EP2459934A2 - Chambre de combustion de turbine à gaz - Google Patents

Chambre de combustion de turbine à gaz

Info

Publication number
EP2459934A2
EP2459934A2 EP10747801A EP10747801A EP2459934A2 EP 2459934 A2 EP2459934 A2 EP 2459934A2 EP 10747801 A EP10747801 A EP 10747801A EP 10747801 A EP10747801 A EP 10747801A EP 2459934 A2 EP2459934 A2 EP 2459934A2
Authority
EP
European Patent Office
Prior art keywords
gas turbine
housing
perforated plate
combustor according
turbine combustor
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
EP10747801A
Other languages
German (de)
English (en)
Other versions
EP2459934B1 (fr
Inventor
Jaman El Masalme
Emil Aschenbruck
Reiner Brinkmann
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.)
Everllence SE
Original Assignee
MAN Diesel and Turbo SE
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 MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2459934A2 publication Critical patent/EP2459934A2/fr
Application granted granted Critical
Publication of EP2459934B1 publication Critical patent/EP2459934B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R3/002—Wall structures
    • 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
    • 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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a gas turbine combustion chamber having a housing, a flame tube accommodated therein and a perforated plate surrounding this, which is fastened to the housing at a front end, and a gas turbine, in particular a stationary gas turbine, with such a gas turbine combustor.
  • combustion air a fluid, usually called air and therefore generalized hereinafter as combustion air, first compressed to a higher pressure level and burned as a combustion air-fuel mixture in a combustion chamber, before in a turbine enthalpy of the exhaust gas converted into mechanical E- energy is and will be available as net output.
  • the combustion chamber experiences both high pressure and temperature loads due to the pressure level and the combustion. Therefore, it is customary in the prior art to reinforce the housing of the combustion chamber by inner and / or outer stiffening ribs to use high temperature resistant materials and to provide a so-called flame tube in the housing, which limits the combustion zone and thus the housing at least partially against the
  • an impingement cooling of the flame tube is known.
  • a perforated plate surrounding the flame tube is provided. Compressed combustion air hits the flame tube from the outside through openings in the perforated plate and cools it before it is fed through a radial swirl generator to the inside of the flame tube or combustion chamber where it is burned.
  • US 6,134,877 shows a gas turbine combustor having a housing, a flame tube accommodated therein, and a conical cylinder surrounding it, which has in a downstream region openings for impingement cooling of a region of decreasing diameter of the flame tube and to a front end attached to the housing.
  • a folded region By a folded region, an axial compliance of the cylinder is introduced to allow thermal expansion.
  • the cylinder opens with its other front end in the turbine outlet.
  • the object of the present invention is therefore to improve a gas turbine or its combustion chamber.
  • a gas turbine combustion chamber according to the preamble of claim 1 is further developed by its characterizing features.
  • Claim 14 provides a gas turbine with at least one Gasturbinenbrennhunt invention under protection, the dependent claims relate to advantageous developments.
  • the present invention is based on the idea to reduce or replace previously required stiffening ribs of the housing by integrating or integrating the perforated plate as a support structure on both sides into the housing structure and thus increasing the structural rigidity and / or strength of the housing.
  • a gas turbine combustor for this purpose, comprises a housing, a flame tube accommodated therein and a perforated plate which at least partially surrounds the latter and which is fastened to the housing at its two end-side ends.
  • the perforated plate can in particular transmit axial loads between its two front ends and introduce them into the housing, which is thus relieved of load.
  • the perforated plate in addition to the flow guidance and cooling, is also used for transmitting loads of the housing and for this purpose is connected to the housing on both sides, the strength and / or inclination can be increased. be increased without increasing its weight by excessive internal or external ribs.
  • gas turbine combustion chamber is designed as a separate, radially outer combustion chamber whose housing thus forms a one-part or multi-part outer housing against the gas turbine environment.
  • the perforated plate at least in a primary combustion region of the flame tube, has cooling openings, in particular bores and / or slot openings, for impingement cooling of the flame tube.
  • the cooling holes for example, an angular offset of axially adjacent cooling holes, so that the perforated plate has network structure, or axially aligned cooling holes, so that the perforated plate has axially continuous webs, by slits in the axial and / or circumferential direction of the perforated plate and / or a limitation of the number and / or diameter of the cooling openings, the, in particular axial, rigidity and strength of the perforated plate can be adjusted.
