WO1993017279A1 - Premix gas nozzle - Google Patents

Premix gas nozzle Download PDF

Info

Publication number
WO1993017279A1
WO1993017279A1 PCT/US1992/010269 US9210269W WO9317279A1 WO 1993017279 A1 WO1993017279 A1 WO 1993017279A1 US 9210269 W US9210269 W US 9210269W WO 9317279 A1 WO9317279 A1 WO 9317279A1
Authority
WO
WIPO (PCT)
Prior art keywords
chamber
gas
gas flow
pilot
conical body
Prior art date
Application number
PCT/US1992/010269
Other languages
French (fr)
Inventor
Aaron S. Hu
Original Assignee
United Technologies Corporation
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 Corporation filed Critical United Technologies Corporation
Priority to EP93900709A priority Critical patent/EP0627062B1/en
Priority to JP51480593A priority patent/JP3180138B2/en
Priority to DE69220091T priority patent/DE69220091T2/en
Publication of WO1993017279A1 publication Critical patent/WO1993017279A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/30—Injector mixers
    • B01F25/31—Injector mixers in conduits or tubes through which the main component flows
    • B01F25/313—Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit
    • B01F25/3131—Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit with additional mixing means other than injector mixers, e.g. screens, baffles or rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the invention relates to fuel nozzles for low NOx 5 combustion and in particular to the stabilization thereof.
  • Gas and air are mixed at a tangential entrance 30 through longitudinal slots in a cylindrical chamber.
  • a center cone provides an increasing axial flow area toward the chamber outlet.
  • the gas swirl within the chamber completes the air and gas mixing. Additional gas is supplied as pilot fuel on the central axis of the chamber near the outlet.
  • This pilot fuel remains in the core. As it leaves the chamber it is met with high temperature recirculating products from the flame. These products are primarily hot air because of the high localized air/fuel ratio. Local self ignition maintains the flame stability. It has also been found to increase the combustion efficiency.
  • pilot fuel is maintained constant, or at least reduced less than the main fuel. This increase in local combustion is acceptable without increasing NOx since the air temperature itself is decreasing at these low loads.
  • Figure 1 is a schematic of a gas turbine engine and combustor
  • Figure 2 is a sectional side view of the burner;
  • Figure 3 is a sectional axial view of the burner;
  • Figure 4 is a sectional axial view taken at 90° from Figure 3;
  • Figure 5 is a sectional axial view of an alternate burner embodiment.
  • FIG. 1 schematic illustrates a gas turbine engine with compressor 10 supplying compressed air to combustor 12.
  • Gas which is fueled through gas supply line 14 provides fuel for combustion within the combustor with the gaseous products passing through turbine 16.
  • combustor 12 is surrounded by combustor liner 18 and has in the upstream face 20 a plurality of circumferentially spaced burners 22.
  • the structure is sized such that of the incoming airflow 24 from the compressor 35 percent of this flow passes as dilution air 26 around a burner with the majority of this passing as cooling air 28 through the combustion liner. 65 percent of this airflow passes as combustion supporting air 30 through the burner.
  • From the fuel header 14 the main gas flow is supplied through line 32 and controlled by valve 34.
  • a pilot flow of gas passes through pilot line 36 being controllable by valve 38.
  • burner 22 is comprised of a substantially cylindrical axially extending chamber 40.
  • Two longitudinally extending slots 42 are located with the walls tangent to the inner wall of the cylindrical chamber. Combustion supporting airflow 30 passes through these slots establishing a whirling action in chamber 40.
  • the main gas flow line 32 is divided to supply two gas distribution manifolds 44 located adjacent the air inlet slot 42.
  • a plurality of holes 46 are located along the length of manifold 44. These distributively inject gas as a plurality of streams 48 into the airflow passing into the slot. The gas and air continue mixing as the mixture swirls through chamber 40.
  • the substantially cylindrically chamber 40 is formed by two semi-cylindrical walls 58 each having its axis offset from one another to form the slots 42.
  • a gas pilot tube 60 passes through the center of the cone with pilot discharge openings 62 at or adjacent the apex 52 of the cone. This location should be within 25 percent of the length of the chamber 40 from the outlet 54 of the chamber.
  • the objective is to introduce the additional gas flow centrally of the swirling air/gas mixture, but not to mix it in with the air/gas mixture. This is aided by the fact that the incoming gas is lighter than the air or air/gas mixture.
  • pilot openings 62 In full load operation of the gas turbine engine, between 4 and 6 percent of the total gas flow may be supplied through the pilot openings 62 without increasing the NOx. In most cases the pilot is not needed for stability at the high load. The flow, however, cools the nozzle, and avoids operational complexity of turning the pilot on when load is reduced. Pilot operation is therefore preferred, though not required at full load.
  • the overall airflow drops less rapidly than the gas flow. Since the relationship of the airflow between the combustion air and the dilution air is set by the physical design of the structure, it remains constant. The mixture in the combustion zone therefore becomes increasingly lean.
  • the preferred operation is to decrease load by closing down on valve 34 while leaving valve 38 open. This increases the proportion of fuel introduced through the pilot. At this same time, however, the air temperature from the compressor decreases. The additional temperature because of the higher concentration of pilot fuel is acceptable without increasing NOx because of this overall temperature decrease.
  • valve 38 is preferred rather than to maintain it in a fixed position. It nonetheless should produce an increasing percentage of the fuel through the pilot during load decrease.
  • Figure 5 illustrates a section through an alternate nozzle embodiment showing chamber 40 and cone

