EP3322939A1 - Brûleur pour turbine à gaz - Google Patents

Brûleur pour turbine à gaz

Info

Publication number
EP3322939A1
EP3322939A1 EP16739076.4A EP16739076A EP3322939A1 EP 3322939 A1 EP3322939 A1 EP 3322939A1 EP 16739076 A EP16739076 A EP 16739076A EP 3322939 A1 EP3322939 A1 EP 3322939A1
Authority
EP
European Patent Office
Prior art keywords
swirler
burner
channel
air flow
base plate
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.)
Withdrawn
Application number
EP16739076.4A
Other languages
German (de)
English (en)
Inventor
Ghenadie Bulat
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP3322939A1 publication Critical patent/EP3322939A1/fr
Withdrawn legal-status Critical Current

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
    • F23R3/02—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
    • F23R3/286—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
    • 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
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • 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
    • F23C7/02—Disposition of air supply not passing through burner
    • F23C7/06—Disposition of air supply not passing through burner for heating the incoming air
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery

Definitions

  • Burner for a gas turbine A burner for a gas turbine can be operated at certain
  • DLE dry low emission
  • the DLE burners comprise fuel lances for the injection of a liquid fuel into the combustion chamber, wherein the lances are sized such that an efficient
  • the pressure drop over the lances is lower in comparison to the full load operation, which results in a less efficient atomisation than at the full load operation.
  • the carbon build-up is formed on the lances it can lead to an obstruction of the fuel and when this carbon build-up is formed at an igniter- port it can lead to a reduction in the efficiency of
  • the DLE combustor is operated such that compressed air is bled from the gas turbine so that less air enters the combustion chamber which raises the flame temperature. With this higher temperature the carbon build-up can at least be partly burned.
  • this operation is disadvantageous since it reduces the efficiency of the gas turbine and can not be performed at a part load of less than 40% of the full load.
  • the burner according to the invention for a gas turbine comprises a combustion chamber, a preheating device adapted to preheat air before it enters the combustion chamber and a swirler adapted to guide a swirler air flow that comprises the preheated air to the combustion chamber, wherein the swirler comprises a wall with a surface that confines the swirler air flow, wherein the surface has a hole adapted to inject a liquid fuel into the swirler air flow and the wall has a channel for transporting the liquid fuel to the hole, wherein at least a part of the channel is oriented
  • the liquid fuel can stream essentially parallel to the surface and can be preheated by the swirler air flow.
  • the viscosity of the liquid fuel is reduced when its temperature is increased by the preheating. This leads advantageously to an efficient atomisation of the liquid fuel and therefore to an efficient mixing of the fuel with the air.
  • the atomisation and the mixing will also be efficient at a part load operation of the burner when the pressure drop of the liquid fuel over the through hole is lower than at a full load operation of the burner.
  • the hole requires a lower pressure drop for the atomisation of the liquid fuel in comparison to a fuel lance. Also for this reason an efficient atomisation of the liquid fuel can take place at low part loads. It is preferred that the part of the channel which is
  • the diameter of the hole is preferably from 0.5 mm to 3 mm. It is preferred that the diameter of the channel in a plane perpendicular to the flow direction of the liquid fuel is from 0.5 mm to 3 mm.
  • the material of the wall preferably consists of carbon steel and/or steel with 1 weight-% carbon. The carbon steel has a heat conductivity of 54 W/ (m*K) and the steel with 1 weight-% carbon has a heat conductivity of 43 W/ (m*K) which are much higher values than the heat conductivity of 16 W/ (m*K) for the conventionally used stainless steel.
  • the wall with the channel is formed by electronic discharge machining, selective laser sintering and/or selective laser melting. With these techniques it is advantageously possible to form channels with complex
  • the wall preferably comprises two joint plates, wherein each plate comprises recesses that form a part of the channel.
  • the recesses in the plates can be formed by milling that is advantageously a simple and cost- efficient technique.
  • the channel has the shape of a spiral.
  • the channel has a meandering shape. With both shapes it is possible to bring a long section of the channel close to the surface, hence making the heat transfer to the liquid fuel particularly efficient .
  • the burner comprises a compressor for compressing the air before it enters the combustion chamber, whereby the temperature of the air raises and the compressor forms the preheating device. By preheating the air in this manner, it is advantageously achieved that the air is
  • the burner comprises preferably a further wall confining the swirler air flow on the same side as and upstream with respect to the swirler air flow from the wall and being displaced with respect to the wall in a direction towards the swirler air flow so that a step being able to cause a flow separation of the swirler air flow is formed by the wall and the further wall.
  • the flow separation caused by the step causes the formation of a vortex downstream with respect to the swirler air flow. Since the liquid fuel is injected via the through hole into the swirler air flow and not by a lance that would protrude from the wall, the liquid fuel is
