EP1284392A1 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

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Publication number
EP1284392A1
EP1284392A1 EP01119561A EP01119561A EP1284392A1 EP 1284392 A1 EP1284392 A1 EP 1284392A1 EP 01119561 A EP01119561 A EP 01119561A EP 01119561 A EP01119561 A EP 01119561A EP 1284392 A1 EP1284392 A1 EP 1284392A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
combustion chambers
chamber arrangement
individual
arrangement according
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Withdrawn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
EP01119561A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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 EP01119561A priority Critical patent/EP1284392A1/fr
Publication of EP1284392A1 publication Critical patent/EP1284392A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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

Definitions

  • the invention relates to a combustion chamber arrangement for gas turbines with a variety of in one, in one Turbine space crossing annular gap opening an input section and individual combustion chambers having a transition area, the input section of the individual combustion chambers burners are connected upstream.
  • the invention relates also a gas turbine with an inventive structure Combustor assembly.
  • combustion chamber assembly used for gas turbines.
  • the individual combustion chambers are in two parts constructed, they have an entrance section and a transition area on.
  • the entrance section which is directly the burner downstream is used to initiate combustion and is constructed from the point of view of combustion technology.
  • the input section usually has one circular cylindrical shape.
  • To the entrance section a transition area closes downstream in the flow direction in which the circular cylindrical shape of the Input section of the individual combustion chambers to a circular ring segment is faded out, which eventually turns into one Annular gap opens.
  • the annular gap has a transition to one of the combustion chamber arrangements downstream turbine chamber, in which the expanding hot gases on an array from guide vanes and blades. Transfer there the hot gases have kinetic energy on the blades and carry the turbine shaft over it.
  • Such a structure of the combustion chamber arrangement has proven to be proven to be advantageous because it combusts the combustion of the Annulus decoupled segment by segment and thus controlled in a targeted manner can be. It can also be divided combustion into individual circular ring segments leads to noise noticeably reduce the turbine.
  • the object of the invention is to create a combustion chamber arrangement in which a reduced need for open cooling and thus a lower loss of cold gas required for the combustion is possible.
  • the invention proposes that input sections and transition areas of the individual combustion chambers form units which are firmly connected to one another and which are suspended in the gas turbine so as to be movable relative to the burner and / or the annular gap.
  • an axial sliding sealing plate between the input section and Burner may be arranged. Because of an axial movement limited relative displacement between the input section and burner are the leaks from there the cold gas flow into the hot gas flow less, and part The cold gas passing through at this point can be due to close to the burner can still be used for combustion. The effective loss of cold gas, that of combustion is not supplied, is therefore significantly lower than in the Solutions known from the prior art.
  • connection between entrance sections and transition areas can according to an advantageous development the invention can be created by a weld that Individual combustion chambers can, however, as a whole be made in one piece.
  • connection between the entrance sections and the transition areas of the individual combustion chambers conceivable that the high thermal occurring in the combustion chamber arrangement Withstand loads.
  • the individual combustion chambers are circular cylindrical, and the transition areas are shaped so that they are one Circle diameter continuously to an annulus sector crossfade. So the entrance section has one for an efficient one Combustion favorable form and in the transition areas the gas flow is essentially free of pressure loss a circular cross-sectional area in a circular ring segment crossfades, which ring segments finally in open an annular gap as a transition into the turbine space. So an even, circular ring enters the turbine chamber Gas flow and forms a good basis for an efficient Use of the kinetic contained in the hot gas stream Energy.
  • the invention relates to the described combustion chamber arrangement also a gas turbine, which one described above Combustion chamber assembly contains.
  • Figure 1 shows a section of a section from a gas turbine with one constructed according to the invention Combustion chamber arrangement 1.
  • the combustion chamber arrangement 1 settles from a plurality of individual combustion chambers 2 (one shown) together.
  • Each of the individual combustion chambers 2 is divided into an entrance section 3 and a transition area 4th entrance section 3 and transition area 4 are along a Connection area 5 firmly connected.
  • a burner 6 is placed on the input section 3, which is fixed to an outer shell of the turbine housing is connected and the input section 3 of the single combustion chamber 2 axially movable on sliding surfaces 7.
  • the input section 3 has in the end region on the burner side the individual combustion chamber 2 an axial sealing plate 8 on Sealing the burner 6 - inlet section 3 connection.
  • a turbine chamber 9 Fluidically downstream of the transition area 4 a turbine chamber 9, in which the combustion in the Single combustion chamber 2 generated hot gas flow through an annular gap 10, in which the transition areas 4 of the individual combustion chambers 2 open, passes.
  • the transition areas 4 of the individual combustion chambers 2 are via articulated connections 11 with a Guide vane carrier 12 of the turbine chamber 9 connected. about this connection can be angled to the axial direction of the Individual combustion chambers 2 occurring relative movements between the burner 6 fixed to the outer housing and the guide vane carrier 12, on which the transition area 4 is arranged is to be balanced.
  • the articulated attachment 11 of the transition area 4 on the guide vane carrier 12 manages essentially without additional cooling, the axially displaceable fixing of the input section 3 on Burner 6 with the sliding surfaces 7 and the axial sealing plate 8 can be designed so that even with arrangement a suspension is in the cold gas flow and none or only a little additional (open) cooling at this point is required.
  • there is the connection point between burner 6 and inlet section 3 so close to the combustion zone, that cold gas entering there also burned and thus to increase the combustion efficiency and used to reduce nitrogen oxide emissions can.
  • FIG. 2 is a perspective view of a section from the combustion chamber arrangement 1 according to the invention.
  • the individual combustion chambers 2 are also clearly visible here arranged in a ring and at an angle to the machine axis are. Entrance sections are also clearly visible 3 and transition areas 4 of the individual combustion chambers 2 as well as the connection areas 5. Particularly in this illustration The ring-shaped outlet openings are clearly visible 13 of the transition areas 4, from which the Hot gas flow into an annular gap leading to the turbine space transforms.
  • the Input sections 3 of the individual combustion chambers 2 a cylindrical Shape with a circular base.
  • the inventive fixed connection between the input section and transition area of the individual combustion chambers and the movable arrangement of the input section and / or Transition areas of the individual combustion chambers on the respective turbine elements is used to cool the state of the art known two-part designs of the individual combustion chambers in the connection area between the entrance section and Transition area required open cooling air flow saved and is therefore available for combustion. This leads to efficient combustion with reduced emissions of stick oxides.
  • the individual combustion chambers according to the invention compared to those from the prior art known two-part embodiments manufactured cheaper what lowers the overall production cost.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01119561A 2001-08-14 2001-08-14 Chambre de combustion Withdrawn EP1284392A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01119561A EP1284392A1 (fr) 2001-08-14 2001-08-14 Chambre de combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01119561A EP1284392A1 (fr) 2001-08-14 2001-08-14 Chambre de combustion

