WO2001027534A1 - Chambre de combustion et procede de combustion de carburant - Google Patents

Chambre de combustion et procede de combustion de carburant Download PDF

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Publication number
WO2001027534A1
WO2001027534A1 PCT/US2000/026252 US0026252W WO0127534A1 WO 2001027534 A1 WO2001027534 A1 WO 2001027534A1 US 0026252 W US0026252 W US 0026252W WO 0127534 A1 WO0127534 A1 WO 0127534A1
Authority
WO
WIPO (PCT)
Prior art keywords
combustor
fuel
annular
mixing space
supply channels
Prior art date
Application number
PCT/US2000/026252
Other languages
English (en)
Inventor
Anatoly Rakhmailov
Original Assignee
Alm Development, Inc.
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 Alm Development, Inc. filed Critical Alm Development, Inc.
Priority to AU79856/00A priority Critical patent/AU7985600A/en
Publication of WO2001027534A1 publication Critical patent/WO2001027534A1/fr

Links

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
    • F23R3/28—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
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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 
    • F23C2202/00—Fluegas recirculation
    • F23C2202/20—Premixing fluegas with fuel

Definitions

  • the invention relates to combustors to be used in gas turbine engines and, more specifically, combustors in gas turbine engines having combustion products containing chemically bound oxygen in their flow ducts.
  • Prior art combustors may take various configurations.
  • One type of prior art combustor has an annular interior space which has circular walls defining the annular interior space, a combustion area in the annular interior space, and a pre-mixing space in the annular interior space.
  • the pre-mixing space has an entry zone and an outlet zone.
  • the pre-mixing space is separated from the combustion area by an annular partition wall.
  • Fuel and air for combustion (“combustion air”) are fed to the pre-mixing space.
  • Combustion air enters the pre- mixing space at the outlet zone of the pre-mixing space, and fuel is supplied to the pre-mixing space at a location proximate to the outlet zone location where the combustion air enters the pre- mixing space.
  • a gas containing chemically bound oxygen is fed to the pre-mixing space in the entry zone of the pre-mixing space.
  • This gas makes up the combustion products (“combustion gas”) that are available in the gas turbine engine flow duct.
  • combustion gas combustion products
  • This prior art combustor has a pre-mixing space in which a mixture of fuel and combustion air is prepared for entering the combustion area of the combustor, where the mixture is ignited.
  • the mixture of fuel and combustion air is supplied to the combustion area through a pre-mixing space outlet zone with the help of the combustion gas that is fed to the pre-mixing space in the pre-mixing space entry zone.
  • the fuel enters the pre-mixing space, it mixes with combustion gas and air. Both the fuel and the combustion gas have high enough temperatures for chemical reactions to occur before the fuel and combustion gas mixture and the combustion air meet.
  • the fuel which enters the pre-mixing space is normally supplied in vapor form.
  • This reaction is an endothermic reaction, and the heat removal from the burning fuel and air mixture from this reaction destabilizes combustion and may cause flame blowoff.
  • the combustion temperature in prior art combustors is increased by raising the quantity of fuel supplied to the combustion area. This is not desirable because the level of NOx emissions increase, and the combustor becomes more expensive to operate.
  • the disorderly mixing of the fuel with the ballast gas and the short residence time result in an incomplete reduction reaction and unstable combustion in certain load ranges in the prior art combustor described here. This incomplete reaction impairs the temperature distribution in the combustion area and increases emission levels, especially NOx level.
  • Another object of the invention is to provide a combustor which would enhance combustion stability.
  • It is also an object of the invention is to provide a combustor which would achieve more uniform and complete fuel combustion.
  • a method for burning fuel that comprises supplying fuel to a combustor pre-mixing space entry zone, and supplying a gas to the entry zone of the pre-mixing space to form a fuel and gas mixture.
  • This gas contains chemically bound oxygen and has flow parameters that assure gas movement through the pre- mixing space to a pre-mixing space outlet.
  • the fuel and gas mixture is then heated to a temperature of 650°C to 1300°C while it moves through the pre-mixing space, and combustion air is supplied to the pre-mixing space outlet zone for mixing the combustion air with the fuel and gas mixture to form the fuel and air mixture for combustion in the combustion area.
  • the combustor in this embodiment has an annular interior space with a combustion area in the annular interior space and a pre-mixing space that has an entry zone and an outlet zone and that is separated from the combustion area by an annular partition wall.
  • a fuel admission opening is located at the pre-mixing space entry zone, and fluid supply ports establish communication between the pre-mixing space and an air source.
  • the fluid supply ports are located at the pre-mixing space outlet zone.
  • An annular gas supply supplies a gas containing chemically bound oxygen. This annular gas supply passage has an outlet located adjacent to the fuel admission opening.
  • Figure 1 is a schematic representation of a combustor according to the invention in a longitudinal section view
  • FIG 2 is an enlarged detail of the combustor shown in Figure 1 ;