  • the combustion chamber is essentially rotationally symmetric around a burner axis and the step is located at a radial distance from the burner axis which is from ri+0.2* ( r 2 - ri ) to ri+0.8* ( r 2 - ri ) , wherein ri is the radial distance from the burner axis to the radial inner end of the swirler and r 2 is the radial distance from the burner axis to the radial outer end of the swirler.
  • the lower boundary advantageously ensures an efficient interaction of the liquid fuel with the vortex.
  • the upstream boundary advantageously ensures the formation of the vortex.
  • each step is preferably from 0.2*L to 0.5*L, wherein L is the distance from the step to the hole. This height advantageously ensures the formation of the vortex that is efficiently interacting with the liquid fuel. It is preferred the height of each step is maximum 15 % of the swirler channel height, wherein the swirler channel height is the distance from the further wall to an opposite wall confining the swirler air flow and facing towards the wall. This maximum height advantageously avoids a large pressure drop of the swirler air flow when passing the step .
  • Fig. 1 shows part of a gas turbine in a sectional view and in which the present inventive burner is incorporated
  • Fig. 2 shows a longitudinal section of the burner and a part of the combustor
  • Fig. 3 shows a perspective view of a part of the a swirler of the burner
  • Fig. 4 shows a sectional view of a part of the swirler with a first channel
  • Fig. 5 shows a top view of the swirler
  • Fig. 6 shows a perspective view of a part of the swirler with a second channel
  • Fig. 7 shows a perspective view of a part of the swirler with a third channel
  • Fig. 8 shows a sectional view of a part of the swirler with a fourth channel.
  • Figs. 9 to 13 show different embodiments for holes of the swirler.
  • Figure 1 shows an example of a gas turbine engine 10 in a sectional view.
  • the gas turbine engine 10 comprises, in flow series, an inlet 12, a compressor section 14, a combustor section 16 and a turbine section 18 which are generally arranged in flow series and generally about and in the direction of a longitudinal or rotational axis 20.
  • the gas turbine engine 10 further comprises a shaft 22 which is rotatable about the rotational axis 20 and which extends longitudinally through the gas turbine engine 10.
  • the shaft 22 drivingly connects the turbine section 18 to the
  • air 24 which is taken in through the air inlet 12 is compressed by the compressor section 14 and delivered to the combustion section or burner section 16.
  • the burner section 16 comprises a burner plenum 26, one or more combustion chambers 28 and at least one burner 30 fixed to each combustion chamber 28.
  • the combustion chambers 28 and the burners 30 are located inside the burner plenum 26.
  • the compressed air preheated through the compressor 14 enters a diffuser 32 and is discharged from the diffuser 32 into the burner plenum 26 from where a portion of the air enters the burner 30 and is mixed with a gaseous or liquid fuel.
  • This exemplary gas turbine engine 10 has a cannular combustor section arrangement 16, which is constituted by an annular array of combustor cans 19 each having the burner 30 and the combustion chamber 28, the transition duct 17 has a generally circular inlet that interfaces with the combustor chamber 28 and an outlet in the form of an annular segment.
  • An annular array of transition duct outlets form an annulus for
  • the turbine section 18 comprises a number of blade carrying discs 36 attached to the shaft 22.
  • two discs 36 each carry an annular array of turbine blades 38.
  • the number of blade carrying discs could be different, i.e. only one disc or more than two discs.
  • guiding vanes 40 which are fixed to a stator 42 of the gas turbine engine 10, are disposed between the stages of annular arrays of turbine blades 38. Between the exit of the combustion chamber 28 and the leading turbine blades 38 inlet guiding vanes 44 are provided and turn the flow of working gas onto the turbine blades 38.
  • the combustion gas from the combustion chamber 28 enters the turbine section 18 and drives the turbine blades 38 which in turn rotate the shaft 22.
  • the guiding vanes 40, 44 serve to optimise the angle of the combustion or working gas on the turbine blades 38.
  • the turbine section 18 drives the compressor section 14.
  • the compressor section 14 comprises an axial series of vane stages 46 and rotor blade stages 48.
  • the rotor blade stages 48 comprise a rotor disc supporting an annular array of blades.
  • the compressor section 14 also comprises a casing 50 that surrounds the rotor stages and supports the vane stages 48.
  • the guide vane stages include an annular array of
  • vanes that are mounted to the casing 50.
  • the vanes are provided to present gas flow at an optimal angle for the blades at a given engine operational point.
  • Some of the guide vane stages have variable vanes, where the angle of the vanes, about their own longitudinal axis, can be adjusted for angle according to air flow characteristics that can occur at different engine operations conditions.
  • the casing 50 defines a radially outer surface 52 of the passage 56 of the compressor 14.
  • a radially inner surface 54 of the passage 56 is at least partly defined by a rotor drum 53 of the rotor which is partly defined by the annular array of blades 48.
  • Figure 2 shows that the burner 30 comprises an inner wall 101 that confines the combustion chamber 28 in a radial
  • the burner 30 comprises a pilot burner 104 and a main burner 105 that are arranged on an axial end of the burner 30 and confine an axial end of the combustion chamber 28.
