EP2949999A1 - Ensemble d'injection de combustible pour une turbine à gaz - Google Patents

Ensemble d'injection de combustible pour une turbine à gaz Download PDF

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Publication number
EP2949999A1
EP2949999A1 EP14170275.3A EP14170275A EP2949999A1 EP 2949999 A1 EP2949999 A1 EP 2949999A1 EP 14170275 A EP14170275 A EP 14170275A EP 2949999 A1 EP2949999 A1 EP 2949999A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
fuel injection
injection assembly
fuel
combustion unit
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Withdrawn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
EP14170275.3A
Other languages
German (de)
English (en)
Inventor
Gaurav Gupta
Sebastian Pfadler
Manoj Singh
Ram Bahadur SINGH
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
Original Assignee
Siemens AG
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 filed Critical Siemens AG
Priority to EP14170275.3A priority Critical patent/EP2949999A1/fr
Priority to PCT/EP2015/059062 priority patent/WO2015180909A1/fr
Publication of EP2949999A1 publication Critical patent/EP2949999A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow 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
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes

Definitions

  • This invention relates to a gas turbine comprising a combustion unit, a flow sleeve surrounding the combustion unit, wherein the flow sleeve is positioned radially outward from the combustion unit.
  • the gas turbine comprises a flange means for supporting the combustion unit and a fuel injection assembly provided with a hollow fuel supply casing having an outer wall.
  • compressed air is discharged from a compressor section and fuel introduced from a source of fuel are mixed together and burned in a combustion section.
  • the mixture is directed through a turbine section, where the mixture expands to provide rotation of a turbine rotor.
  • a flow sleeve is provided to direct the compressed air to the combustion section.
  • fuel may be injected at many points to facilitate premixing of air and fuel.
  • the premixing process provides a high degree of flexibility during engine tuning and is an important component for engine emissions and dynamics.
  • the fuel injection is arranged around the flow sleeve of the gas turbine and injects fuel, through holes on the inner periphery, into the incoming compressed air.
  • the arrangement is as shown in the FIG 1 , which illustrates an embodiment of the state of the art.
  • the fuel injection 6 is attached to the flow sleeve 2 of the gas turbine.
  • the fuel injection 6 includes a plurality of holes 5 along in the inner periphery of the fuel injection assembly 6.
  • the fuel injection assembly 6 injects fuel in a radially inward direction.
  • FIG 1 also illustrates the presence of a flange means 4 for supporting the combustion unit 8.
  • the fuel injection assembly is a hollow casing having circumferential holes 5 disposed around the flow sleeve 2, which injects fuel in a radially inwardly direction (towards the combustion unit 8) into the stream of compressed air flowing in a flow direction 3 within the flow sleeve.
  • the fuel is delivered into the air stream through an array of apertures that are formed in the inner periphery of the fuel supply casing.
  • the compressed air which is pre mixed with fuel passes through a perforated mesh into the combustion section, where the fuel-air mixture is ignited. After the combustion, the hot combustion gases flow along the direction 7 within the combustion unit 8.
  • the unmixedness is the extent of non-uniformity of fuel & air mixture at a particular plane in combustion system.
  • the invention solves the object by integrating the fuel injection assembly with the flange means. As the fuel injection assembly no more connected to the flow sleeve of the turbine, the effect of mechanical vibration on the fuel injection assembly is reduce thereby increasing the life of the fuel injection assembly.
  • the gas turbine comprises a combustion unit, a flow sleeve surrounding the combustion unit, wherein the flow sleeve is positioned radially outward from the combustion unit.
  • An annular cavity extends between the flow sleeve and the combustion unit.
  • a fuel injection assembly is disposed circumferentially surrounding the combustion unit.
  • the fuel injection assembly is provided with a hollow fuel supply casing having an outer wall.
  • a plurality of dispensing tube is coupled to the outer wall.
  • the plurality of dispensing tube is adapted to communicate between the hollow fuel supply casing and a space between the combustion unit and the flow sleeve.
  • the plurality of dispensing tube injects fuel in a radially outward direction.
  • the fuel injection assembly is disposed circumferentially surrounding the combustion unit of the gas turbine.
  • the circumferential placement of the fuel injection assembly enables the fuel injection assembly to support the combustion unit 8, thereby functioning as the flange means.
  • the advantage of this embodiment of the invention is that the plurality of dispensing tube injects fuel into the stream of compressed air passing through the passage. This improves the premixing the fuel with the compressed air.
  • the gas turbine comprises a space between the flow sleeve and the fuel injection assembly for directing the compressed air.