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)

Abstract

A premix gas nozzle has longitudinal tangential entrance slots (42) to a cylindrical chamber (40). There is an axially increasing flow area (56) toward the chamber outlet (54), with pilot fuel (60, 62) centrally introduced near the outlet. A lean mix low NOx fuel nozzle is thereby stabilized.

Description

Description
Premix Gas Nozzle
""
Technical Field
The invention relates to fuel nozzles for low NOx 5 combustion and in particular to the stabilization thereof.
Background of the Invention
Combustion at high temperature leads to the formation of NOx, or oxides of nitrogen, because of the
10 combination of oxygen with nitrogen at high temperature. This is a notorious pollutant and much effort is being put forth to reduce the formation of NOx.
One solution has been to premix the fuel with
15 excess air whereby all of the combustion occurs with a local high excess air and therefore at a relatively low temperature. Such combustion, however, can lead to instability and incomplete combustion.
This problem is exacerbated in gas turbine
20 engines. Once the proper lean mix is set for proper full load operation, low load operation must be considered. At decreasing loads the airflow decreases less than the fuel flow, leading to even leaner mixtures. The air temperature also decreases.
25 Accordingly, flame stability and combustion efficiency (percentage of fuel burnt) becomes an increasing problem.
Summary of the Invention
Gas and air are mixed at a tangential entrance 30 through longitudinal slots in a cylindrical chamber. A center cone provides an increasing axial flow area toward the chamber outlet.
The gas swirl within the chamber completes the air and gas mixing. Additional gas is supplied as pilot fuel on the central axis of the chamber near the outlet.
This pilot fuel remains in the core. As it leaves the chamber it is met with high temperature recirculating products from the flame. These products are primarily hot air because of the high localized air/fuel ratio. Local self ignition maintains the flame stability. It has also been found to increase the combustion efficiency.
As load is decreased pilot fuel is maintained constant, or at least reduced less than the main fuel. This increase in local combustion is acceptable without increasing NOx since the air temperature itself is decreasing at these low loads.
Brief Description of the Drawings
Figure 1 is a schematic of a gas turbine engine and combustor;
Figure 2 is a sectional side view of the burner; Figure 3 is a sectional axial view of the burner; Figure 4 is a sectional axial view taken at 90° from Figure 3; and
Figure 5 is a sectional axial view of an alternate burner embodiment.
Description of the Preferred Embodiment
The Figure 1 schematic illustrates a gas turbine engine with compressor 10 supplying compressed air to combustor 12. Gas which is fueled through gas supply line 14 provides fuel for combustion within the combustor with the gaseous products passing through turbine 16. Referring to Figure 2, combustor 12 is surrounded by combustor liner 18 and has in the upstream face 20 a plurality of circumferentially spaced burners 22. The structure is sized such that of the incoming airflow 24 from the compressor 35 percent of this flow passes as dilution air 26 around a burner with the majority of this passing as cooling air 28 through the combustion liner. 65 percent of this airflow passes as combustion supporting air 30 through the burner. From the fuel header 14 the main gas flow is supplied through line 32 and controlled by valve 34. A pilot flow of gas passes through pilot line 36 being controllable by valve 38.
