GB1376147A - System and method for minimizing nitrogen oxide emission by a gas turbine engine - Google Patents

System and method for minimizing nitrogen oxide emission by a gas turbine engine

Info

Publication number
GB1376147A
GB1376147A GB5560471A GB5560471A GB1376147A GB 1376147 A GB1376147 A GB 1376147A GB 5560471 A GB5560471 A GB 5560471A GB 5560471 A GB5560471 A GB 5560471A GB 1376147 A GB1376147 A GB 1376147A
Authority
GB
United Kingdom
Prior art keywords
combustion chamber
air
gases
main
supplied
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
Application number
GB5560471A
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.)
Nissan Motor Co Ltd
Original Assignee
Nissan Motor Co Ltd
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 Nissan Motor Co Ltd filed Critical Nissan Motor Co Ltd
Publication of GB1376147A publication Critical patent/GB1376147A/en
Expired legal-status Critical Current

Links

Classifications

    • 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

Landscapes

  • 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)
  • Supercharger (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

1376147 Gas turbine engine combustion equipment NISSAN MOTOR CO Ltd 30 Nov 1971 [22 Dec 1970] 55604/71 Headings F1G and F1L The invention relates to a means of minimizing the nitrogen oxide content in the exhaust gases of a gas turbine engine in which diluted combustion gases from a pre-combustion chamber are supplied to the main combustion chamber. In Fig. 2 diluted combustion gases from a pre-combustion chamber 21 are supplied to the main combustion chamber 11 to which air from compressor 16 is supplied as secondary and tertiary air and to which fuel is supplied through an injector. The resulting combustion gases discharge to the turbine 15. The apparatus shown in Fig. 3 comprises an outer casing within which are disposed a pre-combustion chamber 21 and a main combustion chamber 11, air from the compressor passing through passage 22 and entering the pre-combustion chamber 21 through inlets 23 as primary air and through inlets 24 as secondary and tertiary air. A fuel injector 25 and ignition device 26' are provided and the resulting combustion gases pass through swirl device 12 into the main combustion chamber 11 as primary air. Fuel is supplied to the main chamber 11 through injector 13 and secondary and tertiary air are supplied thereto through inlet openings 31, 32 from the passage 22. In Fig. 4 (not shown) the combustion gases from the precombustion chamber 21 are cooled in a heat exchanger (33) before passing to the main combustion chamber. In Fig. 5 (not shown) the combustion gases from the pre-combustion chamber are passed through an auxiliary turbine and then through a heat exchanger, the cooled gases then passing to the inlet of an air compressor to which ambient air also passes. Air from the compressor passes as primary air and secondary or tertiary air to the pre-combustion chamber also to the main combustion chamber, gases passing from the main combustion chamber to the main turbine.
GB5560471A 1970-12-22 1971-11-30 System and method for minimizing nitrogen oxide emission by a gas turbine engine Expired GB1376147A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP1970129344U JPS4724483Y1 (en) 1970-12-22 1970-12-22

Publications (1)

Publication Number Publication Date
GB1376147A true GB1376147A (en) 1974-12-04

Family

ID=15007274

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5560471A Expired GB1376147A (en) 1970-12-22 1971-11-30 System and method for minimizing nitrogen oxide emission by a gas turbine engine

Country Status (3)

Country Link
US (1) US3792581A (en)
JP (1) JPS4724483Y1 (en)
GB (1) GB1376147A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2488942A1 (en) * 1980-08-25 1982-02-26 Hitachi Ltd COMBUSTION PROCESS AND APPARATUS FOR GAS TURBINE

