US3792581A - System and method used in a gas turbine engine for minimizing nitrogen oxide emission - Google Patents

System and method used in a gas turbine engine for minimizing nitrogen oxide emission Download PDF

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Publication number
US3792581A
US3792581A US00203546A US3792581DA US3792581A US 3792581 A US3792581 A US 3792581A US 00203546 A US00203546 A US 00203546A US 3792581D A US3792581D A US 3792581DA US 3792581 A US3792581 A US 3792581A
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United States
Prior art keywords
combustor
air
gas turbine
turbine engine
preliminary
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Expired - Lifetime
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US00203546A
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English (en)
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N Handa
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Nissan Motor Co Ltd
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Nissan Motor Co Ltd
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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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • 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

Definitions

  • ABSTRACT A system and method used in a gas turbine engine for minimizing nitrogen oxide content in the exhaust gases of the gas turbine engine. According to the method having the step of feeding partially contaminated air at least into primary air intakes of the combustor of the gas turbine engine, the system comprises a preliminary combustor for putting the step into practice.
  • the preliminary combustor includes primary air intakes com municating with the air compressor of the gas turbine engine for receiving primary air therefrom, additional air intakes communicating with the air compressor for receiving therefrom additional air as a diluent, a fuel injector communicating with the fuel pump of the gas turbine engine for receiving a liquid fuel therefrom, and an outlet connected to the combustor or the air compressor upstream thereof for introducing the diluted burned gases into the combustor of the gas turbine engine as primary air therefor.
  • the system may be provided with a heat exchanger interposed between the outlet of the preliminary combustor and the primary air intakes of the gas turbine engine for improving reduction efficiency of the nitrogen oxide emission.
  • the present invention relates to a gas turbine engine and, more particularly, to a system used in a gas turbine engine for minimizing nitrogen oxide content in the exhaust gases thereof.
  • a gas turbine engine is advantageous in that, since it can maintain a continuous combustion with a sufficient amount of additional diluent air existing, reaction intermediates such as carbon monoxide or hydrocarbons are reduced to a minimum level.
  • reaction intermediates such as carbon monoxide or hydrocarbons are reduced to a minimum level.
  • reaction itself takes place in an intensively stirred condition in an environment of abundant oxidizer, so that nitrogen oxide content in the exhaust gases sometimes assumes a considerable value.
  • the present invention contemplates to calm down the intensity of the reaction experienced in the combustion chamber of the gas turbine engine.
  • air which contains more inert' composition than ambient fresh air is fed at least into primary air intakes of the combustion chamber. This is based on my experiment, in which the air used has been partially contaminated with burned gases before it is introduced into the combustion chamber.
  • a preliminary combustor is provided, which may communicate either with the primary air intakes of the gas turbine engine or with the upstream of the air compressor of the gas turbine engine.
  • the contaminated air is used as a primary air in the former case, while it is distributed not only to the primary air intakes but to the additional (secondary and/or tertiary) air intakes, in the latter case.
  • a heat exchanger may be provided for cooling the contaminated air through heat transfer.
  • FIG. 1 is a flow chart illustrating the basic concept of the present invention
  • FIG. 2 is a flow chart illustrating one embodiment of the invention
  • FIG. 3 is a sectional view showing a nitrogen oxide content minimizing system diagrammatically shown in FIG. 2;
  • FIG. 4 is similar to FIG. 2 but shows another slightly modified embodiment of FIG. 2;
  • FIG. 5 is similar to FIG. 2 but shows a further embodiment of the invention.
  • a common gas turbine engine as generally designated at numeral is provided with a combustor which includes a combustion chamber 11, a swirler 12 and a fuel injector 13.
  • the fuel injector 13 has fluid communication with a fuel pump 14 for receiving a liquid fuel therefrom.
  • a turbine 15 is also provided in the gas turbine engine 10 for extracting an output power from the energy contained in the combustion products of the combustion chamber 11. Compressed air is supplied to the combustion chamber 11 by an air compressor 16 as secondary and tertiary air, as shown.
  • partially contaminated air is supplied as primary air to the combustion chamber 11 through the swirler 12.
  • the contaminated air can be produced in any suitable fashion, but a practical advantage is obtained if it is composed of burned gases, as has been discussed.
  • a system 20 is provided for minimizing nitrogen oxide content in the exhaust gases of the main combustor l l.
  • the system 20 of the invention is provided with a preliminary combustor 21 which is mounted in an elongated annular air conduit 22 of the main combustor 1 l.
  • the preliminary combustor 21 includes primary air intakes 23 and additional air intake 24, for example, secondary and tertiary air intakes. Ambient fresh air supplied from the air compressor 16 is distributed in accordance with predetermined openings of the air intakes 23 and 24.
  • a sufficient amount of the supplied air is introduced into the preliminary combustor 21 through the additional air intakes 24 so as to dilute and cool down the burned gases, which :are mainly produced by the combustion of an injected fuel with air supplied from the primary air intakes 23.