  • the fuel injection assembly is adapted to discharge fuel into the compressed air passing through the annular cavity.
  • the gas turbine comprises a fuel supply pipe for providing fuel to the fuel injection assembly.
  • the gas turbine further comprises at least one valve for controlling a fuel input to the fuel injection assembly.
  • the valve can be used to control the amount of fuel delivered to the fuel injection assembly.
  • the plurality of dispensing tubes is detachable from the cavities on the casing wall. This feature of the invention enables a user to change the fuel dispensing tube based on a requirement.
  • the length of the plurality of dispensing tube is adjustable.
  • the length of the plurality of dispensing tube is adjusted to control an unmixedness of a mixture of compressed air and fuel. Further, the length of the plurality of fuel dispensing tube is adjusted to split the fuel between main and the pilot nozzles.
  • an angle of the plurality of dispensing tubes with respect to a surface of the outer wall is also adjustable.
  • the advantage of the flexibility in the positioning of the dispensing tubes enables in maintaining a required level of unmixedness.
  • FIG 1 illustrates a gas turbine with a flow sleeve and a fuel injection assembly in accordance with a state of the art.
  • the gas turbine comprises a flow sleeve 2, which directs a stream of compressed air into the combustion unit 8.
  • the flow sleeve is an annular structure surrounding the combustion unit.
  • the flow sleeve is disposed at a radial distance from the combustion unit 8, thereby forming an annular cavity.
  • a fuel injection assembly 6 is integrated with the flow sleeve 2, which injects fuel into the stream of compressed air flowing through the flow sleeve 2.
  • the gas turbine further includes a flange means 4 for supporting the combustion unit 8. The aforementioned arrangement of the fuel injection assembly 6 results in excessive wear and tear of the fuel injection assembly due to mechanical vibrations.
  • FIG 2 illustrates a perspective view of a combustion section of the gas turbine.
  • the gas turbine comprises a combustion unit 8, a flow sleeve 2 surrounding the combustion unit, wherein the flow sleeve 2 is disposed at a radial distance from the combustion unit 8.
  • an annular cavity extends between the flow sleeve 2 and the combustion unit 8.
  • the gas turbine as shown in FIG 2 , comprises a fuel injection assembly integrated with the flange ring 4 (shown in FIG 1 ), which circumferentially surrounds the combustion unit 8.
  • the fuel injection unit also supports the combustion unit 8 within the flow sleeve 2.
  • the fuel injection assembly also acts as flange means 4.
  • the fuel injection assembly includes a hollow fuel supply casing having an outer wall 10.
  • the outer wall 10 comprises a plurality of dispensing tube, wherein the plurality of dispensing tube is adapted to dispense a fluid in a radially outward direction.
  • the fuel injection assembly is disposed in an annular cavity between the flow sleeve and a combustion unit of the gas turbine.
  • the plurality of dispensing tube 12 is adapted to communicate between the hollow fuel supply casing and a space between the combustion unit 8 and the flow sleeve 2.
  • the dispensing tube 12 injects fuel into a stream of compressed air flowing in a direction 3 into the combustion unit 8.
  • the stream of compressed air and fuel mixture is directed, after being blocked by a cover plate, into the combustion unit 8 through a perforated mesh positioned towards a posterior end of the flow sleeve 2. Thereafter, the air and fuel mixture is ignited in the combustion unit 8.
  • the fuel supply casing is circular in structure and surrounds the combustion unit circumferentially.
  • FIG 3 illustrates another perspective view of the fuel injection assembly, without the flow sleeve, in accordance with the invention.
  • FIG 3 shows the upper surface 20 of the outer wall 10 of the fuel injection assembly.
  • the fuel supply casings may be having other polygonal structures like a pentagon, hexagon, octagon and the like.
  • the fuel supply casing can have a cross section such a circle, a square, a rectangle and the like.
  • the fuel supply casing has an outer wall 10.
  • the outer casing may be firmly attached to an inner strip of the same material to constitute the fuel supply casing.
  • the outer wall 10 may accommodate one or more dispensing tubes such as dispensing tube 12, for injecting fuel into the annular cavity.
  • the outer wall 10 includes a plurality of cavities along the circumference to accommodate the dispensing tubes 12.
  • the fuel supply casing has 36 cavities equally spaced from one another. The cavities have a diameter in the range of 2-3 mm. The size of the holes is adjusted based on a pressure drop observed in fuel supply pipe in order to ensure adequate dispensing of the fuel.
  • the fuel supply casing and the dispensing tubes may be casted as a single metallic unit and fitted on to the combustion unit.
  • the fuel supply casing is hollow and is adapted to supply fuel to one or more dispensing tubes 12.
  • a fuel supply pipe (not shown in figures) of the gas turbine may be connected to the fuel supply casing. The fuel supply pipe may supply fuel to be dispensed in the stream of compressed air flowing through the annular cavity.