  • Figure 3 is a sectional view taken along line III-III in Figure 2;
  • Figure 4 is a developed view of area A in Figure 2, showing the arrangement of fuel supply channels;
  • Figure 5 is a developed view of area B in Figure 1 , showing the arrangement of fluid supply ports.
  • Figure 6 is a longitudinal section view of another embodiment of the combustor according to the invention.
  • a combustor according to the invention has an interior annular space generally shown at 10 which is defined by a first circular wall 12 and a second circular wall 14.
  • a combustion area 16 is defined in the annular interior space 10.
  • the combustion area 16 is the area in which combustion takes place.
  • Combustion products leave the combustion area through an outlet 18 at high temperature to be expanded through a gas turbine engine (which is not shown).
  • the combustion gas that is expanded in the turbine stage for performing useful mechanical work moves through the gas turbine engine flow duct, which incorporates the combustor (the engine is not shown).
  • the parameters of the combustion gas change as the combustion gas passes through the flow duct, and this combustion gas contains, among other things, chemically bound oxygen.
  • the combustor has a pre-mixing space 20 which is defined by an annular partition wall 22 located adjacent to, and practically concentric with and on the inner-most circumferential section of second circular wall 14.
  • First circular wall 12 is located opposite to partition wall 22.
  • the pre-mixing space 20 has an entry zone 24 located radially inside outlet area 18 of the combustor and an outlet zone 26 located radially inside combustion area 16 remote from outlet area 18 of the combustor.
  • a fuel supply passage 28 which may be defined by an outer circular wall 30 communicates with a fuel supply to supply fuel to pre-mixing space 20.
  • the fuel supply is not shown.
  • the fuel supply is a fuel tank supply line to a heat exchanger or a fuel heater (not shown) in which the fuel is heated and evaporated.
  • the fuel is fed through fuel supply passage 28 in the vapor phase.
  • the fuel may be a gas fuel which is supplied directly to the fuel supply passage 28.
  • the fuel may be fed to fuel supply passage 28 in the liquid phase.
  • the fuel supply methods do not have any material bearing on the invention.
  • An annular gas passage 32 communicating with a source of ballast gas (a gas containing chemically bound oxygen and/or a combustion gas) supplies the combustion products which are available in the gas turbine engine flow duct.
  • the annular gas passage has an outlet 34.
  • the ballast gas normally has a temperature of 550°C to 700°C.
  • the ballast gas also contains nitrogen, carbon dioxide and water vapor.
  • the ballast gas contains carbon monoxide, which is the most valuable fuel component, and hydrogen, which has the highest heat capacity and contributes to the fuel burning intensity by splitting the chemically bound oxygen molecules.
  • the ballast gas is supplied from the gas turbine engine flow duct (not shown).
  • the combustor has fuel supply channels 36, which communicate with fuel supply passage 28.
  • Fuel supply channels 36 are circumferentially spaced slit channels which in one embodiment may be about 0.125 mm deep and about 1 mm wide. These fuel supply channel dimensions are approximate and are given here as a non-limiting example only; the dimensions for a given set of channels must be determined based on specific combustor output parameters. It is important to have as large a number of these channels as possible and as small a size for each channel as possible to achieve uniform fuel flow in the pre- mixing space, and hence more uniform mixing.
  • An annular manifold 38 ( Figures 1 and 2) at entry zone 24 of pre-mixing space
  • Fuel supply channels 36 extend at an angle ⁇ (see Figure 5) with respect to the plane of longitudinal section of interior annular space 10 of the combustor shown at P ⁇ s in Figure 2.
  • the fuel exits outlet 37 of each fuel supply channel 36 and enters annular manifold 38 at an angle ⁇ , which ranges from 20° to 40°.
  • this angle ⁇ range reflects the most favorable entry conditions for the fuel in order to avoid crowding in the annular manifold and rebound of the fuel flow from an opposite wall 39 of annular manifold 38. Preventing crowding and rebound assures an orderly flow in the manifold and an organized fuel flow exit through the fuel admission opening 40 of annular manifold 38.
  • the cross-sectional area of annular manifold 38 should be greater than the total cross-sectional area of fuel supply channels 36 to prevent pressure surges when fuel exits fuel supply channels 36. This assures uniform fuel flow through annular manifold 38.
  • Projections 42 ( Figure 3) are provided in the fuel admission opening 40 to assure a uniform width for fuel admission opening 40 and to prevent a non-uniform slit size reduction caused by thermal deformations.
  • Fluid supply ports 44 communicate with pre-mixing space 20 at outlet zone 26, and also communicate with an air source.
  • the air source may come from an atmospheric air intake or a compressor.
  • the method in which fluid supply ports 44 communicate with an air source is not shown, it is understood that there are two ways in which air could be supplied to fluid supply ports 44.
  • One way is to supply air directly to the fluid supply ports 44 through a line 45 that connects to an air flow metering device (which is not shown). This connection is shown in Figure 1. It is, however, preferred that air be supplied in a mixture with the ballast gas from a mixer (not shown).
  • the mixer mixes air and ballast gas in a predetermined ratio, in accordance with the operating conditions of the gas turbine engine.
  • line 45 can be dispensed with, and air and ballast gas can be fed through fluid supply ports 44 directly from the mixer.