Publications (1)

Publication Number Publication Date
EP1284392A1 true EP1284392A1 (fr) 2003-02-19

Family

ID=8178326

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01119561A Withdrawn EP1284392A1 (fr) 2001-08-14 2001-08-14 Chambre de combustion

Country Status (1)

Country Link
EP (1) EP1284392A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2351967A4 (fr) * 2008-10-01 2015-08-26 Mitsubishi Hitachi Power Sys Structure de liaison pour chambre de combustion, tuyère terminale de chambre de combustion, procédé de conception de tuyère terminale de chambre de combustion, et turbine à gaz
DE102014204481A1 (de) * 2014-03-11 2015-09-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine
US9335048B2 (en) 2014-03-11 2016-05-10 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1091573A (en) * 1964-06-08 1967-11-22 Lucas Industries Ltd Combustion apparatus for gas turbine engines
US4244178A (en) * 1978-03-20 1981-01-13 General Motors Corporation Porous laminated combustor structure
JPH0893504A (ja) * 1994-09-21 1996-04-09 Kawasaki Heavy Ind Ltd ガスタービン用燃焼器

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1091573A (en) * 1964-06-08 1967-11-22 Lucas Industries Ltd Combustion apparatus for gas turbine engines
US4244178A (en) * 1978-03-20 1981-01-13 General Motors Corporation Porous laminated combustor structure
JPH0893504A (ja) * 1994-09-21 1996-04-09 Kawasaki Heavy Ind Ltd ガスタービン用燃焼器

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1996, no. 08 30 August 1996 (1996-08-30) *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2351967A4 (fr) * 2008-10-01 2015-08-26 Mitsubishi Hitachi Power Sys Structure de liaison pour chambre de combustion, tuyère terminale de chambre de combustion, procédé de conception de tuyère terminale de chambre de combustion, et turbine à gaz
DE102014204481A1 (de) * 2014-03-11 2015-09-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine
US9335048B2 (en) 2014-03-11 2016-05-10 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine
US9506653B2 (en) 2014-03-11 2016-11-29 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine

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