Referring to Figures 3 and 4, burner 22 is comprised of a substantially cylindrical axially extending chamber 40. Two longitudinally extending slots 42 are located with the walls tangent to the inner wall of the cylindrical chamber. Combustion supporting airflow 30 passes through these slots establishing a whirling action in chamber 40. The main gas flow line 32 is divided to supply two gas distribution manifolds 44 located adjacent the air inlet slot 42. A plurality of holes 46 are located along the length of manifold 44. These distributively inject gas as a plurality of streams 48 into the airflow passing into the slot. The gas and air continue mixing as the mixture swirls through chamber 40.
Centrally located within the chamber 40 is a cone 50 with its base toward the upstream end of the chamber and its apex 52 toward the outlet 54 end of the chamber. Resulting flow area 56 therefore increases toward the outlet of the chamber so that the mixture of air and gas passing axially along the chamber maintains a somewhat constant velocity. This deters flashback from the flame into the upstream end of the chamber. The substantially cylindrically chamber 40 is formed by two semi-cylindrical walls 58 each having its axis offset from one another to form the slots 42.
A gas pilot tube 60 passes through the center of the cone with pilot discharge openings 62 at or adjacent the apex 52 of the cone. This location should be within 25 percent of the length of the chamber 40 from the outlet 54 of the chamber. The objective is to introduce the additional gas flow centrally of the swirling air/gas mixture, but not to mix it in with the air/gas mixture. This is aided by the fact that the incoming gas is lighter than the air or air/gas mixture.
In full load operation of the gas turbine engine, between 4 and 6 percent of the total gas flow may be supplied through the pilot openings 62 without increasing the NOx. In most cases the pilot is not needed for stability at the high load. The flow, however, cools the nozzle, and avoids operational complexity of turning the pilot on when load is reduced. Pilot operation is therefore preferred, though not required at full load.
As load is reduced on the gas turbine engine, the overall airflow drops less rapidly than the gas flow. Since the relationship of the airflow between the combustion air and the dilution air is set by the physical design of the structure, it remains constant. The mixture in the combustion zone therefore becomes increasingly lean. The preferred operation is to decrease load by closing down on valve 34 while leaving valve 38 open. This increases the proportion of fuel introduced through the pilot. At this same time, however, the air temperature from the compressor decreases. The additional temperature because of the higher concentration of pilot fuel is acceptable without increasing NOx because of this overall temperature decrease.
It is understood that during test operation it may be found that some other manipulation of valve 38 is preferred rather than to maintain it in a fixed position. It nonetheless should produce an increasing percentage of the fuel through the pilot during load decrease.
Figure 5 illustrates a section through an alternate nozzle embodiment showing chamber 40 and cone
50. Three inlet slots 72 are provided for the air inlet while the main gas flow passes through gas manifolds 74 and ejecting through holes 76 into slot
72. Flame stability is achieved without NOx increase at reduced loads.