  • a suitable liquid fuel is injected into the preliminary combustor 21 by a fuel injector 25, which is in communication with the fuel pump 14 through a fuel regulator 26.
  • An outlet 27 of the preliminary combustor 21 is directly secured to the main combustor 11 at the upstream of the swirler 12, as shown.
  • An ignition plug 26 may be mounted on the preliminary combustor 21 for igniting a liquid fuel supplied from the fuel injector- 25.
  • the preliminary combustor 21 can be considered a burned gas generator for feeding the partially contaminated air to the main combustor 11, because the burned gases are highly diluted with the additional air.
  • the primary air containing burned gases and remaining oxygen gases is introduced into the main combustor 11 through the swirler 12.
  • a liquid fuel pumped out by the fuel pump 14 is metered at a fuel regulator 28 and, then, is supplied to the fuel injector 13 of the main combustor 11.
  • the liquid fuel injected by the fuel injector 13 is ignited by an ignition plug 29, which is mounted on the main combustor 11.
  • Additional diluent air supplied through the elongated annular air conduit 22 is concurrently introduced into the main combustor 11 through secondary and tertiary air intakes 31 and 32, which are formed in the housing of the main combustor l 1. From a practical standpoint, the best result can be obtained when fuel flow rates respectively supplied to the preliminary and main combustois 21 and 11 are l 9.
  • the preliminary combustor 21 is operated not only as a burned gas generator during all the driving modes but I as a power generator during idling and light load ditions.
  • the main combustor 11 be operated only when the automobile is under 1 load condition. This operational characteristics uld also be appreciated in view of fuel consumption nomy.
  • FIG. 4 slightly modified embodiment is shown in FIG. 4, which the flow chart is illustrated in a simplified mer.
  • the system of the intion is provided with a heat exchanger 33 in addil to the preliminary combustor 21.
  • This heat exnger 33 is interposed between the outlet of the pre- .nary combustor 21 and the upstream of the swirler of the main combustor 11 for cooling the partially taminated air through heat transfer. urning now to FIG. 5, the burned gases produced in preliminary combustor 21 is fed back to the air ipressor 16.
  • the contaminated air is partially ulated in the circuit including the preliminary comtor 21 and the air compressor 16, and as such is supd to the main combustor not only through the la 12 as primary air but also through the secondary tertiary air intakes 31 and 32. Therefore, the final t'uel ratio in the preliminary combustor 21 should be ted toward a richer side than the previous two ex- )les.
  • This embodiment may also be provided with heat exchanger 33 for the same purpose as before. .esired, an auxiliary turbine 34 may be provided 'nstream of the preliminary combustor 21 and upam of the heat exchanger 33 for directly extracting tuxiliary output power from the energy contained in burned gases of the preliminary combustor 21. This ossible because the overall combustion in the prenary combustor 21 takes place at a richer side, rely, in the neighbourhood of the stoichiometric dition.
  • a gas turbine engine comprising a combustor ing a swirler and a fuel injector, primary air intakes; :ast one additional air intake, an air compressor for plying air to the combustor through said additional make, a fuel pump for supplying a liquid fuel to the injector, a turbine extracting an output power from energy contained in the combustion products of the ibustor, and a preliminary combustor for feeding :liluted combustion gases to the first-named corn tor, which preliminary combustor includes:
  • rimary air intakes communicating with the air compressor for receiving primary air therefrom; lditional air intakes communicating with the air compressor for receiving therefrom additional air as a diluent;
  • a fuel injector communicating with the fuel pump for receiving a liquid fuel therefrom;
  • a gas turbine engine according to claim 1, wherein the outlet of the preliminary combustor communicates with the primary air intakes of the combustor through the swirler thereof.
  • a gas turbine engine according to claim 2, and further comprising a heat exchanger interposed between the outlet of the preliminary combustor and the primary air intakes of the combustor for cooling the air burned gases through heat transfer before feeding the same to the primary air intakes of the combustor.
  • a gas turbine engine according to claim 1, wherein the outlet of the preliminary combustor communicates with the primary air intakes of the combustor through the air compressor.
  • a gas turbine engine according to claim 4, and further comprising a heat exchanger interposed between the outlet of the preliminary combustor and the air compressor for cooling the air burned gases through heat transfer before feeding the same to the air compressor.
  • a method of minimizing nitrogen oxide content in the exhaust gases of a gas turbine engine by feeding airdiluted combustion gases to the primary air intakes of the combustor of a gas turbine engine comprising:
  • feeding step further comprises the step of cooling said diluted burned gases through a heat transfer before introducing the same into said primary air intakes.
  • said feeding step further comprises the step of:
  • feeding step further comprises the step of cooling said diluted burned gases through a heat transfer before introducing the same into the primary air intakes of both the preliminary combustor and the combustor of the gas turbine engine.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Air Supply (AREA)
  • Supercharger (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
US00203546A 1970-12-22 1971-12-01 System and method used in a gas turbine engine for minimizing nitrogen oxide emission Expired - Lifetime US3792581A (en)