  • FIG 4 illustrates a front view of the gas turbine with the fuel injection assembly in accordance with the invention.
  • the fuel injection assembly circumferentially surrounds the combustion unit, as illustrated in FIG 4 .
  • the combustion unit includes a plurality of main burners 14 and a pilot burner 16.
  • the outer wall 10 of the fuel injection assembly is adapted to supply fuel to the plurality of dispensing tube 12, which sprays the fuel into the cavity between the combustion unit 8 and the flow sleeve 2 (not shown in FIG 4 ).
  • the compressed air, premixed with fuel is supplied to the main and pilot burners for facilitating the combustion.
  • FIG 5 illustrates a top view of a cross-section of the gas turbine combustion system with the fuel injection assembly in accordance with the invention.
  • FIG 5 clearly illustrates the annular cavity 18, inside the outer wall 10 of the fuel injection assembly.
  • the cross section of the annular cavity is rectangular.
  • the annular cavity can have other cross sections such as, circular, triangular and other polygons based on the requirement.
  • the fuel supply casing is connected with a fuel supply pipe for providing fuel to the fuel injection assembly. The fuel is then delivered into the compressed air passing through the flow sleeve 2, thereby premixing fuel with compressed air.
  • FIG 6 illustrates a longitudinal cross-sectional view of the fuel injection assembly in accordance with the invention.
  • the outer casing wall 10 of the fuel injection assembly includes the hollow cavity 18 in order to provide fuel the dispensing tube 12.
  • the dispensing tube 12 has a tube like structure for dispensing the fuel.
  • the dispensing tube may be one or more of, but is not limited to, jet nozzle and a spray nozzle. Further, the dispensing tube may be one or more of, a cone nozzle, a bell nozzle and a spike nozzle.
  • the angle of the dispensing tubes with respect to the surface of the outer casing wall may also be changed for achieving a desired unmixedness of the fuel and compressed air.
  • dispensing tubes such as dispensing tube 12 are detachable from the outer casing 10 of the fuel injection assembly.
  • a user can select an appropriate length of the dispensing tube for achieving a right measure of unmixedness of the fuel-air mixture.
  • the unmixedness is the extent of non-uniformity of fuel and air mixture at a particular location in the flow sleeve.
  • the length of the dispensing tube 12 may also be chosen such that the fuel is dispensed in a region outside a recirculation zone.
  • the recirculation zone is a region where the there is an accumulation of air and fuel mixture. When the air and fuel mixture in the recirculation zone starts flowing suddenly, it results in a flashback.
  • the flashback is reduced by creating Computer Aided analysis of the fluid motion within the annular cavity where the fuel is injected.
  • the fuel injection assembly is fixed to the gas turbine combustion section by welding techniques.
  • the welding techniques may include, for example, laser welding and electron beam welding.
  • FIG 7 illustrates an exemplary welding scheme for affixing the fuel injection assembly to the gas turbine combustion section.
  • the weld joints such as weld joints 17, are shifted away from the combustion unit 8.
  • Another weld joint coupling the fuel supply pipe and the fuel supply casing is moved away from the surface of the outer wall 10, towards a cover plate 13. Moving the weld joints away from the surface of the combustion unit reduces the mechanical and thermal stress acting on the weld joints thereby increasing the life of the weld joint.
  • the components of the combustion section of the gas turbine may be fabricated so as to enable the joints to be welded as shown in FIG 7 .
  • the direction of flow 21 indicates the direction of flow of compressed air within the flow sleeve (not shown in the figure).
  • direction of flow 23 indicates the direction in which hot gases originating from the combustion unit 8 is adapted to flow.
  • the arrangement of the fuel injection assembly as disclosed hereinbefore, has improved resistance towards mechanical vibrations and thermal stress. Therefore, the fuel injection assembly has improved durability and performance characteristics. Further, the positioning of the fuel injection assembly is towards a cover plate of the gas turbine, which renders the fuel injection assembly less prone to cracks and mechanical stress. Further, the fuel injection assembly is flexible in construction and can be adapted to deliver the fuel into a stream of compressed air so as to maintain an optimum unmixedness.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
EP14170275.3A 2014-05-28 2014-05-28 Ensemble d'injection de combustible pour une turbine à gaz Withdrawn EP2949999A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14170275.3A EP2949999A1 (fr) 2014-05-28 2014-05-28 Ensemble d'injection de combustible pour une turbine à gaz
PCT/EP2015/059062 WO2015180909A1 (fr) 2014-05-28 2015-04-27 Ensemble d'injection de carburant pour turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14170275.3A EP2949999A1 (fr) 2014-05-28 2014-05-28 Ensemble d'injection de combustible pour une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2949999A1 true EP2949999A1 (fr) 2015-12-02