Claims

Claims
1. A low NOx burner for a gas turbine engine, comprising: a substantially cylindrical burner chamber having an axially extending chamber wall, and having an upstream end and an outlet end; at least one longitudinally extending slot in the wall of said cylindrical chamber having a slot wall tangential to said chamber wall; supply means for supplying air through said slot; a gas distribution manifold located adjacent said slot and having a plurality of axially space openings for delivering gas into the airflow as it passes into said slot; a conical body located in said chamber on the axis of said chamber with the base of said conical body at the upstream end of said chamber and the apex of said conical body toward the outlet end of said chamber; and a gas pilot tube having a discharge opening through said conical body at the apex end.
2. A burner as in claim 1 comprising also: said substantially cylindrical chamber formed of a plurality of partial cylinders having the axis of each cylinder offset from the axis of the others, whereby said slot is formed between the walls of adjoining partial cylinders.
3. A burner as in claim 2 comprising also: the number of partial cylinders being two.
4. A burner as in claim 1 comprising also: said gas pilot tube having a plurality of circumferentially spaced discharge openings around the periphery of said conical body at or slightly upstream of the apex of said conical body.
5. A burner as in claim 1 comprising also: said discharge opening through said conical body being located within 25 percent of the axial length of said chamber from the outlet of said chamber.
6. A burner as in claim 3 comprising also: said gas pilot tube having a plurality of circumferentially spaced discharge openings around the periphery of said conical body at or slightly upstream of the apex of said conical body.
7. A burner as in claim 4 comprising also: said discharge opening through said conical body being located within 25 percent of the axial length of said chamber from the outlet of said chamber.
8. A burner as in claim 6 comprising also: said discharge opening through said conical body being located within 25 percent of the axial length of said chamber from the outlet of said chamber.
9. A method of burning gas in the combustor of a gas turbine engine with a premixing type of combustion, comprising: tangentially introducing combustion air into a substantially cylindrical chamber having increased axial flow area toward an outlet end of said substantially cylindrical chamber; distributively injecting a main gas flow into said combustion air at the entrance to said substantially cylindrical chamber; burning said main gas flow at the outlet of said substantially cylindrical chamber; and introducing a pilot gas flow into said gas chamber at the central axes of said chamber.
10. The method of claim 9 including also: introducing said pilot gas flow at a location within 25 percent of the axial length of said chamber from the outlet of said chamber.
11. The method of claim 9 comprising also: at maximum output of said gas turbine engine introducing as pilot gas flow between 4 and 6 percent of the total of said pilot gas flow and said main gas flow; and increasing the percentage of said pilot gas flow as a percentage of the total flow at outputs below said maximum amount.
12. The method of claim 10 comprising also: at maximum output of said gas turbine engine introducing as pilot gas flow between 4 and 6 percent of the total of said pilot gas flow and said main gas flow; and increasing the percentage of said pilot gas flow as a percentage of the total flow at outputs below said maximum amount.
PCT/US1992/010269 1992-02-26 1992-11-20 Premix gas nozzle WO1993017279A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP93900709A EP0627062B1 (en) 1992-02-26 1992-11-20 Premix gas nozzle
JP51480593A JP3180138B2 (en) 1992-02-26 1992-11-20 Premixed gas nozzle
DE69220091T DE69220091T2 (en) 1992-02-26 1992-11-20 PRE-MIXING GAS NOZZLE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US841,942 1992-02-26
US07/841,942 US5307634A (en) 1992-02-26 1992-02-26 Premix gas nozzle

Publications (1)

Publication Number Publication Date
WO1993017279A1 true WO1993017279A1 (en) 1993-09-02

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1992/010269 WO1993017279A1 (en) 1992-02-26 1992-11-20 Premix gas nozzle

Country Status (5)

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US (2) US5307634A (en)
EP (1) EP0627062B1 (en)
JP (1) JP3180138B2 (en)
DE (1) DE69220091T2 (en)
WO (1) WO1993017279A1 (en)