  • the main burner 105 is arranged radially outside from the pilot burner 104.
  • the burner 30 comprises an outer wall 102 that is arranged radially outside of the inner wall 101.
  • the inner wall 101 and the outer wall 102 are essentially rotationally symmetric around a burner axis 35 of the burner 30.
  • the air 24 is streamed in the space between the inner wall 101 and the outer wall 102 towards the pilot burner 104 and the main burner 105 as indicated by arrows 108, so that the inner wall 101 is cooled and the air 24 is preheated before it enters the combustion chamber 28.
  • the inner wall 101 and the outer wall 102 form a preheating device for preheating the air.
  • the burner 30 comprises a swirler 107 located on the main burner 105 for swirling the air before it enters the
  • the burner 30 is configured for dry operation only, i.e. it is not configured for the injection of water into the combustion chamber 28.
  • the swirler 107 comprises a first axial end 113 that
  • the swirler 107 furthermore comprises a multitude of swirler sectors or vanes 118 that are in contact with the first axial end 113 and the second axial end 114.
  • the first axial end 113, the second axial end 114 and the swirler sectors 118 confine a swirler air flow 125.
  • the swirler sectors 118 are shaped such that the air flow entering the combustion chamber 28 has a flow direction with respect to the burner axis 35, wherein the flow
  • the swirler 107 comprises an annular array of vanes 118 (swirler sectors) extending from a base plate or wall 116 which define an annular array of passages for the swirler airflow (125) .
  • the base plate 116 defines one of the surfaces of the passages over which the swirler air flow 125 flows.
  • Figures 2 to 8 show that the swirler 107 comprises a wall or base plate 116 with a surface that confines the swirler air flow 125 at the first axial end 113.
  • the surface has a hole
  • the wall has a channel 131 to 134 for transporting the liquid fuel to the hole 103, wherein at least a part of the channel 131 to 134 is oriented essentially parallel to the surface so that the liquid fuel can stream essentially parallel to the surface and is partly preheated by the swirler air flow 125.
  • the swirler itself incurs temperature input directly from the combustion flame and the surrounding combustor or burner architecture. As it can be seen in
  • the liquid fuel is atomised and mixed with the swirler air flow 125 in an atomisation region 119.
  • the part of the channel 131 to 134 which is oriented essentially parallel to the surface has a distance to the surface from 2 mm to 10 mm.
  • the diameter of the hole 103 is from 0.5 mm to 3 mm.
  • the diameter of the channel 131 to 134 in a plane perpendicular to the flow direction of the liquid fuel is from 0.5 mm to 3 mm.
  • the wall 116 consists of a material with high heat conductivity, for example carbon steel and/or steel with 1 weight-% carbon. It is conceivable that the wall 116 with the channel 131 to 134 is formed by electronic discharge machining, selective laser sintering and/or selective laser melting.
  • the burner 30 comprises a further wall 115 confining the swirler air flow 125 on the same side as and upstream with respect to the swirler air flow 125 from the wall 116.
  • the further wall 115 can be displaced with respect to the wall 116 in a direction towards the swirler air flow so that a step being able to cause a flow separation of the swirler air flow 125 is formed by the wall 116 and the further wall 115.
  • Figure 4 shows the burner 30 with a first channel 131.
  • the first channel 131 has a meandering shape, wherein a multitude of sections of the first channel 131 are arranged next to each other in the axial direction with respect to the burner axis 35.
  • Figure 6 shows the burner 30 with a second channel 132.
  • the second channel 132 has a meandering shape, wherein the section of the second channel 132 with the meandering shape is arranged parallel to the surface of wall 116.
  • Figure 7 shows the burner 30 with a third channel 133.
  • the third channel 133 has the shape of a spiral, wherein the hole 103 is located in the centre of the spiral.
  • Figure 8 shows the burner 30 with a fourth channel 134.
  • the fourth channel 134 has a meandering shape, wherein a multitude of sections of the forth channel 134 are arranged next to each other in the axial direction with respect to the burner axis 35.
  • the fourth channel 134 extends almost over the entire wall 116 for an effective heat transfer from the swirler air flow 125 to the liquid fuel.
  • Figure 4 shows the swirler 107 with the second channel 132 according to Figure 6 and and the third channel 133 according to Figure 7. As it can be seen in Figure 4 a single hole 103 can be arranged between two neighboured swirler sectors 108 or a multitude of holes can be arranged between two
  • Figures 9 to 13 show possible geometries for the holes 103.
  • the first hole 121 according to Figure 9 has the shape of a circle with a missing sector having an angle of 90°.
  • the second hole 122 according to Figure 10 has the shape of a ring.
  • the hole 123 according to Figure 11 consists of a plurality of elongate holes that are arranged tilted with respect to each other.
  • the hole 124 according to Figure 12 has the form of a circle.
  • Figure 13 shows a perspective view of a plate 126 containing the hole 124 according to Figure 12.
  • the holes 103 can be formed as an assembly of several joint layers of metal.
  • the invention is not constrained by the disclosed examples and other variations can be derived by the person skilled in the art, without leaving the extent of the protection of the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Spray-Type Burners (AREA)

