EP1531305A1 - Injecteur de carburant multi-point - Google Patents

Injecteur de carburant multi-point Download PDF

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Publication number
EP1531305A1
EP1531305A1 EP03257138A EP03257138A EP1531305A1 EP 1531305 A1 EP1531305 A1 EP 1531305A1 EP 03257138 A EP03257138 A EP 03257138A EP 03257138 A EP03257138 A EP 03257138A EP 1531305 A1 EP1531305 A1 EP 1531305A1
Authority
EP
European Patent Office
Prior art keywords
nozzles
fuel
arrays
nozzle
fuel injector
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Withdrawn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
EP03257138A
Other languages
German (de)
English (en)
Inventor
Alexander G. Chen
Donald W. Kendrick
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies 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 Technologies Corp filed Critical United Technologies Corp
Priority to EP03257138A priority Critical patent/EP1531305A1/fr
Publication of EP1531305A1 publication Critical patent/EP1531305A1/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Withdrawn legal-status Critical Current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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2237/00—Controlling
    • F23N2237/02—Controlling two or more burners

Definitions

  • the present invention relates to a multi-point fuel injector for use in a combustor of a gas turbine engine or other types of combustors
  • a novel multi-point injector broadly comprises a plurality of nozzles arranged in at least two arrays and means for independently controlling a fuel flow to each array of nozzles.
  • Each of the nozzles in each array includes an outer body defining a fluid channel and vane means for creating a swirling flow within the fluid channel.
  • a method for injecting a fuel/air mixture into a combustor of a gas turbine engine broadly comprises the steps of providing an injector having nozzles arranged in at least two arrays, injecting a fuel/air mixture into the combustor stage by supplying fuel in a first quantity to each nozzle in an outermost one of the arrays and supplying fuel in a second quantity to each nozzle in a second one of the arrays; and maintaining the outermost one of the arrays at a flame temperature high enough to maintain a stable and less polluting flame.
  • FIG. 1 illustrates a first embodiment of a multipoint injector 10 in accordance with the present invention.
  • the multi-point injector 10 has nozzles 12 for injecting a fuel-air mixture into a combustor stage of a gas turbine engine.
  • the nozzles 12 are arranged in a plurality of arrays.
  • the nozzles 12 are arranged in four concentric rings 14, 16, 18, and 20 with an optional nozzle in the center. While the nozzle arrays have been shown to be concentric rings, it should be recognized that the nozzles 12 can be arranged in different configurations, including but not limited to squares, rectangles, hexagons, or parallel lines.
  • the fuel flow rate controlling means comprises a different fuel circuit 22 for each ring 14, 16, 18, and 20 and the optional center nozzle.
  • Each fuel circuit 22 may each comprise any suitable valve and conduit arrangement known in the art for allowing control over the flow rate of the fuel provided to each one of the rings 14, 16, 18 and 20 and to the optional center nozzle.
  • the flow of fuel is reduced differently for each ring 14, 16, 18 and 20 and the optional center nozzle.
  • the outermost ring 14 may be kept at a flame temperature that is high enough to keep the flame stable so that CO and UHC created from the combustor and dynamic pressure is low, but not so high that ring 14 creates excessive NOx.
  • the other rings 16, 18, and 20 and the optional center nozzle are preferably fueled at lower fuel/air ratios. As a result, lower flame temperature occurs at these rings to achieve more power reduction or to accommodate lower ambient temperature.
  • some or all of the other rings can be fueled at higher fuel/air ratios if better flame stability is wanted and if NOx limit and power setting/ambient temperature allow. Since nozzle rings 16, 18, and 20 do not interact with the cooler wall or cooling film on the combustor wall 24, the flame from the nozzles 12 in those rings will be less quenched, thus avoiding the creating of excessive CO and UHC. In this way, the CO and UHC emissions can be reduced at lower power settings of the engine or at lower ambient temperature. Since the nozzles 12 in ring 14 are kept at a high enough flame temperature as the power is reduced or ambient temperature is reduced, they can serve as flame stabilizers to stabilize the entire combustion process for all the nozzles 12 and extend lean blowout limit.
  • each ring 14, 16, 18, and 20 may define a zone and the injector may be provided with a means for controlling the flow of fuel to one zone as a function of the flow of fuel to a second zone.
  • the injector 10 and the method outlined above can be used in different kind of combustors (can or annular).
  • annular burneras shown in Figure 5 the flame temperatures in the zones near at least one of the combustor walls 24 is kept high enough to stablize the flame while leaning some others to reduce power or to accommodate lower ambient temperature.
  • the annular burner will have a plurality of nozzle rings such as nozzle rings 16, 18 and 20.
  • the zone which is kept hot to stabilize the flame preferably is the one next to a wall. In some instances, this may be the outermost ring of nozzles. In other instances, this may be the innermost ring of nozzles. In some situations, it may be desirable to keep an outer zone hot, a middle zone cool, and an inner zone hot.