Cited By (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0641971A2 (en) * 1993-09-06 1995-03-08 Abb Research Ltd. Method for operating a premix burner
WO1995023316A1 (en) * 1994-02-24 1995-08-31 United Technologies Corporation Tangential entry fuel nozzle
DE4435473A1 (en) * 1994-10-04 1996-04-11 Abb Management Ag Flame stabilised, premix burner for liq. fuel
DE4446945A1 (en) * 1994-12-28 1996-07-04 Abb Management Ag Gas powered premix burner
DE19527088A1 (en) * 1995-07-25 1997-01-30 Viessmann Werke Kg Oil vapor burner
EP0777081A2 (en) 1995-12-02 1997-06-04 Abb Research Ltd. Premix burner
DE19545310A1 (en) * 1995-12-05 1997-06-12 Asea Brown Boveri Pre-mixing burner for mixing fuel and combustion air before ignition
EP0786626A1 (en) * 1995-12-27 1997-07-30 Asea Brown Boveri Ag Premixing burner
EP0833105A2 (en) 1996-09-30 1998-04-01 Abb Research Ltd. Premix burner
EP0778445A3 (en) * 1995-12-05 1999-04-28 Asea Brown Boveri Ag Premix burner
EP0916894A1 (en) * 1997-11-13 1999-05-19 Abb Research Ltd. Burner for operating a heat generator
EP0881432A3 (en) * 1997-05-26 1999-06-16 Abb Research Ltd. Burner for operating a hot gas generating unit
EP1065346A1 (en) 1999-07-02 2001-01-03 Asea Brown Boveri AG Gas-turbine engine combustor
EP1070914A1 (en) 1999-07-22 2001-01-24 ABB Alstom Power (Schweiz) AG Premix burner
EP1070915A1 (en) 1999-07-22 2001-01-24 Asea Brown Boveri AG Premix burner
DE10029607A1 (en) * 2000-06-15 2001-12-20 Alstom Power Nv Method to operate burner; involves operating burner with two groups of fuel outlets to supply different amounts of same fuel, where outlet groups are supplied independently and controlled separately
WO2001096785A1 (en) * 2000-06-15 2001-12-20 Alstom (Switzerland) Ltd Method for operating a burner and burner with stepped premix gas injection
WO2002033324A1 (en) 2000-10-16 2002-04-25 Alstom (Switzerland) Ltd. Burner with progressive fuel injection
EP1279898A2 (en) 2001-07-26 2003-01-29 ALSTOM (Switzerland) Ltd Premix burner with high flame stability
US6558154B2 (en) 2000-11-13 2003-05-06 Alstom (Switzerland) Ltd Burner system with staged fuel injection and method for its operation
DE10160907A1 (en) * 2001-12-12 2003-08-14 Alstom Switzerland Ltd Operation method for burner with swirl cup, especially in gas turbines, involves adapting velocity of fuel to supply to velocity of combustion air
US6640545B2 (en) 2000-12-22 2003-11-04 Alstom Ltd. Burner with high flame stability
US6679060B2 (en) 2000-12-16 2004-01-20 Alstom Technology Ltd Method for operating a premix burner
US6901760B2 (en) 2000-10-11 2005-06-07 Alstom Technology Ltd Process for operation of a burner with controlled axial central air mass flow
US6969251B2 (en) 2002-10-12 2005-11-29 Alstom Technology Ltd Burner
US7003960B2 (en) 2000-10-05 2006-02-28 Alstom Technology Ltd Method and appliance for supplying fuel to a premixing burner
US7003957B2 (en) 2001-10-19 2006-02-28 Alstom Technology Ltd Burner for synthesis gas
US7013648B2 (en) 2002-05-16 2006-03-21 Alstom Technology Ltd. Premix burner
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
US7424804B2 (en) 2003-03-07 2008-09-16 Alstom Technology Ltd Premix burner
EP2058590A1 (en) 2007-11-09 2009-05-13 ALSTOM Technology Ltd Method for operating a burner
WO2009068424A1 (en) 2007-11-27 2009-06-04 Alstom Technology Ltd Method and device for burning hydrogen in a premix burner
US7584616B2 (en) 2004-12-23 2009-09-08 Alstom Technology Ltd Method for the operation of a gas turbo group
US7610761B2 (en) 2005-03-23 2009-11-03 Alstom Technology Ltd. Method and device for the combustion of hydrogen in a premix burner
US7871262B2 (en) 2004-11-30 2011-01-18 Alstom Technology Ltd. Method and device for burning hydrogen in a premix burner
WO2011032935A2 (en) 2009-09-17 2011-03-24 Alstom Technology Ltd. Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method
US8033821B2 (en) 2007-11-27 2011-10-11 Alstom Technology Ltd. Premix burner for a gas turbine
US9062886B2 (en) 2010-01-26 2015-06-23 Alstom Technology Ltd. Sequential combustor gas turbine including a plurality of gaseous fuel injection nozzles and method for operating the same
EP3077722A4 (en) * 2013-12-04 2017-08-30 King Abdullah University Of Science And Technology Apparatuses and methods for combustion
EP3228937A1 (en) 2016-04-08 2017-10-11 Ansaldo Energia Switzerland AG Method for combusting a fuel, and combustion device
EP3228939A1 (en) 2016-04-08 2017-10-11 Ansaldo Energia Switzerland AG Method for combusting a fuel, and combustion appliance
EP3306194A1 (en) 2016-10-06 2018-04-11 Ansaldo Energia IP UK Limited Combustor wall element and method for manufacturing the same

