EP3221642B1 - Lance injector for injecting fuel into a combustion chamber of a gas turbine - Google Patents

Lance injector for injecting fuel into a combustion chamber of a gas turbine Download PDF

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Publication number
EP3221642B1
EP3221642B1 EP15823002.9A EP15823002A EP3221642B1 EP 3221642 B1 EP3221642 B1 EP 3221642B1 EP 15823002 A EP15823002 A EP 15823002A EP 3221642 B1 EP3221642 B1 EP 3221642B1
Authority
EP
European Patent Office
Prior art keywords
tubular body
sealing rings
injector according
foregoing
injector
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.)
Active
Application number
EP15823002.9A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3221642A1 (en
Inventor
Marco Alecci
Pierpaolo Pastorino
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.)
Ansaldo Energia SpA
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Ansaldo Energia SpA
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Publication date
Application filed by Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP3221642A1 publication Critical patent/EP3221642A1/en
Application granted granted Critical
Publication of EP3221642B1 publication Critical patent/EP3221642B1/en
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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines

Definitions

  • the present invention relates to a lance injector for injecting fuel into a combustion chamber of a gas turbine.
  • gas turbines especially if used in electric power production plants, may be fed with different types of fuel.
  • gaseous fuels of different nature and characteristics natural gas, syngas
  • fuel oils like diesel fuel can be injected into gas turbines.
  • gas turbines are equipped with burners comprising injectors, normally of the lance type, specifically designed for injecting a controlled flow of fuel.
  • Lance injectors generally comprise a plurality of coaxial tubular bodies, at one end of which a terminal equipped with a nozzle is fitted.
  • the tubular bodies define between them at least one delivery line between an inlet and the nozzle, and a return line allowing the recovery of the excess fuel supplied to the nozzle.
  • a line for feeding cooling water or air can also be provided.
  • a common problem in lance injectors is due to the different thermal expansion of the components in use, with particular reference to the tubular bodies.
  • the thermal stress is in fact remarkable because of the high temperatures in the combustion chamber (i.e. close to the terminal and the nozzle).
  • the consequent thermal expansion is not only important, but also remarkably different from one component to another, due to the differences in geometry and in the exposure to high temperatures in the combustion chamber and to the cooling air introduced from outside or to the process fluid.
  • EP 1 918 548 A2 discloses a lance injector for a combustion chamber of a gas turbine comprising: a first and a second tubular body; a nozzle connected to respective first ends of the first tubular body and of the second tubular body; a guiding bushing fitted onto the first tubular body so as to allow the first tubular body to axially slide with respect to the second tubular body on account of thermal expansion and contraction; and sealing members between the first tubular body and the guiding bushing.
  • the sealing members are defined by sealing rings and the first tubular body and the guiding bushing are separated by an annular gap except at the sealing rings.
  • the object of the present invention is therefore to provide a lance injector for injecting fuel into a combustion chamber of a gas turbine that can overcome the described limitations.
  • the present invention provides a lance injector for injecting fuel into a combustion chamber of a gas turbine according to claim 1.
  • the reference number 1 indicates in its entirety a burner unit for injecting fuel, in particular gas, into a combustion chamber 2 of a gas turbine, only partially shown.
  • the burner unit 1 extends along an axis A and comprises a peripheral gas main burner 3, a central gas pilot burner 4 and a lance injector 5 for injecting fuel oil into the combustion chamber 2.
  • the main burner 3 is of the premixing type, is arranged around the pilot burner 4 and is provided with a swirler 7, which comprises a plurality of blades 10, defining respective flow channels for conveying, oblique with respect to the axis A, a flow of combustion air and fuel gas towards the combustion chamber 2.
  • the fuel gas is supplied through nozzles 11 arranged on the blades 10.
  • the pilot burner 4 is coaxial to the main burner 3 and is provided with an axial swirler 8, which comprises a plurality of blades 12, defining respective flow channels for conveying, substantially along the axis A, a further flow of combustion air towards the combustion chamber 2.
  • the lance injector 5 extends along the axis A and has one end inserted in the pilot burner 4.
  • the lance injector 5 comprises an inner tubular body 15, an intermediate tubular body 16, an outer tubular body 17, a terminal element 18 and a nozzle 20. Furthermore, the lance injector 5 is provided with flanges 21, 22.
  • the inner tubular body 15, the intermediate tubular body 16 and the outer tubular body 17 concentrically extend along the axis A and define a first fluid line 23, a second fluid line 24 and a third fluid line 25.
  • the first fluid line 23 is defined in a gap between the inner tubular body 15 and the intermediate tubular body 16 and allows the alternating supply of a flow of cooling air along the lance injector 5 or of a flow of fuel oil to the nozzle 20, thus working as a delivery line.
  • the second fluid line 24 is defined in the inner tubular body 15 and allows to recover the excess fuel oil fed to the nozzle 20 and to reintroduce it in a manifold (not shown), thus working as a return line.
  • the third fluid line 25 is defined in a gap between the intermediate tubular body 16 and the outer tubular body 17 and may supply a different type of fuel, for example gas, or an inert fluid like water.
