EP1422479B1 - Brennkammer zur Verbrennung eines brennbaren Fluidgemisches - Google Patents

Brennkammer zur Verbrennung eines brennbaren Fluidgemisches Download PDF

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Publication number
EP1422479B1
EP1422479B1 EP02026101A EP02026101A EP1422479B1 EP 1422479 B1 EP1422479 B1 EP 1422479B1 EP 02026101 A EP02026101 A EP 02026101A EP 02026101 A EP02026101 A EP 02026101A EP 1422479 B1 EP1422479 B1 EP 1422479B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
liner
rail
coolant
elements
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.)
Expired - Lifetime
Application number
EP02026101A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1422479A1 (de
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 ES02026101T priority Critical patent/ES2307702T3/es
Priority to EP02026101A priority patent/EP1422479B1/de
Priority to DE50212643T priority patent/DE50212643D1/de
Priority to US10/672,506 priority patent/US7322196B2/en
Priority to CNB2003101156358A priority patent/CN100370177C/zh
Priority to JP2003387648A priority patent/JP2004177108A/ja
Publication of EP1422479A1 publication Critical patent/EP1422479A1/de
Application granted granted Critical
Publication of EP1422479B1 publication Critical patent/EP1422479B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/04—Supports for linings

Definitions

  • the present invention relates to a combustion chamber for combustion of a combustible fluid mixture with a burner arranged on the combustion chamber.
  • the invention further relates to a method for cooling a combustion chamber according to the invention.
  • Combustion chambers in particular for gas turbines, are generally provided in their interior with a flow guide body, which is referred to as a liner.
  • a flow guide body which is referred to as a liner.
  • combustion chamber arrangements are used which are composed of a plurality of individual combustion chambers, which open into a common opening.
  • the opening is preferably formed as an annular opening, which also represents the transition to the turbine room.
  • a burner which is provided in the combustion chamber, supplies a combustible fluid mixture, which ignites in the combustion chamber and is conducted through the liner in the direction of the outlet opening.
  • Another concept of a combustor assembly provides a single annular annular combustor instead of a plurality of individual combustors. In such an annular combustion chamber burned ignited combustible fluid mixture enters, burns therein and expands in the direction of the outlet opening.
  • a lining for an inner wall of an industrial furnace which comprises the oven wall upstream of the furnace interior ceramic fiber insulating molded parts. Between the ceramic fiber insulating molded parts and the furnace wall resilient elastomeric fiber mats are arranged. Between adjacent, spaced apart juxtaposed mold parts in each case a T-shaped profiled strip with a strip web and a strip flange is arranged. The strip web engages between the mold parts while the strip flange abuts the inside of the strip in a tight manner. Cooling of the bar or the molded parts by means of cooling fluid is not described.
  • a generic combustion chamber with an on the Combustor arranged burner, a combustion chamber arranged in the liner and an outlet opening proposed, wherein the liner has liner elements which are elastically fixed by means of rail elements on a combustion chamber housing, wherein the rail elements are arranged combustion chamber side and protrude between two adjacently arranged liner elements to the outside.
  • the rail element and the liner elements have coolant channels, which are fluidically connected with each other.
  • the liner element can be fixed by means of a fastening element provided on the outside of the rail element.
  • standard fastening means can thus be used to fix the liner elements to the rail elements. Costs and assembly costs can be reduced.
  • the fastening element is formed by a screw.
  • a releasable connection can be achieved, which can be carried out by means of conventional, known tools. Special tools to perform the attachment can be avoided.
  • the fastening element is formed by a clamping element, in particular a clamping spring.
  • a clamping spring With the use of clamping springs, a particularly simple and fast assembly or disassembly of liner elements can be achieved. This has an advantageous effect in particular when the service life of a system, such as a gas turbine, represents a significant cost factor. Low lifetimes can be achieved.
  • the rail element has a coating at least on the combustion chamber side.
  • the coating can lead both to reducing the physical stress during normal operation and to reducing wear. Maintenance intervals can be extended.
  • a coating may also be provided to form, for example, an inert surface with respect to the fluid in the combustion chamber.
  • the rail element can also be provided with a coating on its entire surface in order to simplify, for example, a coating process.