  • the housing may have an annular chamber for acting on the perforated plate with combustion air so as to preferably cool this thermally highly stressed axial section of the flame tube.
  • An annular chamber is preferably designed such that the entire supplied combustion air is supplied to the flame tube through cooling openings of the perforated plate and may extend for this purpose in the axial direction preferably substantially in the primary combustion region.
  • the perforated plate can define or define the annular chamber radially from the inside and can extend axially on one or both sides beyond the annular chamber adjacent to it from outside.
  • the annular chamber can be placed on the perforated plate from the outside, which is thus structurally particularly advantageously integrated into the outer housing as part of the outer housing.
  • the perforated plate is permanently fastened to the housing at one or both front ends, in particular welded, glued, caulked and / or riveted thereto. This can cause structural loads be transferred particularly cheap between housing and perforated plate.
  • the perforated plate may form part of the housing.
  • the perforated plate can have one or more sections which delimit a combustion air feed to the outside environment.
  • Such sections may be formed with one section with cooling openings in one or more parts, in particular with each other ur- or reshaped or welded.
  • the housing at least in the region of the perforated plate, be formed largely free of ribs.
  • the gas turbine combustor has a radial swirl generator with a, preferably annular, plate, which may form part of a housing, in particular an outer housing, or may be attached thereto. On the plate, a front end of the perforated plate may be attached.
  • the housing can be advantageously formed thinner walls.
  • one or more corresponding areas of the housing and the perforated plate have substantially the same wall thickness.
  • regions at the same axial height of the combustion chamber are referred to as corresponding regions.
  • the flame tube is axially fixed at its upstream front end to the housing. Due to the connection of the perforated plate on both sides, the larger clearance or the larger thermal expansions can occur in an upstream head region of the combustion chamber, so that it may be advantageous to provide the fixed bearing of a fixedly mounted flame tube there.
  • the perforated plate is formed substantially circular cylindrical, so as to provide a higher structural rigidity or strength available. Further advantages and features emerge from the subclaims and the exemplary embodiments. This shows, partially schematized:
  • Fig. 1 a gas turbine according to the prior art with two external combustion chambers;
  • Fig. 2 a gas turbine combustor according to an embodiment of the present invention in axial or longitudinal section.
  • a gas turbine according to the prior art with two outer combustion chambers shown the housing 100 are reinforced with stiffening ribs 110 and thus complicate the handling by their higher weight handling and the underlying turbine housing on which they are attached, burden.
  • Fig. 2 shows a gas turbine combustor according to an embodiment of the present invention in axial or longitudinal section to replace the combustion chambers shown in Fig. 1.
  • a flame tube 2 In its interior, a flame tube 2 defines a combustion chamber. This is supplied by a radial swirl generator 5, a combustion air-fuel mixture B, burned substantially in a cylindrical primary combustion zone of the combustion or flame tube interior and the exhaust gas A from there to a turbine (not shown) supplied.
  • the outer housing 1 of the combustion chamber forms an annular chamber 1 which is formed in several parts from sheet-metal parts welded together.
  • the one-piece perforated plate 3 is on welds 8 on the one hand on both Stirnsei- th with an annular plate 6 of the swirl generator 5 and a flange for attachment of the outer combustion chamber to a turbine housing (not shown) and on the other hand attached to the annular chamber 1, so that its two end-side end portions 3.1, 3.2 form integral parts of the outer housing.
  • the perforated plate is formed axially in several parts with a central part having the cooling holes 4 and the front side in each case to the annular chamber 1 or edge strips 3.1, 3.2 of the perforated plate is welded.
  • the plate 6 of the swirl generator 5 and the flange, to which the perforated plate 3 forming part of the outer housing is welded, are connected via screw connections 7.1, 7.2 to a cover or turbine housing (not shown).
  • the perforated plate 3 for transmitting loads of the housing 1 and for this purpose at its front ends 3.1, 3.2 attached to the housing, it can in addition to its function, combustion air V to be directed to the flame tube 2 and to the swirl generator lead to reinforce the housing. This can therefore, at least in the reinforced by the tethered perforated plate area, largely free of ribs and thus easier to be formed.
  • the perforated plate can also be advantageous, especially in low-load areas 3.1, 3.2, directly form the outer housing, which makes the construction of the combustion chamber advantageously more compact and manufacturing technology cheaper. Since the perforated plate defines the annular chamber radially from the inside and subsequently defines the combustion air supply to the swirl generator in the regions 3.1, 3.2 as the outer housing, the whole is used in a structurally advantageous manner