  • the nozzle 20 is coupled to the inner tubular body 15, to the intermediate tubular body 16 and to the outer tubular body 17 with the aid of the terminal element 18.
  • the nozzle 20 is mounted on the ends 15a, 16a of the inner tubular body 15 and of the intermediate tubular body 16 by a threaded or hot-keyed coupling.
  • the terminal element 18 is fitted on one end 17a of the outer tubular body 17 and coupled to it by a threaded coupling or, where appropriate, by a hot-keyed coupling.
  • the nozzle 20 and the terminal element 18 are coupled by interference, and the nozzle 20 axially protrudes outwards with respect to the terminal element 18.
  • the flange 21 extends around the axis A and has a through axial cavity 29 and radial fluid passages 27, 28 ( Figure 1 ), respectively communicating with the first fluid line 23 and the third fluid line 25.
  • the axial cavity 29 houses one end 15b of the inner tubular body 15, which extends beyond the edge of the intermediate tubular body 16 and is inserted in a guiding bushing 30.
  • the guiding bushing 30 is tightened between the flange 21 and the flange 22 and is fitted onto the inner tubular body 15.
  • the guiding bushing 30 therefore supports the inner tubular body 15 in a position centred on the axis A and allows its axial sliding, in particular as a result of the thermal expansion and of the subsequent contraction of the portion nearest to the combustion chamber 2. Furthermore, the guiding bushing 30 ensures the fluid-tight seal against the side wall of the inner tubular body 15 to prevent a leakage of fuel oil, as explained in more detail below.
  • the flange 22 is coupled to the flange 21 and has an axial cavity 31, which defines a contrast seat and houses a contrast elastic device 32 co-operating with the inner tubular body 15 to absorb and recover the effects of thermal expansion and contraction.
  • the device 32 comprises an elastic contrast pushing member 33 coupled to the end 15b of the inner tubular body 15 and a stack of belleville washers 35 co-operating with the pushing member 33 and the contrast seat defined in the axial cavity 31 of the flange 22.
  • the pushing member 33 is axially hollow and, in one embodiment, comprises a tubular body 33a, abutting the end 15b of the inner tubular body 15 and provided with a plate 33b for its coupling to the belleville washers 35, which are housed in the contrast seat of the axial cavity 31.
  • the pushing member 33 puts in fluid communication the inner tubular body 15 with a supply duct (not shown).
  • the sealing members 37 include at least two sealing rings 38 that, in one embodiment, are integral with the inner tubular body 15.
  • the sealing rings 38 define the only points of contact between the inner tubular body 15 and the guiding bushing 30.
  • the inner tubular body 15 and the guiding bushing 30 are then separated by an annular gap 40 except at the sealing rings 38.
  • the sealing rings 38 have a radially rounded outer profile, for example having a circular section with a radius R1 comprised between 0.5 mm and 4 mm, as shown in Figure 3 . In this way, the contact between the inner tubular body 15 and the guiding bushing 30 is limited to the crests of the sealing rings 38, but is sufficient to prevent the leakage of fluid.
  • the sealing rings 38 radially protrude from the side surface of the inner tubular body 15 and their radial thickness T is comprised between 10% and 25% of a radius R2 of the side surface of the inner tubular body 15.
  • the radial thickness T of the sealing rings 38 is comprised between 0.5 mm and 1.5 mm.
  • the sealing rings 38 are mutually spaced by a distance D comprised between 2 mm and 5 mm.
  • sealing members 137 in particular comprising at least two sealing rings 138, are present between the inner tubular body and the guiding bushing, here respectively indicated by 115 and 130.
  • the inner tubular body 115 and the guiding bushing 130 are then separated by an annular gap 140 except at the sealing rings 138.
  • the sealing rings 138 are integral with the guiding bushing 130 and radially project towards the inner tubular body 115.
  • the sealing rings 138 have a radially rounded inner profile, so that the contact between the inner tubular body 115 and the guiding bushing 130 is limited to the crests of the sealing rings 138, but is sufficient to prevent the leakage of fluid.
  • the thermal stresses occurring during normal operation may cause serious problems in the lance injectors of known type.
  • the result is a loss of efficiency of the machine, an imperfect control of combustion conditions and emissions and, in serious cases, the machine stop.
  • the described tight coupling between the inner tubular body and the guiding bushing.
  • the described coupling limits the points of contact between the inner tubular body and the guiding bushing to the crests of the sealing rings, while for the rest, the inner tubular body and the guiding bushing are separated by an annular gap.
  • the contact limited to the crests of the sealing rings and the greater available clearance allow some misalignment of the end of the inner tubular body with respect to the guiding bushing without compromising the sealing function, and therefore avoiding any leakage.
  • the described solution thus favours the relative axial sliding between the inner tubular body and the intermediate tubular body and avoids any jamming. Consequently, the stress on the element terminal and on the nozzle due to the thermal expansion is reduced and the possible damage is significantly limited, especially with regard to the fitting loss.
  • the fluid lines can otherwise be used for injecting one or more liquid or gaseous fuels or a cooling fluid, for example air or water.
  • one of the tubular bodies in particular one between the intermediate tubular body and the outer tubular body, may be missing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15823002.9A 2014-11-21 2015-11-20 Lance injector for injecting fuel into a combustion chamber of a gas turbine Active EP3221642B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITMI20142019 2014-11-21
PCT/IB2015/059018 WO2016079720A1 (en) 2014-11-21 2015-11-20 Lance injector for injecting fuel into a combustion chamber of a gas turbine