Abstract

L'invention concerne un brûleur pour une turbine à gaz (10), où le brûleur (30) comprend une chambre de combustion (28), un dispositif de préchauffage conçu pour préchauffer de l'air avant qu'il entre dans la chambre de combustion (28) et un générateur de turbulences (107) conçu pour guider un écoulement d'air de générateur de turbulences (125) qui comprend l'air préchauffé jusqu'à la chambre de combustion (28), où le générateur de turbulences (107) comprend une plaque de base (116) avec une surface qui confine l'écoulement d'air du générateur de turbulences (125), où la surface comporte un trou (103) conçu pour injecter un combustible liquide dans l'écoulement d'air du générateur de turbulences (125) et la plaque de base comporte un canal (131 à 134) pour transporter le combustible liquide jusqu'au trou (103), où au moins une partie du canal (131 à 134) est orientée essentiellement parallèlement à la surface pour que le combustible liquide puisse ruisseler essentiellement parallèlement à la surface et puisse être préchauffé par l'écoulement d'air de générateur de turbulences (125).
EP16739076.4A 2015-07-13 2016-07-08 Brûleur pour turbine à gaz Withdrawn EP3322939A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP15176506 2015-07-13
PCT/EP2016/066333 WO2017009247A1 (fr) 2015-07-13 2016-07-08 Brûleur pour turbine à gaz

Publications (1)

Publication Number Publication Date
EP3322939A1 true EP3322939A1 (fr) 2018-05-23

Family

ID=53673765

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16739076.4A Withdrawn EP3322939A1 (fr) 2015-07-13 2016-07-08 Brûleur pour turbine à gaz

Country Status (4)

Country Link
US (1) US20180195724A1 (fr)
EP (1) EP3322939A1 (fr)
CN (1) CN107850309A (fr)
WO (1) WO2017009247A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3450850A1 (fr) * 2017-09-05 2019-03-06 Siemens Aktiengesellschaft Ensemble de chambre de combustion de turbine à gaz ayant une cavité à vortex piégé
GB201910284D0 (en) 2019-07-18 2019-09-04 Rolls Royce Plc Fuel injector
WO2021243406A1 (fr) * 2020-06-02 2021-12-09 Amaero Engineering Pty Ltd Outil défibreur et procédé de fabrication d'un outillage similaire

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7065972B2 (en) * 2004-05-21 2006-06-27 Honeywell International, Inc. Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions
EP1890083A1 (fr) * 2006-08-16 2008-02-20 Siemens Aktiengesellschaft Injecteur de carburant pour une turbine à gaz
GB2443431B (en) * 2006-11-02 2008-12-03 Siemens Ag Fuel-injector nozzle
CN204404240U (zh) * 2014-10-28 2015-06-17 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机燃烧室喷嘴

Also Published As

Publication number Publication date
CN107850309A (zh) 2018-03-27
US20180195724A1 (en) 2018-07-12
WO2017009247A1 (fr) 2017-01-19

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