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JP1970129344U JPS4724483Y1 (enrdf_load_stackoverflow) 1970-12-22 1970-12-22

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Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3846979A (en) * 1971-12-17 1974-11-12 Engelhard Min & Chem Two stage combustion process
US3872664A (en) * 1973-10-15 1975-03-25 United Aircraft Corp Swirl combustor with vortex burning and mixing
US3901026A (en) * 1973-11-05 1975-08-26 Gen Motors Corp Gas turbine with auxiliary gasifier engine
US3937008A (en) * 1974-12-18 1976-02-10 United Technologies Corporation Low emission combustion chamber
FR2289738A2 (fr) * 1974-10-30 1976-05-28 Engelhard Min & Chem Procede et appareillage d'obtention d'une combustion entretenue dans une turbine a gaz
US3973390A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones
US3973395A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Low emission combustion chamber
US3998581A (en) * 1974-05-14 1976-12-21 Hotwork International Limited Gaseous fuel burners
US4004413A (en) * 1972-11-28 1977-01-25 Nissan Motor Co., Ltd. Combustible mixture supply system
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
US4045956A (en) * 1974-12-18 1977-09-06 United Technologies Corporation Low emission combustion chamber
US4058977A (en) * 1974-12-18 1977-11-22 United Technologies Corporation Low emission combustion chamber
FR2355162A1 (fr) * 1976-06-14 1978-01-13 Gen Electric Procede pour reduire les emissions nocives des moteurs a turbine a gaz et moteurs ainsi obtenus
US4470261A (en) * 1980-09-29 1984-09-11 Ab Volvo Gas turbine plant for automotive operation
US5038558A (en) * 1988-01-08 1991-08-13 Hitachi, Ltd. Gas turbine combustor and a method of combustion thereby
US5199255A (en) * 1991-04-03 1993-04-06 Nalco Fuel Tech Selective gas-phase nox reduction in gas turbines
US5216876A (en) * 1990-11-05 1993-06-08 Consolidated Natural Gas Service Company, Inc. Method for reducing nitrogen oxide emissions from gas turbines
DE4429757A1 (de) * 1994-08-22 1996-02-29 Abb Management Ag Brennkammer
EP0943868A3 (en) * 1998-03-18 2000-03-22 General Electric Company Gas turbine combustor
WO2005028960A3 (en) * 2003-09-05 2005-06-16 Delavan Inc Pilot combustor for stabilizing combustion in gas turbine engines
US20070234702A1 (en) * 2003-01-22 2007-10-11 Hagen David L Thermodynamic cycles with thermal diluent
DE102009003610A1 (de) 2008-05-15 2009-11-19 General Electric Co. Trockene dreiwege-katalytische Reduktion von Gasturbinen-NOx
US20100180565A1 (en) * 2009-01-16 2010-07-22 General Electric Company Methods for increasing carbon dioxide content in gas turbine exhaust and systems for achieving the same
US20130213050A1 (en) * 2010-09-21 2013-08-22 Miro Turbine Technology BV Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine
US8720179B2 (en) 2011-10-07 2014-05-13 General Electric Company Power plant including an exhaust gas recirculation system for injecting recirculated exhaust gases in the fuel and compressed air of a gas turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5741524A (en) * 1980-08-25 1982-03-08 Hitachi Ltd Combustion method of gas turbine and combustor for gas turbine