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EP14170275.3A Withdrawn EP2949999A1 (fr) 2014-05-28 2014-05-28 Ensemble d'injection de combustible pour une turbine à gaz

Country Status (2)

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EP (1) EP2949999A1 (fr)
WO (1) WO2015180909A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109099461A (zh) * 2018-08-03 2018-12-28 新奥能源动力科技（上海）有限公司 燃烧室的头部装置、燃烧室及燃气轮机
CN109185923A (zh) * 2018-08-03 2019-01-11 新奥能源动力科技（上海）有限公司 一种燃烧室头部装置、燃烧室及燃气轮机
CN109185924A (zh) * 2018-08-03 2019-01-11 新奥能源动力科技（上海）有限公司 燃烧室的头部装置、燃烧室及燃气轮机

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US20100018208A1 (en) * 2008-07-28 2010-01-28 Siemens Power Generation, Inc. Turbine engine flow sleeve
US8281596B1 (en) * 2011-05-16 2012-10-09 General Electric Company Combustor assembly for a turbomachine
US20130180261A1 (en) * 2012-01-13 2013-07-18 General Electric Company Combustor and method for reducing thermal stresses in a combustor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US20100018208A1 (en) * 2008-07-28 2010-01-28 Siemens Power Generation, Inc. Turbine engine flow sleeve
US8281596B1 (en) * 2011-05-16 2012-10-09 General Electric Company Combustor assembly for a turbomachine
US20130180261A1 (en) * 2012-01-13 2013-07-18 General Electric Company Combustor and method for reducing thermal stresses in a combustor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109099461A (zh) * 2018-08-03 2018-12-28 新奥能源动力科技（上海）有限公司 燃烧室的头部装置、燃烧室及燃气轮机
CN109185923A (zh) * 2018-08-03 2019-01-11 新奥能源动力科技（上海）有限公司 一种燃烧室头部装置、燃烧室及燃气轮机
CN109185924A (zh) * 2018-08-03 2019-01-11 新奥能源动力科技（上海）有限公司 燃烧室的头部装置、燃烧室及燃气轮机
CN109099461B (zh) * 2018-08-03 2023-08-15 新奥能源动力科技（上海）有限公司 燃烧室的头部装置、燃烧室及燃气轮机
CN109185923B (zh) * 2018-08-03 2023-09-12 新奥能源动力科技（上海）有限公司 一种燃烧室头部装置、燃烧室及燃气轮机
CN109185924B (zh) * 2018-08-03 2023-09-12 新奥能源动力科技（上海）有限公司 燃烧室的头部装置、燃烧室及燃气轮机

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Publication number Publication date
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