  • the rail element has liner-like toes for establishing a fluidic connection between a channel of the rail element and a channel of the liner element for a coolant. It can be advantageously achieved a cooling system, which also allows cooling of the liner elements and the rail elements.
  • the combustion chamber has a closed cooling.
  • the coolant can be supplied to the combustion chamber, wherein it feeds its energy absorbed in the context of the cooling function back to the process.
  • energy loss due to the cooling function can be reduced and on the other hand, the coolant can be used for combustion in the combustion chamber. A high efficiency can be achieved.
  • the combustion chamber is arranged in a turbomachine, in particular a gas turbine. Maintenance costs and service life of a gas turbine can be further reduced.
  • the invention further proposes a method for cooling a combustion chamber according to the invention, wherein a coolant flowing through the liner rail flows at least partially in the circumferential direction of the combustion chamber in the direction of the liner element and is deflected in or against the flow direction of the combustion chamber in a channel of the liner element.
  • a channel provided in a liner element which is provided, for example, for cooling the liner element, can be used for discharging the coolant flowing through the liner rail.
  • a closed cooling system for a combustion chamber so the design effort for the flow guidance of the coolant can be reduced.
  • components and assembly costs can be reduced if, for example, a separatedefluidab Entry can be saved.
  • air is used as the coolant.
  • the proportion of the air used for cooling fed back to the combustion chamber so that on the one hand, the heat absorbed by the cooling function and the energy for providing the cooling air can be at least partially recycled to the process. A further increase in the efficiency can be achieved.
  • Fig. 1 shows a section of a gas turbine with a combustion chamber 1 according to the invention, which is designed in the present case as an annular combustion chamber.
  • the combustion chamber 1 has a Housing 7, in which a liner 4 is arranged. At one end of the liner 4 opens a burner 2, via which a combustible fluid is supplied. At the opposite end of the liner, an outlet opening 3 is provided, which is connected to an inlet to a flow channel of a downstream gas turbine, which is not shown. In the middle, a rotor shaft 14 is arranged.
  • Fig. 2 the upper part of the combustion chamber 1 is shown enlarged in section. The combustible fluid supplied via the burner 2 is ignited in a combustion space 15 in the liner 4 and flows in the direction of the outlet opening 3 to the downstream turbine.
  • the liner 4 is constructed in a segment-like manner from liner elements 5, which are each connected adjacent to one another via rail elements 6 ( Fig. 3 ). Via the rail elements 6, the liner elements 5 are at the same time fixed elastically to the combustion chamber housing 7 of the combustion chamber 1. According to the invention, the rail elements 6 are arranged on the combustion chamber side and protrude between two adjacently arranged liner elements 5 to the outside. For attachment, the rail element 6 has openings 17 through which a fastening device 8 can be inserted, via which the rail element 6 is fixed elastically to the housing 7 of the combustion chamber 1. To compensate occurring expansions, the fastening devices 8 are formed elastically in their longitudinal extent. For sealing between the rail element 6 and the liner element 5, a sealing element 16 is provided in each case.
  • the rail element 6 is hot gas side between the two adjacent liners 5 on outer Linerverhakungen not shown on and clamps the liner elements 5 firmly.
  • the rail element 6 also has alternately over its longitudinal extent alternately staggered mounting areas and cooling areas.
  • openings 11 are provided in the rail element, via the one Coolant from the rail member 6 via a provided in an edge region of the liner member 5 channel 20 into the channel 13 of the liner member 5 flows.
  • the rail element 6 is provided with a coating 9, which causes thermal insulation in relation to the hot gas flow within the combustion chamber 1.
  • the coating 9 forms a protection by which the aging of the rail element 6 is reduced.
  • the rail element 6 has liner-like toes, in which the liner elements 5 are fastened to the housing 7 of the combustion chamber 1.
  • the coolant flow is removed in the circumferential direction in the liner elements 5.
  • the area to be cooled is thereby divided into fastening regions 19, which are flowed through in the circumferential direction, and into cooling regions 18, which are flowed through axially.
  • air is used as the coolant, which is taken behind an intake compressor of the gas turbine, not shown, and the cooling system of the gas turbine is supplied.
  • the gas turbine has a combustion chamber with a closed cooling system, so that the air taken from the process for cooling purposes in the combustion chamber can be fed back. The heat energy absorbed by the cooling function is thus returned to the process.