Citations (8)

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Publication number Priority date Publication date Assignee Title
US2721444A (en) * 1948-09-21 1955-10-25 Johnson Horace James Series-type multiple ram jet propulsion system
US2773350A (en) * 1950-01-31 1956-12-11 Hillard E Barrett Combustion chamber assembly for ram jet fuel burner
US2901032A (en) * 1954-11-24 1959-08-25 Gen Thermique Procedes Brola S Combustion apparatus
US2913874A (en) * 1955-03-30 1959-11-24 Gen Electric Tailpipe thrust augmentor
US3048014A (en) * 1955-07-07 1962-08-07 Fritz A F Schmidt Combustion chamber for jets and similar engines
US3541790A (en) * 1967-10-05 1970-11-24 Cav Ltd Hot gas generators
US3656298A (en) * 1970-11-27 1972-04-18 Gen Motors Corp Combustion apparatus
US3705492A (en) * 1971-01-11 1972-12-12 Gen Motors Corp Regenerative gas turbine system

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2721444A (en) * 1948-09-21 1955-10-25 Johnson Horace James Series-type multiple ram jet propulsion system
US2773350A (en) * 1950-01-31 1956-12-11 Hillard E Barrett Combustion chamber assembly for ram jet fuel burner
US2901032A (en) * 1954-11-24 1959-08-25 Gen Thermique Procedes Brola S Combustion apparatus
US2913874A (en) * 1955-03-30 1959-11-24 Gen Electric Tailpipe thrust augmentor
US3048014A (en) * 1955-07-07 1962-08-07 Fritz A F Schmidt Combustion chamber for jets and similar engines
US3541790A (en) * 1967-10-05 1970-11-24 Cav Ltd Hot gas generators
US3656298A (en) * 1970-11-27 1972-04-18 Gen Motors Corp Combustion apparatus
US3705492A (en) * 1971-01-11 1972-12-12 Gen Motors Corp Regenerative gas turbine system