Families Citing this family (57)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5450724A (en) * 1993-08-27 1995-09-19 Northern Research & Engineering Corporation Gas turbine apparatus including fuel and air mixer
US5564271A (en) * 1994-06-24 1996-10-15 United Technologies Corporation Pressure vessel fuel nozzle support for an industrial gas turbine engine
DE4435266A1 (en) * 1994-10-01 1996-04-04 Abb Management Ag burner
US5479773A (en) * 1994-10-13 1996-01-02 United Technologies Corporation Tangential air entry fuel nozzle
DE4440558A1 (en) * 1994-11-12 1996-05-15 Abb Research Ltd Premix burner
US5671597A (en) * 1994-12-22 1997-09-30 United Technologies Corporation Low nox fuel nozzle assembly
DE19502796B4 (en) * 1995-01-30 2004-10-28 Alstom burner
DE19515082B4 (en) * 1995-04-25 2005-02-03 Alstom premix
DE19619873A1 (en) * 1996-05-17 1997-11-20 Abb Research Ltd burner
DE19626240A1 (en) * 1996-06-29 1998-01-02 Abb Research Ltd Premix burner and method of operating the burner
EP0849528A3 (en) 1996-12-20 1999-06-02 United Technologies Corporation Two stream tangential entry nozzle
EP0849530A3 (en) 1996-12-20 1999-06-09 United Technologies Corporation Fuel nozzles and centerbodies therefor
US5899076A (en) * 1996-12-20 1999-05-04 United Technologies Corporation Flame disgorging two stream tangential entry nozzle
US5761897A (en) 1996-12-20 1998-06-09 United Technologies Corporation Method of combustion with a two stream tangential entry nozzle
EP0849529B1 (en) 1996-12-20 2004-03-03 United Technologies Corporation Tangential entry fuel nozzle
US5865609A (en) 1996-12-20 1999-02-02 United Technologies Corporation Method of combustion with low acoustics
US5896739A (en) * 1996-12-20 1999-04-27 United Technologies Corporation Method of disgorging flames from a two stream tangential entry nozzle
US5791562A (en) * 1996-12-20 1998-08-11 United Technologies Corporation Conical centerbody for a two stream tangential entry nozzle
US5971026A (en) * 1997-12-09 1999-10-26 Honeywell Inc. Internal geometry shape design for venturi tube-like gas-air mixing valve
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
US6178752B1 (en) 1998-03-24 2001-01-30 United Technologies Corporation Durability flame stabilizing fuel injector with impingement and transpiration cooled tip
US6141954A (en) 1998-05-18 2000-11-07 United Technologies Corporation Premixing fuel injector with improved flame disgorgement capacity
DE10049203A1 (en) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Process for introducing fuel into a premix burner
GB2368386A (en) * 2000-10-23 2002-05-01 Alstom Power Nv Gas turbine engine combustion system
US6360776B1 (en) 2000-11-01 2002-03-26 Rolls-Royce Corporation Apparatus for premixing in a gas turbine engine
US6539721B2 (en) 2001-07-10 2003-04-01 Pratt & Whitney Canada Corp. Gas-liquid premixer
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US6820424B2 (en) 2001-09-12 2004-11-23 Allison Advanced Development Company Combustor module
JP3940705B2 (en) * 2003-06-19 2007-07-04 株式会社日立製作所 Gas turbine combustor and fuel supply method thereof
WO2006094922A1 (en) * 2005-03-09 2006-09-14 Alstom Technology Ltd Premix burner for producing an ignitable fuel/air mixture
DE102005015152A1 (en) * 2005-03-31 2006-10-05 Alstom Technology Ltd. Premix burner for a gas turbine combustor
US20070204624A1 (en) * 2006-03-01 2007-09-06 Smith Kenneth O Fuel injector for a turbine engine
EP1999409B1 (en) * 2006-03-30 2018-05-02 Ansaldo Energia IP UK Limited Burner arrangement
US7870736B2 (en) * 2006-06-01 2011-01-18 Virginia Tech Intellectual Properties, Inc. Premixing injector for gas turbine engines
US8413446B2 (en) * 2008-12-10 2013-04-09 Caterpillar Inc. Fuel injector arrangement having porous premixing chamber
US9134023B2 (en) 2012-01-06 2015-09-15 General Electric Company Combustor and method for distributing fuel in the combustor
US9416973B2 (en) 2013-01-07 2016-08-16 General Electric Company Micromixer assembly for a turbine system and method of distributing an air-fuel mixture to a combustor chamber
EP3084307B1 (en) 2013-12-19 2018-10-24 United Technologies Corporation Dilution passage arrangement for gas turbine engine combustor
US9689571B2 (en) * 2014-01-15 2017-06-27 Delavan Inc. Offset stem fuel distributor
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Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0310327A2 (en) * 1987-09-28 1989-04-05 Exxon Research And Engineering Company Method of operating a staged-air vortex burner
EP0433790B1 (en) * 1989-12-22 1995-03-08 Asea Brown Boveri Ag Burner