  • the exact method of supplying air and ballast gas to fluid supply ports 44 does not have any direct bearing on this invention.
  • Fluid supply ports 44 may also communicate with a source of a gas containing chemically bound oxygen that has a temperature of 550° to 700° (lower ports 44 in Figure 1). As mentioned above, this gas may be supplied in a mixture with combustion air from a mixer which is not shown. This gas is necessary to replace a part of air that does not take part in the combustion process. This gas is supplied to replace the air which is fed to the combustion area. The temperature in the combustion area consequently will not rise because the amount of free oxygen is lowered and because this gas mixture has a higher specific heat.
  • fluid supply ports 44 extend at an angle ⁇ with respect to the plane of longitudinal section P ⁇ s of annular interior space 10. Fluid supply ports 44 are inclined in the same direction as fuel supply channels 36. The angle ⁇ should not exceed 40°. If angle ⁇ exceeds 40°, the air flow would impinge upon annular partition wall 22 and create a perturbation of the fuel and ballast gas mixture moving through pre-mixing space 20. How small angle ⁇ can be depends on manufacturing limitations. Additional fluid supply ports 46 communicate with pre-mixing space 20 and with an air source (not shown). The additional fluid supply ports 46 are located between entry zone 24 and outlet zone 26 of pre-mixing space 20.
  • additional fluid supply ports 46 are preferably located at a distance from outlet slit 34 that measures up to one half of the length of pre-mixing space 20. This provides more favorable conditions for the formation of the fuel mixture. Additional fluid supply ports 46 have the same angle and direction of inclination as the fluid supply ports 44. Additional fluid supply ports 46 ensure more uniform fuel and ballast gas mixing with the combustion air by dividing the mixing with air into two steps. In addition, the preliminary mixing with air within pre-mixing space 20 helps in oxidizing the carbon that is present in the partly decomposed fuel before the mixture enters combustion area 16.
  • ports 44 and 46 air only; air and ballast gas to ports 44; air only, ballast gas only, and air and ballast gas to ports 46. These combinations of air and ballast gas supply to pre-mixing space 20 allow for different composition and parameters of the fuel mixture before it enters combustion area 16 of the combustor. Additional fluid supply ports 46 may communicate with an air source through a line 47. Additional fluid supply ports 46 may also communicate with a gas source containing chemically bound oxygen having a temperature of 550°C to 700°C (ballast gas).
  • the ballast gas that is available in the gas turbine engine flow duct is supplied to the intermediate position of pre-mixing space 20 to add reagents (CO 2 , H 2 O) to the reduction reaction zone within pre-mixing space 20. Adding reagents to the reduction reaction zone maintains the optimum reaction mixture composition in this zone because the ballast gas moving with the fuel through pre- mixing space 20 depletes these reagents.
  • reagents CO 2 , H 2 O
  • This additional ballast gas may also be supplied through line 47 instead of from an air source. Both air and ballast gas may be supplied to additional fluid supply ports 46 from a mixer in the same manner as described above with reference to fluid supply ports 44.
  • the fuel vapor that escapes from fuel supply channels 36 enters annular manifold 38 and forms a continuous uniform layer within fuel admission opening 40.
  • the fuel vapor which escapes from fuel admission opening 40 is mixed uniformly with the ballast gas that escapes from outlet 34 of gas passage 32.
  • the ballast gas causes the fuel vapor to move through pre-mixing space 20 toward outlet zone 26.
  • the velocity vector of the fuel flow which escapes from fuel admission opening 40 differs in direction and magnitude from the velocity vector of the ballast gas which exits outlet 34 of gas passage 32, thus ensuring thorough mixing of the two fluids before mixing with combustion air.
  • a part of the ballast gas containing chemically bound oxygen is supplied from a source of the ballast gas through an annular channel 148 as shown by arrow "C" and through a channel 150 which extends along the length "LI" of a circular wall 112.
  • Channel 150 terminates at an outlet zone 126 of a pre-mixing space 120.
  • This supply of the ballast gas to outlet zone 126 along circular wall 112 allows the heat that is in abundance in the hottest part of a combustion area 116 to be transferred to outlet zone 126 of pre- mixing space 120. This heat transfer allows the heat to be removed from the hottest part of the combustor.
  • both air and ballast gas are supplied to fluid supply ports 144 and additional fluid supply ports 146 from the gas turbine engine flow duct.
  • the same options with feeding (a) only the air to ports 144, or (b) either only the air or only the ballast gas to ports 146 are possible in the same manner as was described with reference to Figure 1.
  • the supply of ballast gas to the combustion area with the fuel and combustion air creates milder conditions for combustion, and the temperature in the combustion area may be lowered. This lower temperature coupled with a lower oxygen level results in reduced NOx emissions.
  • a mixture of the ballast gas and combustion air may be prepared in a mixing device before the combustion air and the ballast gas are supplied to the pre-mixing space 20. This will allow the ratio between the air and ballast gas to be controlled to control the conditions for combustion in the combustor depending on the demand of the gas turbine engine incorporating the combustor.