  • FIG. 1 illustrates the use of four rings 14, 16, 18, and 20, the number of rings of nozzles can be arbitrary. Different rings of nozzles can be fueled differently to achieve the best emissions and stability.
  • FIGS. 2 and 3 illustrate an embodiment of an injector 10' which has three concentric rings 30, 32, and 34 of nozzles 12. The rings of nozzles 30, 32, and 34 may be fueled so that the outermost ring 30 and the innermost ring 34 are maintained hotter than the center ring 32. As before, each of the rings 30, 32, and 34 of nozzles 12 may be fueled via independent fuel circuits 22A, 22B, and 22C, respectively.
  • the centerbody portion 36 may be closed if desired or used to inject fuel or fuel/air mixture and an ignitor 38 may be positioned off center.
  • each nozzle 12 used in the embodiments of FIGS. 1 and 2 may have a construction such as that shown in FIG. 4.
  • each nozzle 12 may have an outer body 40, such as a cylindrical or other shape casing, an inner body 42 which is cylindrical, conical, rectangular and the like, centered or off-centered or even non-existent and one or more swirler vanes 44 extending between the inner body 42 and an inner wall 46 of the casing 40.
  • the swirler vanes 44 are used to create a swirling flow in the fluid channel 47 formed by the inner wall of the outer body 40 and the inner body 42. It has been found that the creation of the swirlingflow in the channel 47 promotes mixing of the fuel and air which reduces NOx and flame stabilization.
  • the swirler vanes 44 for a respective nozzle 12 may be in the same direction or in different directions.
  • Each nozzle 12 used in the embodiments of FIGS. 1 and 2 may have otherconstructions such as that shown in FIG. 6.
  • the fuel and air aretangentially injected from the outer wall of a swirl cup 58 via tangential inlets 60 and 62 respectively to create swirling motion.
  • the injection direction does not have to be perpendicular to the axis of the swirl cup 58.
  • One or more fuel inlets can be injecting fuel upstream or downstream of the air injection or injections, or in between air injections. Axial air or fuel or both can also be added.
  • vanes 44 may be omitted if desired.
  • each nozzle 12 is provided with a fuel/air mixture.
  • a fuel injection unit 49 may be placed adjacent the inlet 51 of the nozzle 12 for premixed flame or be placed adjacent to outlet 52 for diffusion flame.
  • the fuel injection unit 49 may have one or more fuel inlets 50 for delivering fuel to the interior of the fuel injection unit 49.
  • the fuel injection unit can also be an object hanging in the air stream.
  • the fuel inlet 50 can be upstream or downstream of the vanes 44, in the area of the vanes 44, in the vanes 44, from the wall of the outer body 40, or from the inner body 42
  • the fuel inlets 50 may be supplied with fuel from one of the fuel circuits 22A, 22B, and 22C. While the fuel injection unit 49 and nozzle 12 may be separate elements, they could also be a single integral unit. Further, a diffusion or premixed pilot can be added to the inner body 42.
  • the swirl vane angle does not have to be the same within the swirler, within the zone, or among different zones. Further, the outlet of all the nozzles does not have to be in one plane.
  • Liquid fuel can be prevaporized or directly injected into the nozzle 12.
  • the liquid fuel can be injected from the inner body 42, outer body 40, vanes, or from a separate injection unit or injection units.
  • the liquid fuel can be injected from the bottom of the swirl cup 58, the outer wall, the inlets 60, 62, or from a separate injection unit or injection units.
  • the nozzles 12 in each of the arrays in the embodiments of FIGS. 1 and 2 have outlets 52 which terminate in a common plane 54, although this is not mandatory. It has been found that by providing such a non-staggered nozzle arrargement, the nozzles 12 in one array, due to the arrangement and the turbulent flow exiting the nozzle 12, can aid combustion of the fuel/air mixture in the nozzles 12 of an adjacent array or within the array. This is highly desirable from the standpoint of promoting flame stability. Such assistance is less effective in arrangements where the nozzle outlets are staggered although it is still possible.
  • injectors 10 of the present invention it is possible to achieve the production of low quantities of NOx, CO and UHC for extended power range and ambient conditions.
  • NOx at a level of less than 7.0 ppm and to have both CO and UHC at levels less than 10 ppm for extended poweror ambient range.
  • the injectors of the present invention don't turn fuel off to a particular array or ring. Fuel is always fed to each nozzle in each array or ring. Thus, in the injectors of the present invention, one does not have to worry about a disabled zone quenching an enabled zone. As a result, one does not have to have annular baffles and/or axial separation. In the injectors of the present invention, the various arrays or rings of nozzles 12 are designed to interact with each other.
  • FIG. 7 illustrates a parallel array burner having five fuel zones 70, 72, 74, 76, 78 with each fuel zone being independently controlled for staging the flame temperature in at least one zone, preferably the zone near the burner wall 24, is kept high enough to stabilize the entire flame.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP03257138A 2003-11-12 2003-11-12 Injecteur de carburant multi-point Withdrawn EP1531305A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03257138A EP1531305A1 (fr) 2003-11-12 2003-11-12 Injecteur de carburant multi-point