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)

Abstract

L'invention concerne une chambre de combustion de turbine à gaz, qui présente une enceinte (1), un tube à flammes (2) monté dedans et une tôle perforée (3) entourant au moins en partie ledit tubes à flammes. Ladite tôle perforée est fixée à l'enceinte à ses deux extrémités frontales (3.1, 3.2).
EP10747801.8A 2009-07-31 2010-07-20 Chambre de combustion de turbine à gaz Active EP2459934B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009035550A DE102009035550A1 (de) 2009-07-31 2009-07-31 Gasturbinenbrennkammer
PCT/DE2010/050048 WO2011012126A2 (fr) 2009-07-31 2010-07-20 Chambre de combustion de turbine à gaz

Publications (2)

Publication Number Publication Date
EP2459934A2 true EP2459934A2 (fr) 2012-06-06
EP2459934B1 EP2459934B1 (fr) 2018-07-18

Family

ID=43087426

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10747801.8A Active EP2459934B1 (fr) 2009-07-31 2010-07-20 Chambre de combustion de turbine à gaz

Country Status (6)

Country Link
US (1) US9377197B2 (fr)
EP (1) EP2459934B1 (fr)
JP (1) JP5443604B2 (fr)
CA (1) CA2769233C (fr)
DE (1) DE102009035550A1 (fr)
WO (1) WO2011012126A2 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2405200A1 (fr) * 2010-07-05 2012-01-11 Siemens Aktiengesellschaft Appareil de combustion et moteur de turbine à gaz
US9625153B2 (en) * 2010-11-09 2017-04-18 Opra Technologies B.V. Low calorific fuel combustor for gas turbine
DE102011007562A1 (de) * 2011-04-18 2012-10-18 Man Diesel & Turbo Se Brennkammergehäuse und damit ausgerüstete Gasturbine
US9341374B2 (en) * 2014-06-03 2016-05-17 Siemens Energy, Inc. Fuel nozzle assembly with removable components

Family Cites Families (21)

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Publication number Priority date Publication date Assignee Title
US3777484A (en) * 1971-12-08 1973-12-11 Gen Electric Shrouded combustion liner
JPS57154857U (fr) * 1981-03-19 1982-09-29
JPS57154857A (en) 1981-03-20 1982-09-24 Hitachi Ltd Semiconductor integrated circuit device
JPS58210413A (ja) * 1982-06-02 1983-12-07 Hitachi Ltd ガスタ−ビン燃焼器
US4567730A (en) * 1983-10-03 1986-02-04 General Electric Company Shielded combustor
JPH0752014B2 (ja) * 1986-03-20 1995-06-05 株式会社日立製作所 ガスタ−ビン燃焼器
US5291732A (en) * 1993-02-08 1994-03-08 General Electric Company Combustor liner support assembly
US5457954A (en) * 1993-12-21 1995-10-17 Solar Turbines Inc Rolling contact mounting arrangement for a ceramic combustor
GB9505067D0 (en) 1995-03-14 1995-05-03 Europ Gas Turbines Ltd Combustor and operating method for gas or liquid-fuelled turbine
GB2328011A (en) 1997-08-05 1999-02-10 Europ Gas Turbines Ltd Combustor for gas or liquid fuelled turbine
DE19751299C2 (de) * 1997-11-19 1999-09-09 Siemens Ag Brennkammer sowie Verfahren zur Dampfkühlung einer Brennkammer
JP2002162036A (ja) 2000-11-22 2002-06-07 Mitsubishi Heavy Ind Ltd 燃焼器
JP2002317650A (ja) * 2001-04-24 2002-10-31 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
EP1312865A1 (fr) 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Chambre de combustion annulaire de turbine à gaz
JP2003176728A (ja) 2001-12-10 2003-06-27 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器のバイバス空気取入装置
US6826913B2 (en) * 2002-10-31 2004-12-07 Honeywell International Inc. Airflow modulation technique for low emissions combustors
US7036316B2 (en) * 2003-10-17 2006-05-02 General Electric Company Methods and apparatus for cooling turbine engine combustor exit temperatures
US7334960B2 (en) * 2005-06-23 2008-02-26 Siemens Power Generation, Inc. Attachment device for removable components in hot gas paths in a turbine engine
DE102006042124B4 (de) 2006-09-07 2010-04-22 Man Turbo Ag Gasturbinenbrennkammer
US20100225902A1 (en) * 2006-09-14 2010-09-09 General Electric Company Methods and apparatus for robotically inspecting gas turbine combustion components
US7617684B2 (en) * 2007-11-13 2009-11-17 Opra Technologies B.V. Impingement cooled can combustor

Non-Patent Citations (1)

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Title
See references of WO2011012126A2 *

Also Published As

Publication number Publication date
JP2013501203A (ja) 2013-01-10
EP2459934B1 (fr) 2018-07-18
US9377197B2 (en) 2016-06-28
DE102009035550A1 (de) 2011-02-03
WO2011012126A3 (fr) 2011-04-14
US20120144834A1 (en) 2012-06-14
CA2769233A1 (fr) 2011-02-03
JP5443604B2 (ja) 2014-03-19
WO2011012126A2 (fr) 2011-02-03
CA2769233C (fr) 2014-04-08

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