WO2024079656A1 - Brûleur par tout ou peu à écoulement à contre-courant tourbillonnaire à deux couches - Google Patents

Brûleur par tout ou peu à écoulement à contre-courant tourbillonnaire à deux couches Download PDF

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Publication number
WO2024079656A1
WO2024079656A1 PCT/IB2023/060239 IB2023060239W WO2024079656A1 WO 2024079656 A1 WO2024079656 A1 WO 2024079656A1 IB 2023060239 W IB2023060239 W IB 2023060239W WO 2024079656 A1 WO2024079656 A1 WO 2024079656A1
Authority
WO
WIPO (PCT)
Prior art keywords
section
flame tube
swirler
nozzle
inlet nozzle
Prior art date
Application number
PCT/IB2023/060239
Other languages
English (en)
Inventor
Roman ILIEV
Original Assignee
Ecospectr Llc
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
Priority claimed from RU2022126445A external-priority patent/RU2797727C1/ru
Application filed by Ecospectr Llc filed Critical Ecospectr Llc
Publication of WO2024079656A1 publication Critical patent/WO2024079656A1/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
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/58—Cyclone or vortex type combustion chambers

Definitions

  • Embodiments of the invention relate to fuel combustion devices, in particular to vortex burners.
  • the invention relates to fuel combustion devices, in particular to vortex burners.
  • the prior art is a device for burning fuel, described in the patent for the invention RU 2708011, publ. 03.12.2019.
  • the device contains three types of fuel supply devices.
  • the first type of fuel supply devices is made in the form of jet nozzles located in the swirler, the outlet openings of the flow channels of which are perpendicular to the end wall of the swirler, and the outlet openings of the channels exit in the minimum cross section of the flow channels of the tangential nozzle swirler.
  • the second type of devices contains at least one centrifugal nozzle.
  • the third type of devices is made in the form of a branch pipe installed in the axial hole on the end wall of the flame tube.
  • the second and third types of fuel supply devices are located at the end of the flame tube opposite from the swirler.
  • EFFECT invention provides increased launch reliability and stable operation on liquid, gaseous and ballasted fuels both with non-combustible components and water, as well as fuel, including crushed solid combustible components and their mixtures with water
  • the specified device for burning fuel is the closest in technical essence to the claimed invention and was used as a prototype.
  • Two-stage burner with a two-layer vortex counter current flow comprises a burner body and a flame tube containing an ignition device coaxially installed in it, and an outlet nozzle, between the burner body and the flame tube there is an air channel with the first swirler placed in it.
  • the flame tube is made of the first section and the second section, separated by a partition wall comprising an outlet nozzle, the front wall of the first section has a toroidal shape, forming an inlet nozzle inside the first section, which is connected to the air channel.
  • the first fuel supply device is located in the inlet nozzle, inside the first and second sections near the partition wall there are second and third swirlers connected to the air channel and to the second and third fuel supply devices, respectively.
  • the first swirler is combined with the inlet nozzle.
  • EFFECT improved formation of the combustion zone and efficient afterburning of fuel in a wide range of operating modes due to the use of a profiled end in the flame tube and the presence of two combustion zones, as well as a uniform air supply to the channel between the body and the flame tube.
  • FIG. 1 is a schematic illustration of a two stage burner according to embodiments of the invention.
  • the terms “plurality” and “a plurality” as used herein may include, for example, “multiple” or “two or more”.
  • the terms “plurality” or “a plurality” may be used throughout the specification to describe two or more components, devices, elements, units, parameters, or the like.
  • the term set when used herein may include one or more items.
  • the method embodiments described herein are not constrained to a particular order or sequence. Additionally, some of the described method embodiments or elements thereof can occur or be performed simultaneously, at the same point in time, or concurrently.
  • the technical result of the claimed invention consists in improved formation of the combustion zone and efficient afterburning of fuel in a wide range of operating modes due to the use of a profiled end in the flame tube and the presence of two combustion zones, as well as a uniform air supply to the channel between the housing and the flame tube.
  • the second section of the flame tube as a transition pipe for connection with a gas turbine plant.
  • a two-stage burner with a two-layer vortex countercurrent flow containing a burner body and a flame tube containing an ignition device coaxially installed in it, and an outlet nozzle, between the burner body and the flame tube there is an air channel with the first swirler placed in it, while the flame tube is made in the form of two sections interconnected and between which the outlet nozzle is located, the front wall of the first section has a toroidal shape, forming the inlet nozzle inside the section, which is connected to the air channel, the first fuel supply device is located in the inlet nozzle, inside each section at the outlet nozzle there are the second and third swirlers connected to the air channel, and the second and third fuel supply devices, respectively.
  • the toroidal shape of the front wall of the burner makes it possible to reduce the resistance to the air flow passing through the air channel to the inlet nozzle, and contributes to the creation of a swirling paraxial flow and a combustion stabilization zone inside the flame tube.
  • the location of the first swirler can be combined with the inlet nozzle.