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03257138A EP1531305A1 (fr) 2003-11-12 2003-11-12 Injecteur de carburant multi-point

Publications (1)

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EP1531305A1 true EP1531305A1 (fr) 2005-05-18

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EP03257138A Withdrawn EP1531305A1 (fr) 2003-11-12 2003-11-12 Injecteur de carburant multi-point

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7673454B2 (en) 2006-03-30 2010-03-09 Mitsubishi Heavy Industries, Ltd. Combustor of gas turbine and combustion control method for gas turbine
WO2010112318A1 (fr) * 2009-04-01 2010-10-07 Alstom Technology Ltd. Turbine à gaz présentant un meilleur comportement d'émission en charge partielle
CN102052158A (zh) * 2009-11-09 2011-05-11 通用电气公司 反向旋转式燃气涡轮机燃料喷嘴
RU2566621C2 (ru) * 2012-10-22 2015-10-27 Альстом Текнолоджи Лтд Способ работы газовой турбины с последовательным сгоранием и газовая турбина для осуществления указанного способа
WO2018212761A1 (fr) * 2017-05-16 2018-11-22 Siemens Aktiengesellschaft Schéma d'étagement de carburant binaire permettant d'améliorer les émissions de débit dans la combustion d'une turbine à gaz à pré-mélange pauvre

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3943705A (en) * 1974-11-15 1976-03-16 Westinghouse Electric Corporation Wide range catalytic combustor
US4356698A (en) * 1980-10-02 1982-11-02 United Technologies Corporation Staged combustor having aerodynamically separated combustion zones
EP0335978A1 (fr) * 1987-09-04 1989-10-11 Hitachi, Ltd. Bruleur de turbine a gaz
US5303542A (en) * 1992-11-16 1994-04-19 General Electric Company Fuel supply control method for a gas turbine engine
EP0620402A1 (fr) * 1993-04-15 1994-10-19 Westinghouse Electric Corporation Chambre de combustion à prémélange avec des passages annulaires concentriques
DE4412315A1 (de) * 1994-04-11 1995-10-12 Abb Management Ag Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine
US5469700A (en) * 1991-10-29 1995-11-28 Rolls-Royce Plc Turbine engine control system
EP0974789A1 (fr) * 1998-07-22 2000-01-26 Asea Brown Boveri AG Procédé de fonctionnement d'une chambre de combustion de turbine à gaz à carburant liquide
US6092363A (en) * 1998-06-19 2000-07-25 Siemens Westinghouse Power Corporation Low Nox combustor having dual fuel injection system
US6360525B1 (en) * 1996-11-08 2002-03-26 Alstom Gas Turbines Ltd. Combustor arrangement

