014-10-23 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
US20160010866A1 (en) * 2013-02-19 2016-01-14 United Technologies Corporation Aerating fuel injector system for a gas turbine engine
US20160097535A1 (en) * 2013-03-12 2016-04-07 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US10208956B2 (en) * 2013-03-12 2019-02-19 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US20140305128A1 (en) * 2013-04-10 2014-10-16 Alstom Technology Ltd Method for operating a combustion chamber and combustion chamber
US10544736B2 (en) * 2013-04-10 2020-01-28 Ansaldo Energia Switzerland AG Combustion chamber for adjusting a mixture of air and fuel flowing into the combustion chamber and a method thereof
CN105899878B (zh) * 2013-06-18 2018-11-13 伍德沃德有限公司 燃气涡轮燃烧室组件及发动机及相关联的操作方法
WO2014204449A1 (en) * 2013-06-18 2014-12-24 Woodward, Inc. Gas turbine engine flow regulating
CN105899878A (zh) * 2013-06-18 2016-08-24 伍德沃德有限公司 燃气涡轮发动机流调节
US10408454B2 (en) 2013-06-18 2019-09-10 Woodward, Inc. Gas turbine engine flow regulating
US9482433B2 (en) 2013-11-11 2016-11-01 Woodward, Inc. Multi-swirler fuel/air mixer with centralized fuel injection
US10415832B2 (en) 2013-11-11 2019-09-17 Woodward, Inc. Multi-swirler fuel/air mixer with centralized fuel injection
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US9587833B2 (en) 2014-01-29 2017-03-07 Woodward, Inc. Combustor with staged, axially offset combustion
US20150338101A1 (en) * 2014-05-21 2015-11-26 General Electric Company Turbomachine combustor including a combustor sleeve baffle
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DE102017120370B4 (de) 2017-09-05 2019-06-06 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennerkopf, Brennersystem und Verfahren zum Betreiben des Brennersystems
US11339970B1 (en) 2020-12-07 2022-05-24 Rolls-Royce Plc Combustor with improved aerodynamics
US11353215B1 (en) * 2020-12-07 2022-06-07 Rolls-Royce Plc Lean burn combustor
US11603993B2 (en) 2020-12-07 2023-03-14 Rolls-Royce Plc Combustor with improved aerodynamics

Also Published As

Publication number Publication date
DE2538512A1 (de) 1976-03-11
IT1042151B (it) 1980-01-30
CA1028511A (en) 1978-03-28
FR2283321B1 (it) 1980-01-04
JPS5185033A (it) 1976-07-26
FR2283321A1 (fr) 1976-03-26
GB1489496A (en) 1977-10-19
SE7509617L (sv) 1976-03-01
IN142712B (it) 1977-08-20

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