  • the implementation of the two-section flame tube allows efficient afterburning of combustion products from the first section in the second in the entire range of operating modes due to the creation in each section of a separate vortex flow of the fuel-air mixture and combustion products: counter-current (in the first section) and direct-flow (in the second section). Also, this embodiment of the pipe allows you to significantly expand the range of stable operation of the combustion chamber with low emission characteristics of emissions.
  • Fig. 1 is a schematic illustration of a two-stage burner 100 according to embodiments of the present invention.
  • Two-stage burner 100 with a two-layer vortex countercurrent flow comprises a housing 105 and a flame tube 110 containing an ignition device and made of two sections (see Fig.).
  • An air channel 112 is made between the body or housing 105 and the flame tube 110, through which the air mixture enters the flame tube 110.
  • the first swirler 1 is located in this channel 112, which ensures the creation of a paraxial vortex in the flame tube, passing along its entire length.
  • the first section 11 la and the second section 11 lb of the flame tube are interconnected and separated by a partition wall 115 having an opening in which the outlet nozzle 120 of the flame tube 110 is located.
  • the outlet nozzle 120 is a cylindrical ring with a diameter of D2 with a longitudinal length exceeding the thickness of the baffle.
  • the flame tube 110 and the outlet nozzle 120 are arranged coaxially relative to each other.
  • the main body of the flame tube has a cylindrical shape.
  • the front wall 125 of the first section 11 la has a toroidal shape (or W-shaped profile).
  • the form is made in such a way that the part protruding inside the first section is an inlet window 130, which is connected with an air channel, which practically repeats the shape of the front wall of the first section and goes into the inlet window.
  • the specified window 130 is an inlet nozzle with a diameter of DI, through which the air flow for the paraxial vortex enters.
  • the first swirler 1 is located either near the inlet nozzle or directly in the inlet nozzle itself.
  • the first fuel supply device 150a is also located in the inlet nozzle 130.
  • the toroidal shape of the front wall 125 and, accordingly, the air channel in this area contributes to a smooth reversal of the air flow in the opposite direction and the creation of an axial flow in the flame tube 105.
  • the presence of a swirler in the channel makes such a flow swirling and efficient for mixing with the fuel from the first fuel feeder 150a.
  • the second swirler 2 and the third swirl 3, respectively, are installed, which are connected to the air channel 112.
  • These swirlers are located near the partition wall 115 and create peripheral vortices of fuel- air mixtures in their sections.
  • the second swirler 2 ensures the creation of a vortex movement in the first section I lla, directed opposite to the axial vortex movement (a countercurrent flow is created).
  • the third swirler 3 creates a paraxial vortex in the second section 11 lb, moving unidirectionally with the paraxial flow (cocurrent flow is created).
  • the second swirler 2 and the third swirl 3 are connected to the second and third fuel supply devices 150b, 150c, respectively.
  • the partition wall 115 between the sections makes it possible to separate the combustion zones, forming a combustion zone 1 and a combustion zone 2, thereby facilitating the afterburning of residual gases from the first section to the second.
  • Three fuel supply devices 150a, 150b, 150c provide an increase in the range of stable operation of the claimed burner 100 when its load changes. So, during the operation of a two- stage burner 100 at low power levels (less than 30% of the maximum), fuel is not supplied to the third fuel supply device, afterburning of the residual gases of the first section is carried out due to the air flow from the third swirler.
  • Methane, propane, butane, diesel, kerosene or gasoline can be used as fuel. It is also possible, in some burner applications, to supply a low-calorie fuel such as syngas or pyrolysis gas to the third fuel supply.
  • a low-calorie fuel such as syngas or pyrolysis gas
  • the second section 11 IB of the flame tube 105 has a profiled shape that allows you to connect to the nozzle apparatus of the turbine of the gas turbine plant without using additional adapters in the form of nozzles.
  • the second section 111b is a gas collector. Structurally, it is made as follows: the front part of the second section, attached to the first section, has a cylindrical design, and the outlet part, which is connected to the gas turbine plant, has a trapezoidal shape.
  • the operation of a two-stage burner with a two-layer vortex countercurrent flow is carried out as follows. Air is supplied to the air channel, which enters the corresponding sections of the flame tube through the first, second and third swirlers.
  • the first and second fuel supply devices are supplied with fuel, which is mixed with air to form a fuel-air mixture.
  • the fuel-air mixture from the second swirler moves in a spiral along the inner surface of the first section, creating a peripheral vortex that cools the walls of the flame tube. Reaching the toroidal wall, this vortex unfolds and merges with the central vortex formed by the first swirler from the inlet nozzle, forming a stable combustion stabilization zone, which is ignited in the start mode by the ignition device installed in the first section.
  • Combustion products come from the first section to the second through the outlet nozzle, where they mix with the air flow from the third swirler to bum off residual combustible gases.
  • the presence of three swirlers 1, 2, 3 through which air enters, allows you to reduce the combustion temperature and control harmful emissions of nitrogen oxides and carbon oxides.
  • the third fuel supply device which is mixed with the air flow of the third swirler to form a fuel-air mixture, followed by its ignition in the axial zone of the second section.