Publications (2)

Publication Number Publication Date
EP3221642A1 EP3221642A1 (en) 2017-09-27
EP3221642B1 true EP3221642B1 (en) 2018-09-05

Family

ID=52463031

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15823002.9A Active EP3221642B1 (en) 2014-11-21 2015-11-20 Lance injector for injecting fuel into a combustion chamber of a gas turbine

Country Status (4)

Country Link
EP (1) EP3221642B1 (ja)
CN (1) CN107110504B (ja)
RU (1) RU2693202C2 (ja)
WO (1) WO2016079720A1 (ja)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114543118B (zh) * 2022-02-21 2023-04-25 中国航发贵阳发动机设计研究所 离心式起动喷嘴

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB648699A (en) * 1947-10-17 1951-01-10 Arthur Holmes Fletcher Improvements in or relating to gas-turbine engine fuel systems and liquid fuel injectors therefor
US6357222B1 (en) * 2000-04-07 2002-03-19 General Electric Company Method and apparatus for reducing thermal stresses within turbine engines
US7703287B2 (en) * 2006-10-31 2010-04-27 Delavan Inc Dynamic sealing assembly to accommodate differential thermal growth of fuel injector components
RU2375597C2 (ru) * 2008-02-12 2009-12-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Топливный коллектор камеры сгорания газотурбинного двигателя
US8443608B2 (en) * 2008-02-26 2013-05-21 Delavan Inc Feed arm for a multiple circuit fuel injector
EP2270398A1 (de) * 2009-06-30 2011-01-05 Siemens Aktiengesellschaft Brenner, insbesondere für Gasturbinen
US20130180261A1 (en) * 2012-01-13 2013-07-18 General Electric Company Combustor and method for reducing thermal stresses in a combustor

Also Published As

Publication number Publication date
RU2017121565A (ru) 2018-12-21
CN107110504A (zh) 2017-08-29
RU2693202C2 (ru) 2019-07-01
CN107110504B (zh) 2019-11-26
RU2017121565A3 (ja) 2019-05-21
WO2016079720A1 (en) 2016-05-26
EP3221642A1 (en) 2017-09-27

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