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

Abstract

L'invention concerne une chambre de combustion pour une turbine à gaz. Cette chambre de combustion comprend un espace (16) intérieur annulaire destiné à la combustion, et un espace (20) de pré-mélange pourvu d'une zone d'entrée (24) et d'une zone de sortie (26) et dans lequel du carburant (28) et un gaz (32) de ballast sont mélangés puis chauffés à une température de 650 °C à 1300 °C avant d'être combinés avec de l'air (44) pour la combustion et avant d'entrer dans la zone de combustion (16).
PCT/US2000/026252 1999-10-12 2000-10-11 Chambre de combustion et procede de combustion de carburant WO2001027534A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU79856/00A AU7985600A (en) 1999-10-12 2000-10-11 Combustor and method of burning fuel

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US15906699P 1999-10-12 1999-10-12
US60/159,066 1999-10-12
US63305300A 2000-08-04 2000-08-04
US09/633,053 2000-08-04

Publications (1)

Publication Number Publication Date
WO2001027534A1 true WO2001027534A1 (fr) 2001-04-19

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PCT/US2000/026252 WO2001027534A1 (fr) 1999-10-12 2000-10-11 Chambre de combustion et procede de combustion de carburant

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AU (1) AU7985600A (fr)
WO (1) WO2001027534A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006060004A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Dispositif de combustion pour moteur de turbine
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
WO2014071065A3 (fr) * 2012-11-02 2016-06-23 General Electric Company Système et procédé pour une chambre de combustion de turbine
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US158934A (en) 1875-01-19 Improvement in machines for making toy confectionery
US158929A (en) 1875-01-19 Improvement in reflectors
US158935A (en) 1875-01-19 Improvement in car-couplings
US159065A (en) 1875-01-26 Improvement in sewing-machines
US3927958A (en) * 1974-10-29 1975-12-23 Gen Motors Corp Recirculating combustion apparatus
US4563875A (en) * 1974-07-24 1986-01-14 Howald Werner E Combustion apparatus including an air-fuel premixing chamber
US5265425A (en) * 1991-09-23 1993-11-30 General Electric Company Aero-slinger combustor
US5473882A (en) * 1993-06-03 1995-12-12 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Combustion apparatus for a gas turbine having separate combustion and vaporization zones
US5651252A (en) * 1995-02-15 1997-07-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Fuel injection assembly for a gas turbine engine
EP0985882A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Amortissement des vibrations dans des combusteurs

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US158934A (en) 1875-01-19 Improvement in machines for making toy confectionery
US158929A (en) 1875-01-19 Improvement in reflectors
US158935A (en) 1875-01-19 Improvement in car-couplings
US159065A (en) 1875-01-26 Improvement in sewing-machines
US4563875A (en) * 1974-07-24 1986-01-14 Howald Werner E Combustion apparatus including an air-fuel premixing chamber
US3927958A (en) * 1974-10-29 1975-12-23 Gen Motors Corp Recirculating combustion apparatus
US5265425A (en) * 1991-09-23 1993-11-30 General Electric Company Aero-slinger combustor
US5473882A (en) * 1993-06-03 1995-12-12 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Combustion apparatus for a gas turbine having separate combustion and vaporization zones
US5651252A (en) * 1995-02-15 1997-07-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Fuel injection assembly for a gas turbine engine
EP0985882A1 (fr) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Amortissement des vibrations dans des combusteurs

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006060004A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Dispositif de combustion pour moteur de turbine
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
WO2014071065A3 (fr) * 2012-11-02 2016-06-23 General Electric Company Système et procédé pour une chambre de combustion de turbine
US9869279B2 (en) 2012-11-02 2018-01-16 General Electric Company System and method for a multi-wall turbine combustor

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Publication number Publication date
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