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

Abstract

La présente invention concerne un brûleur par tout ou peu (100) à écoulement à contre-courant tourbillonnaire à deux couches, lequel brûleur par tout ou peu comprend un corps de brûleur (105) et un tube à flamme (110) contenant un dispositif d'allumage et une buse de sortie (120). Un canal d'air (112) ayant une première coupelle de turbulence (1) est disposé entre le corps de brûleur (105) et le tube à flamme (110). Le tube à flamme (110) est constitué d'une première section (Illa) et d'une seconde section (lib), séparées par une paroi de séparation (115) comprenant une buse de sortie (120). La paroi avant (125) de la première section (Illa) a une forme toroïdale, formant une buse d'entrée (130) à l'intérieur de la première section (Illa). Un premier dispositif d'alimentation en combustible (150a) est situé dans la buse d'entrée (130). Des deuxième et troisième coupelles de turbulence (2, 3) reliées au canal d'air (112) et à des deuxième et troisième dispositifs d'alimentation en combustible (150b, 150c), respectivement, sont disposées à l'intérieur des première et seconde sections (Illa, 111b) près de la paroi de séparation (115). La première coupelle de turbulence (1) est combinée à la buse d'entrée. La partie de sortie de la seconde section du tube à flamme (110) a une forme trapézoïdale.
PCT/IB2023/060239 2022-10-11 2023-10-11 Brûleur par tout ou peu à écoulement à contre-courant tourbillonnaire à deux couches WO2024079656A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2022126445A RU2797727C1 (ru) 2022-10-11 Двухступенчатая горелка с двухслойным вихревым противоточным течением
RU2022126445 2022-10-11

Publications (1)

Publication Number Publication Date
WO2024079656A1 true WO2024079656A1 (fr) 2024-04-18

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB825124A (en) * 1955-09-14 1959-12-09 Reginald Percy Fraser Improvements relating to combustion chambers and to the production of clean gaseous combustion products
US4420929A (en) * 1979-01-12 1983-12-20 General Electric Company Dual stage-dual mode low emission gas turbine combustion system
US5195315A (en) * 1991-01-14 1993-03-23 United Technologies Corporation Double dome combustor with counter rotating toroidal vortices and dual radial fuel injection
US6263663B1 (en) * 1998-06-11 2001-07-24 Institut Francais Du Petrole Variable-throat gas-turbine combustion chamber
JP2011163626A (ja) * 2010-02-08 2011-08-25 Niigata Power Systems Co Ltd ガスタービン燃焼器及びガスタービン燃焼器における燃焼用空気供給方法
US20180245792A1 (en) * 2017-02-24 2018-08-30 General Electric Company Combustion System with Axially Staged Fuel Injection
WO2022154693A1 (fr) * 2021-01-13 2022-07-21 Роман Лазирович Илиев Brûleur à écoulement à contre courant tourbillonnaire à deux couches

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB825124A (en) * 1955-09-14 1959-12-09 Reginald Percy Fraser Improvements relating to combustion chambers and to the production of clean gaseous combustion products
US4420929A (en) * 1979-01-12 1983-12-20 General Electric Company Dual stage-dual mode low emission gas turbine combustion system
US5195315A (en) * 1991-01-14 1993-03-23 United Technologies Corporation Double dome combustor with counter rotating toroidal vortices and dual radial fuel injection
US6263663B1 (en) * 1998-06-11 2001-07-24 Institut Francais Du Petrole Variable-throat gas-turbine combustion chamber
JP2011163626A (ja) * 2010-02-08 2011-08-25 Niigata Power Systems Co Ltd ガスタービン燃焼器及びガスタービン燃焼器における燃焼用空気供給方法
US20180245792A1 (en) * 2017-02-24 2018-08-30 General Electric Company Combustion System with Axially Staged Fuel Injection
WO2022154693A1 (fr) * 2021-01-13 2022-07-21 Роман Лазирович Илиев Brûleur à écoulement à contre courant tourbillonnaire à deux couches

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DATABASE WPI Week 201158, Derwent World Patents Index; AN 2011-K80741, XP002810762 *

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