Families Citing this family (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
GB1454280A (en) * 1972-11-28 1976-11-03 Nissan Motor 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
GB1498034A (en) * 1974-05-14 1978-01-18 Secr Defence Dinghies
FR2289738A2 (en) * 1974-10-30 1976-05-28 Engelhard Min & Chem PROCESS AND APPARATUS FOR OBTAINING SUSTAINED COMBUSTION IN A GAS TURBINE
US3973395A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Low emission combustion chamber
US3937008A (en) * 1974-12-18 1976-02-10 United Technologies Corporation Low emission combustion chamber
US4058977A (en) * 1974-12-18 1977-11-22 United Technologies Corporation Low emission combustion chamber
US3973390A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones
US4045956A (en) * 1974-12-18 1977-09-06 United Technologies Corporation Low emission combustion chamber
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
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
SE423742B (en) * 1980-09-29 1982-05-24 United Motor & Transmissions A GAS TURBLE INSTALLATION FOR AUTOMOTIVE OPERATION
JPH076630B2 (en) * 1988-01-08 1995-01-30 株式会社日立製作所 Gas turbine combustor
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 (en) * 1994-08-22 1996-02-29 Abb Management Ag Two=stage combustion chamber
US6192689B1 (en) * 1998-03-18 2001-02-27 General Electric Company Reduced emissions gas turbine combustor
US8631657B2 (en) * 2003-01-22 2014-01-21 Vast Power Portfolio, Llc Thermodynamic cycles with thermal diluent
CN100552301C (en) * 2003-09-05 2009-10-21 德拉文公司 The smooth combustion pilot combustor of gas turbine engine
US8397482B2 (en) * 2008-05-15 2013-03-19 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
NL2005381C2 (en) * 2010-09-21 2012-03-28 Micro Turbine Technology B V 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

Family Cites Families (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
NL98183C (en) * 1954-11-24
US2913874A (en) * 1955-03-30 1959-11-24 Gen Electric Tailpipe thrust augmentor
DE1074920B (en) * 1955-07-07 1960-02-04 Ing habil Fritz A F Schmidt Murnau Dr (Obb) Method and device for regulating gas turbine combustion chambers with subdivided combustion and several pressure levels
GB1225759A (en) * 1967-10-05 1971-03-24
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 (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2488942A1 (en) * 1980-08-25 1982-02-26 Hitachi Ltd COMBUSTION PROCESS AND APPARATUS FOR GAS TURBINE

Also Published As

Publication number Publication date
JPS4724483Y1 (en) 1972-08-02
US3792581A (en) 1974-02-19

Similar Documents

Publication Publication Date Title
GB1376147A (en) System and method for minimizing nitrogen oxide emission by a gas turbine engine
US5178119A (en) Combustion process and fuel supply system for engines
US4206593A (en) Gas turbine
US4004413A (en) Combustible mixture supply system
GB1335134A (en) Combustion apparatus of a gas turbine engine
US3588298A (en) Detonation wave combustion
JPS55156243A (en) Cylinder fuel injection engine
GB1009978A (en) Installation for supplying gas to a blast furnace or the like
GB1023752A (en) Improvements in or relating to an oscillating gas column combustion apparatus
GB1457152A (en) Internal combustion engine
ES413299A1 (en) Combustion chambers for internal combustion engines equipped with a turbo-compressor unit with reheating upstream of the turbine
US3908618A (en) Torch-ignition reciprocating-piston type internal combustion engine
GB1512445A (en) Intake and exhaust apparatus for precombustion chamber internal combustion engines
GB992304A (en) Apparatus for supplying air to a blast furnace
US2298214A (en) Coolant-fuel mechanism and method
US3999530A (en) Internal combustion spark ignition engine
US3444686A (en) Gas turbine smog control for internal combustion engine
GB1354333A (en) Regenerative gas turbine engines
GB1522873A (en) Method of operating spark ignition internal combustion engine and an engine carrying out the method
GB1437867A (en)
GB1520178A (en) Multi-cylinder internal combustion engine with exhaust cleaning apparatus
GB1525185A (en) Spark ignition internal combustion engine
GB1044339A (en) Improvements in or relating to heat engine combustion systems
GB1339227A (en) Heat engines
GB104734A (en) Improvements in the Process for the Production of Nitric Oxide in Internal Combustion Engines.

Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
746 Register noted 'licences of right' (sect. 46/1977)