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EP3657072A1 - Lanze für einen brenner und verfahren zum nachrüsten einer lanze - Google Patents

Lanze für einen brenner und verfahren zum nachrüsten einer lanze Download PDF

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Publication number
EP3657072A1
EP3657072A1 EP18208164.6A EP18208164A EP3657072A1 EP 3657072 A1 EP3657072 A1 EP 3657072A1 EP 18208164 A EP18208164 A EP 18208164A EP 3657072 A1 EP3657072 A1 EP 3657072A1
Authority
EP
European Patent Office
Prior art keywords
duct
lance
sleeve
pin
nozzle
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.)
Granted
Application number
EP18208164.6A
Other languages
English (en)
French (fr)
Other versions
EP3657072B1 (de
Inventor
Paul Marlow
Fabien Fleuriot
Ark Jan TIJSSEN
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 Switzerland AG
Thomassen Energy BV
Original Assignee
Ansaldo Energia Switzerland AG
Ansaldo Thomassen BV
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 Ansaldo Energia Switzerland AG, Ansaldo Thomassen BV filed Critical Ansaldo Energia Switzerland AG
Priority to EP18208164.6A priority Critical patent/EP3657072B1/de
Publication of EP3657072A1 publication Critical patent/EP3657072A1/de
Application granted granted Critical
Publication of EP3657072B1 publication Critical patent/EP3657072B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/48—Nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors
    • 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

Definitions

  • the present invention relates to lance for a burner and a method for retrofitting a lance.
  • Burners in particular those of the reheat type, can comprise a body, through which a hot gas flow can flow through, and a lance protruding into the body for injecting fuel into the hot gas flow.
  • the lance can have a duct for a first fuel and nozzles for injecting it.
  • the lance can further comprise a sleeve encircling the duct and provided with nozzles as well; the nozzles of the sleeve are aligned with the nozzles of the duct.
  • the lance can further comprise an inner duct, provided inside of the duct for injecting a second fuel, typically different from the fuel passing through the duct, via nozzles.
  • the nozzles of the inner duct are also aligned with the nozzles of the duct and nozzles of the sleeve.
  • fuel is supplied via the inner duct or via the duct and at the same time air is supplied via the sleeve, such that fuel (from the inner duct or from the duct) is injected together with shielding air (via the sleeve).
  • An aspect of the invention includes providing a lance and a method by which the alignment of the nozzles through which fuel and shielding air is injected is improved compared to existing lances.
  • these show a burner, preferably of a gas turbine.
  • the gas turbine can comprise, in sequence, a compressor, a first combustion chamber, a second combustion chamber and a turbine. Between the first and the second combustion chambers a high pressure turbine and/or a mixer for supplying diluting air can be provided.
  • air is compressed at the compressor and is supplied into the first combustion chamber, where fuel is supplied and combusted with the compressed air, generating hot gas.
  • the hot gas can be partially expanded in a high pressure turbine and/or can be diluted with air in a mixer (according to the scheme of the gas turbine) and is then supplied into the second combustion chamber.
  • a mixer accordinging to the scheme of the gas turbine
  • At the second combustion chamber further fuel is injected and combusted with the residual oxygen contained in the hot gas after the combustion in the first combustion chamber; the hot gas emerging from the second combustion chamber is expanded in the turbine.
  • the second combustion chamber is schematically shown in figure 1 and it is identified with reference 1.
  • the second combustion chamber 1 comprises a burner 2 and a combustion area 3.
  • the burner 2 has a tubular body 4 with vortex generators 5 at its entrance to increase vorticity of the hot gas, and a lance 6 for injecting fuel.
  • Reference 7 in figure 1 identifies the flame.
  • the lance 6 has a duct 10 for carrying a fuel 11, typically gas, and one or preferably more than one nozzles 12, for injecting the fuel 11.
  • the lance 6 also has a sleeve 13, provided around the duct 10, preferably concentrically; the sleeve 13 defines a channel between the duct 10 and the sleeve 13 and has one or preferably more than one nozzles 14.
  • the sleeve 13 carries air 15, that is injected through the nozzles 14 as shielding air.
  • the nozzles 12 of the duct 10 and the nozzle 14 of the sleeve 13 are aligned, e.g. their axes substantially overlap.
  • the lance 6 can also have an inner duct 17 inside the duct 10; preferably the inner duct 17 is concentrically provided in the duct 10.
  • the inner duct 17 is provided with one or more than one nozzles 18, which are aligned with the nozzles 12 of the duct 10 and nozzles 14 of the sleeve 13, e.g. the axes of the nozzles 12, 14, 18 substantially overlap.
  • the terminal parts of the duct 10 and inner duct 17 are connected together.
  • a first channel for carrying a fuel 19, which can be same as or different from the fuel 11, is defined by the inner duct 17.
  • the sleeve 13 has a terminal portion 20 closed by a cap 21 having a pin 22; correspondingly, the duct 10 has an end with a hole 23.
  • the pin 22 is form fittingly inserted into the hole 23. Therefore the pin 22 prevents radial movements of the sleeve 13 with respect to the duct 10 as indicated by the arrow RM, but it allows axial sliding of the pin 22 into the hole 23, in the direction of arrow AM, caused for example by differential temperatures among the different parts of the lance 6 during operation.
  • the pin 22 since the pin 22 is provided in a cap that is connected to the terminal part of the sleeve, it can be manufactured with very small tolerances; likewise the hole 23 can be realised with very small tolerances, such that the coupling of the pin 22 into the hole 23 defines a form fitting coupling.
  • the cap 21 has a hub part 25 and a concave part 26 extending from the hub part 25; the pin 22 extends from the hub part 25 and is housed in the concave part 26.
  • the concave part 26 has a cap border 27 defining a terminal section for the cap 21; the pin end 28 is closer to the cap border 27 than to the hub part 25.
  • the pin 22 has a length L that is at least as large as its diameter D.
  • Figure 3 shows a lance similar to the one of figure 2 .
  • the lance of figure 3 has a bush 29 between the pin 22 and the hole 23.
  • a lance according to this embodiment can be the result of a repair operation, in which damaged material around the hole 23 is removed and the bush 29 is provided to match the new bigger diameter of the hole 23 with the diameter of the pin 22.
  • the lance also has a centering arrangement, which is provided between the duct 10 and the sleeve 13, for fixing the radial position of the sleeve 13 with respect to the duct 10.
  • the centering arrangement is provided at a side of the lance 6 opposite the one with the cap 21 with respect to the aligned nozzles 12, 14, 18.
  • the lance 6 further has a stop arrangement for fixing the axial position of the sleeve 13 with respect to the duct 10; this stop arrangement is also provided between the duct 10 and the sleeve 13.
  • the centering arrangement and the stop arrangement are defined by a same system 30, such as a bayonet system.
  • a further centering arrangement 31 is also provided between the duct 10 and the inner duct 17.
  • Fuel 11 gas fuel
  • fuel 19 liquid fuel
  • shielding air 15 is injected via the nozzles 14.
  • the present invention also refers to a method for retrofitting a lance.
  • the lance before retrofitting ( figure 5 ), comprises
  • the method comprises
  • the method can also comprises providing a bush 29 between the hole 23 and the pin 22 ( figure 11 ); in this case the provision of the hole can also encompass the provision of an enlargement of an already existing hole, e.g. a hole is already provided but it is made bigger, e.g. to remove damaged material.
  • This particular embodiment of the method is particularly relevant for repair of damaged lances.
  • figures 5 through 8 show the steps of a method for retrofitting a lance that originally is not provided with pin 22 and hole 23
  • figures 9 through 12 show the steps of a method for retrofitting a lance that is originally already provided with pin 22 and hole 23.
  • the bush 29 is preferably fixed only to the hole 23 and the pin 22 is form fittingly inserted into the bush 29.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP18208164.6A 2018-11-23 2018-11-23 Lanze für einen brenner und verfahren zum nachrüsten einer lanze Active EP3657072B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP18208164.6A EP3657072B1 (de) 2018-11-23 2018-11-23 Lanze für einen brenner und verfahren zum nachrüsten einer lanze