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3943705A (en) * 1974-11-15 1976-03-16 Westinghouse Electric Corporation Wide range catalytic combustor
US4356698A (en) * 1980-10-02 1982-11-02 United Technologies Corporation Staged combustor having aerodynamically separated combustion zones
EP0335978A1 (fr) * 1987-09-04 1989-10-11 Hitachi, Ltd. Bruleur de turbine a gaz
US5469700A (en) * 1991-10-29 1995-11-28 Rolls-Royce Plc Turbine engine control system
US5303542A (en) * 1992-11-16 1994-04-19 General Electric Company Fuel supply control method for a gas turbine engine
EP0620402A1 (fr) * 1993-04-15 1994-10-19 Westinghouse Electric Corporation Chambre de combustion à prémélange avec des passages annulaires concentriques
DE4412315A1 (de) * 1994-04-11 1995-10-12 Abb Management Ag Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine
US6360525B1 (en) * 1996-11-08 2002-03-26 Alstom Gas Turbines Ltd. Combustor arrangement
US6092363A (en) * 1998-06-19 2000-07-25 Siemens Westinghouse Power Corporation Low Nox combustor having dual fuel injection system
EP0974789A1 (fr) * 1998-07-22 2000-01-26 Asea Brown Boveri AG Procédé de fonctionnement d'une chambre de combustion de turbine à gaz à carburant liquide

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007004864C5 (de) * 2006-03-30 2014-09-25 Mitsubishi Heavy Industries, Ltd. Brennkammer einer Gasturbine und Verbrennungssteuerverfahren für eine Gasturbine
DE102007004864B4 (de) * 2006-03-30 2010-08-19 Mitsubishi Heavy Industries, Ltd. Brennkammer einer Gasturbine und Verbrennungssteuerverfahren für eine Gasturbine
US7673454B2 (en) 2006-03-30 2010-03-09 Mitsubishi Heavy Industries, Ltd. Combustor of gas turbine and combustion control method for gas turbine
WO2010112318A1 (fr) * 2009-04-01 2010-10-07 Alstom Technology Ltd. Turbine à gaz présentant un meilleur comportement d'émission en charge partielle
US8434312B2 (en) 2009-04-01 2013-05-07 Alstom Technology Ltd. Gas turbine with improved part load emissions behavior
US8794008B2 (en) 2009-04-01 2014-08-05 Alstom Technology Ltd Methods of operation of a gas turbine with improved part load emissions behavior
CN102052158A (zh) * 2009-11-09 2011-05-11 通用电气公司 反向旋转式燃气涡轮机燃料喷嘴
RU2566621C2 (ru) * 2012-10-22 2015-10-27 Альстом Текнолоджи Лтд Способ работы газовой турбины с последовательным сгоранием и газовая турбина для осуществления указанного способа
US9518511B2 (en) 2012-10-22 2016-12-13 General Electric Technology Gmbh Method for operating a gas turbine with sequential combustion and gas turbine for conducting said method
WO2018212761A1 (fr) * 2017-05-16 2018-11-22 Siemens Aktiengesellschaft Schéma d'étagement de carburant binaire permettant d'améliorer les émissions de débit dans la combustion d'une turbine à gaz à pré-mélange pauvre
CN110612419A (zh) * 2017-05-16 2019-12-24 西门子公司 贫预混燃气涡轮机燃烧的改善调低排放的二元燃料分级方案
US11125437B2 (en) 2017-05-16 2021-09-21 Siemens Energy Global GmbH & Co. KG Binary fuel staging scheme for improved turndown emissions in lean premixed gas turbine combustion
CN110612419B (zh) * 2017-05-16 2022-01-25 西门子能源全球两合公司 贫预混燃气涡轮机燃烧的改善调低排放的二元燃料分级方案

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