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)
EP02026101A 2002-11-22 2002-11-22 Brennkammer zur Verbrennung eines brennbaren Fluidgemisches Expired - Lifetime EP1422479B1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
ES02026101T ES2307702T3 (es) 2002-11-22 2002-11-22 Camara de combustion para la combustion de una mezcla combutible de fluidos.
EP02026101A EP1422479B1 (de) 2002-11-22 2002-11-22 Brennkammer zur Verbrennung eines brennbaren Fluidgemisches
DE50212643T DE50212643D1 (de) 2002-11-22 2002-11-22 Brennkammer zur Verbrennung eines brennbaren Fluidgemisches
US10/672,506 US7322196B2 (en) 2002-11-22 2003-09-26 Combustion chamber for combusting a combustible fluid mixture
CNB2003101156358A CN100370177C (zh) 2002-11-22 2003-11-10 用于燃烧一种可燃烧的液态混合燃料的燃烧室
JP2003387648A JP2004177108A (ja) 2002-11-22 2003-11-18 可燃性流体混合物を燃焼させる燃焼器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02026101A EP1422479B1 (de) 2002-11-22 2002-11-22 Brennkammer zur Verbrennung eines brennbaren Fluidgemisches

Publications (2)

Publication Number Publication Date
EP1422479A1 EP1422479A1 (de) 2004-05-26
EP1422479B1 true EP1422479B1 (de) 2008-08-13

Family

ID=32187194

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02026101A Expired - Lifetime EP1422479B1 (de) 2002-11-22 2002-11-22 Brennkammer zur Verbrennung eines brennbaren Fluidgemisches

Country Status (6)

Country Link
US (1) US7322196B2 (zh)
EP (1) EP1422479B1 (zh)
JP (1) JP2004177108A (zh)
CN (1) CN100370177C (zh)
DE (1) DE50212643D1 (zh)
ES (1) ES2307702T3 (zh)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
MY154620A (en) * 2008-02-20 2015-07-15 Alstom Technology Ltd Gas turbine having an improved cooling architecture
US8863527B2 (en) * 2009-04-30 2014-10-21 Rolls-Royce Corporation Combustor liner
DE102011076473A1 (de) 2011-05-25 2012-11-29 Rolls-Royce Deutschland Ltd & Co Kg Segmentbauteil aus Hochtemperaturgussmaterial für eine Ringbrennkammer, Ringbrennkammer für ein Flugzeugtriebwerk, Flugzeugtriebwerk und Verfahren zur Herstellung einer Ringbrennkammer
BR112017011472B1 (pt) 2014-12-15 2022-09-13 Nuovo Pignone Tecnologie Srl Combustor para uma turbina a gás e método para montar um forro de combustor
GB201501817D0 (en) * 2015-02-04 2015-03-18 Rolls Royce Plc A combustion chamber and a combustion chamber segment

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2155165A (en) * 1937-05-28 1939-04-18 Heuer Russell Pearce Furnace roof
US2463217A (en) * 1944-09-28 1949-03-01 Tonneson Paul Refractory brick lined furnace wall
NL69245C (zh) * 1946-01-09
US2634694A (en) * 1948-08-18 1953-04-14 Detrick M H Co Suspended arch tile structure
US3328014A (en) * 1965-03-17 1967-06-27 Levi S Longenecker Veneer furnace wall construction
US4246852A (en) * 1979-06-21 1981-01-27 General Signal Corporation Industrial furnace with ceramic insulating modules
DE8603826U1 (de) * 1986-02-13 1986-05-07 Abicht, Roland, Ing.(grad.), 5828 Ennepetal Feuerfeste Auskleidung für einen Industrieofen
DE3625056C2 (de) * 1986-07-24 1997-05-28 Siemens Ag Feuerfeste Auskleidung, insbesondere für Brennkammern von Gasturbinenanlagen
AU594814B2 (en) * 1986-09-13 1990-03-15 Foseco International Limited Furnaces
DE3940381A1 (de) * 1989-12-06 1991-06-13 Pks Engineering Heissgaskanal sowie verschlusselement
DE4309200A1 (de) * 1993-03-22 1994-09-29 Abb Management Ag Vorrichtung zur Einhängung und Entfernung thermisch hoch belasteter Teile in Turbinenanlagen
DE59706557D1 (de) * 1997-07-28 2002-04-11 Alstom Keramische Auskleidung
GB2368902A (en) * 2000-11-11 2002-05-15 Rolls Royce Plc A double wall combustor arrangement

Also Published As

Publication number Publication date
DE50212643D1 (de) 2008-09-25
EP1422479A1 (de) 2004-05-26
ES2307702T3 (es) 2008-12-01
JP2004177108A (ja) 2004-06-24
CN100370177C (zh) 2008-02-20
US7322196B2 (en) 2008-01-29
US20050097894A1 (en) 2005-05-12
CN1506617A (zh) 2004-06-23

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