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3846979A (en) * 1971-12-17 1974-11-12 Engelhard Min & Chem Two stage combustion process
US4004413A (en) * 1972-11-28 1977-01-25 Nissan Motor Co., Ltd. Combustible mixture supply system
US3872664A (en) * 1973-10-15 1975-03-25 United Aircraft Corp Swirl combustor with vortex burning and mixing
US3901026A (en) * 1973-11-05 1975-08-26 Gen Motors Corp Gas turbine with auxiliary gasifier engine
US3998581A (en) * 1974-05-14 1976-12-21 Hotwork International Limited Gaseous fuel burners
FR2289738A2 (fr) * 1974-10-30 1976-05-28 Engelhard Min & Chem Procede et appareillage d'obtention d'une combustion entretenue dans une turbine a gaz
US3973390A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones
US3973395A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Low emission combustion chamber
FR2295236A1 (fr) * 1974-12-18 1976-07-16 United Technologies Corp Chambre de combustion a faible emission polluante
US3937008A (en) * 1974-12-18 1976-02-10 United Technologies Corporation Low emission combustion chamber
US4045956A (en) * 1974-12-18 1977-09-06 United Technologies Corporation Low emission combustion chamber
US4058977A (en) * 1974-12-18 1977-11-22 United Technologies Corporation Low emission combustion chamber
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
FR2355162A1 (fr) * 1976-06-14 1978-01-13 Gen Electric Procede pour reduire les emissions nocives des moteurs a turbine a gaz et moteurs ainsi obtenus
US4083181A (en) * 1976-06-14 1978-04-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Gas turbine engine with recirculating bleed
US4470261A (en) * 1980-09-29 1984-09-11 Ab Volvo Gas turbine plant for automotive operation
US5038558A (en) * 1988-01-08 1991-08-13 Hitachi, Ltd. Gas turbine combustor and a method of combustion thereby
US5216876A (en) * 1990-11-05 1993-06-08 Consolidated Natural Gas Service Company, Inc. Method for reducing nitrogen oxide emissions from gas turbines
US5199255A (en) * 1991-04-03 1993-04-06 Nalco Fuel Tech Selective gas-phase nox reduction in gas turbines
DE4429757A1 (de) * 1994-08-22 1996-02-29 Abb Management Ag Brennkammer
EP0943868A3 (en) * 1998-03-18 2000-03-22 General Electric Company Gas turbine combustor
US6192689B1 (en) 1998-03-18 2001-02-27 General Electric Company Reduced emissions gas turbine combustor
US20070234702A1 (en) * 2003-01-22 2007-10-11 Hagen David L Thermodynamic cycles with thermal diluent
US8631657B2 (en) * 2003-01-22 2014-01-21 Vast Power Portfolio, Llc Thermodynamic cycles with thermal diluent
RU2406936C2 (ru) * 2003-09-05 2010-12-20 Делэвэн Инк Горелка для камеры сгорания газовой турбины (варианты)
CN100552301C (zh) * 2003-09-05 2009-10-21 德拉文公司 燃气轮机引擎的稳定燃烧用导引燃烧器室
US7621132B2 (en) 2003-09-05 2009-11-24 Delavan Inc. Pilot combustor for stabilizing combustion in gas turbine engines
US20070175219A1 (en) * 2003-09-05 2007-08-02 Michael Cornwell Pilot combustor for stabilizing combustion in gas turbine engines
WO2005028960A3 (en) * 2003-09-05 2005-06-16 Delavan Inc Pilot combustor for stabilizing combustion in gas turbine engines
DE102009003610A1 (de) 2008-05-15 2009-11-19 General Electric Co. Trockene dreiwege-katalytische Reduktion von Gasturbinen-NOx
US20090284013A1 (en) * 2008-05-15 2009-11-19 General Electric Company Dry 3-way catalytic reduction of gas turbine NOx
US8397482B2 (en) 2008-05-15 2013-03-19 General Electric Company Dry 3-way catalytic reduction of gas turbine NOx
US8991149B2 (en) 2008-05-15 2015-03-31 General Electric Company Dry 3-way catalytic reduction of gas turbine NOX
US20100180565A1 (en) * 2009-01-16 2010-07-22 General Electric Company Methods for increasing carbon dioxide content in gas turbine exhaust and systems for achieving the same
US20130213050A1 (en) * 2010-09-21 2013-08-22 Miro Turbine Technology BV Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine
US8720179B2 (en) 2011-10-07 2014-05-13 General Electric Company Power plant including an exhaust gas recirculation system for injecting recirculated exhaust gases in the fuel and compressed air of a gas turbine engine

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Publication number Publication date
JPS4724483Y1 (enrdf_load_stackoverflow) 1972-08-02
GB1376147A (en) 1974-12-04

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