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18208164.6A EP3657072B1 (de) 2018-11-23 2018-11-23 Lanze für einen brenner und verfahren zum nachrüsten einer lanze

Publications (2)

Publication Number Publication Date
EP3657072A1 true EP3657072A1 (de) 2020-05-27
EP3657072B1 EP3657072B1 (de) 2021-08-11

Family

ID=64456905

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18208164.6A Active EP3657072B1 (de) 2018-11-23 2018-11-23 Lanze für einen brenner und verfahren zum nachrüsten einer lanze

Country Status (1)

Country Link
EP (1) EP3657072B1 (de)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070207425A1 (en) * 2004-08-23 2007-09-06 Alstom Technology Ltd. Hybrid burner lance
EP2199674A1 (de) * 2008-12-19 2010-06-23 ALSTOM Technology Ltd Brenner einer Gasturbine
EP2388520A1 (de) * 2010-05-20 2011-11-23 Alstom Technology Ltd Lanze eines Gasturbinenbrenners

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070207425A1 (en) * 2004-08-23 2007-09-06 Alstom Technology Ltd. Hybrid burner lance
EP2199674A1 (de) * 2008-12-19 2010-06-23 ALSTOM Technology Ltd Brenner einer Gasturbine
EP2388520A1 (de) * 2010-05-20 2011-11-23 Alstom Technology Ltd Lanze eines Gasturbinenbrenners

Also Published As

Publication number Publication date
EP3657072B1 (de) 2021-08-11

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