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4292801A (en) * 1979-07-11 1981-10-06 General Electric Company Dual stage-dual mode low nox combustor
GB2073399B (en) * 1980-04-02 1983-11-02 United Technologies Corp Dual premix tube fuel nozzle
JPS6057131A (en) * 1983-09-08 1985-04-02 Hitachi Ltd Fuel feeding process for gas turbine combustor
EP0210462B1 (en) * 1985-07-30 1989-03-15 BBC Brown Boveri AG Dual combustor
US4653278A (en) * 1985-08-23 1987-03-31 General Electric Company Gas turbine engine carburetor
JP2644745B2 (en) * 1987-03-06 1997-08-25 株式会社日立製作所 Gas turbine combustor
CH674561A5 (en) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
CH678757A5 (en) * 1989-03-15 1991-10-31 Asea Brown Boveri
US4977740A (en) * 1989-06-07 1990-12-18 United Technologies Corporation Dual fuel injector

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0310327A2 (en) * 1987-09-28 1989-04-05 Exxon Research And Engineering Company Method of operating a staged-air vortex burner
EP0433790B1 (en) * 1989-12-22 1995-03-08 Asea Brown Boveri Ag Burner

Cited By (63)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0641971A3 (en) * 1993-09-06 1995-08-16 Abb Research Ltd Method for operating a premix burner.
EP0641971A2 (en) * 1993-09-06 1995-03-08 Abb Research Ltd. Method for operating a premix burner
WO1995023316A1 (en) * 1994-02-24 1995-08-31 United Technologies Corporation Tangential entry fuel nozzle
DE4435473A1 (en) * 1994-10-04 1996-04-11 Abb Management Ag Flame stabilised, premix burner for liq. fuel
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US5699667A (en) * 1994-12-28 1997-12-23 Asea Brown Boveri Ag Gas-operated premixing burner for gas turbine
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US5791894A (en) * 1995-12-02 1998-08-11 Abb Research Ltd. Premix burner
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EP0786626A1 (en) * 1995-12-27 1997-07-30 Asea Brown Boveri Ag Premixing burner
EP0833105A2 (en) 1996-09-30 1998-04-01 Abb Research Ltd. Premix burner
US6126439A (en) * 1996-09-30 2000-10-03 Abb Alstom Power (Switzerland) Ltd Premix burner
EP0833105A3 (en) * 1996-09-30 1998-10-21 Abb Research Ltd. Premix burner
EP0881432A3 (en) * 1997-05-26 1999-06-16 Abb Research Ltd. Burner for operating a hot gas generating unit
US6027331A (en) * 1997-11-13 2000-02-22 Abb Research Ltd. Burner for operating a heat generator
EP0916894A1 (en) * 1997-11-13 1999-05-19 Abb Research Ltd. Burner for operating a heat generator
EP1065346A1 (en) 1999-07-02 2001-01-03 Asea Brown Boveri AG Gas-turbine engine combustor
US6331109B1 (en) 1999-07-22 2001-12-18 Alstom (Switzerland) Ltd. Premix burner
EP1070915A1 (en) 1999-07-22 2001-01-24 Asea Brown Boveri AG Premix burner
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DE10029607A1 (en) * 2000-06-15 2001-12-20 Alstom Power Nv Method to operate burner; involves operating burner with two groups of fuel outlets to supply different amounts of same fuel, where outlet groups are supplied independently and controlled separately
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US6769903B2 (en) 2000-06-15 2004-08-03 Alstom Technology Ltd Method for operating a burner and burner with stepped premix gas injection
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US6901760B2 (en) 2000-10-11 2005-06-07 Alstom Technology Ltd Process for operation of a burner with controlled axial central air mass flow
WO2002033324A1 (en) 2000-10-16 2002-04-25 Alstom (Switzerland) Ltd. Burner with progressive fuel injection
US7189073B2 (en) 2000-10-16 2007-03-13 Alstom Technology Ltd. Burner with staged fuel injection
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Also Published As

Publication number Publication date
DE69220091T2 (en) 1998-01-02
US5307634A (en) 1994-05-03
EP0627062B1 (en) 1997-05-28
US5402633A (en) 1995-04-04
EP0627062A1 (en) 1994-12-07
JP3180138B2 (en) 2001-06-25
JPH07504265A (en) 1995-05-11
DE69220091D1 (en) 1997-07-03

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