EP2093487A2 - Chambre de combustion de turbine à gaz dotée d'un tube de flamme céramique - Google Patents

Chambre de combustion de turbine à gaz dotée d'un tube de flamme céramique Download PDF

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Publication number
EP2093487A2
EP2093487A2 EP09002226A EP09002226A EP2093487A2 EP 2093487 A2 EP2093487 A2 EP 2093487A2 EP 09002226 A EP09002226 A EP 09002226A EP 09002226 A EP09002226 A EP 09002226A EP 2093487 A2 EP2093487 A2 EP 2093487A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
flame tube
gas turbine
turbine combustor
combustor 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.)
Granted
Application number
EP09002226A
Other languages
German (de)
English (en)
Other versions
EP2093487B1 (fr
EP2093487A3 (fr
Inventor
Miklos Dr. Gerendás
Sermed Sadig
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2093487A2 publication Critical patent/EP2093487A2/fr
Publication of EP2093487A3 publication Critical patent/EP2093487A3/fr
Application granted granted Critical
Publication of EP2093487B1 publication Critical patent/EP2093487B1/fr
Not-in-force 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
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2212/00—Burner material specifications
    • F23D2212/10—Burner material specifications ceramic

Definitions

  • the present invention relates to a gas turbine combustor having a substantially cylindrical flame tube.
  • the GB-A 1 450 894 describes the construction of a gas turbine combustor with monolithic ceramic shingles.
  • the shingles are used for thermal insulation and are attached to a structural metal housing component. Since ceramic and metal have different thermal expansions, attention must be paid to their connection.
  • the bearing surface between metallic and ceramic component is in a special angle, which is characterized in that the clamping force remains constant even at elevated temperatures.
  • a disadvantage of the gas turbine combustor is the direct connection of the shingles to the housing, which is not suitable for axial combustion chambers with a high mass flow rate, since the radial cross section is not sufficient to bring the pressure loss in the annulus to a sufficiently low level. Due to the segmented structure of the flame tube, there is the additional problem of keeping the gap between the individual shingles, which leave the support structure unprotected, from hot gas.
  • the US-A 6,397,603 describes a gas turbine combustor whose flame tube is made entirely of CMC (ceramic matrix composite material).
  • the combustion chamber is held at the head with studs in their appropriate position.
  • the combustion chamber structure has the disadvantage that the connection of the flame tube with the combustion chamber head via a bolt that allows large radial movements. Due to the type of connection, however, a large radial clearance is required, its control within the operation as very is considered difficult.
  • the gap results from the resulting relative thermal expansions of the CMC tube relative to the metallic combustion chamber head and the housing. During pressure oscillations or impacts in the engine mount, the CMC component beats due to the necessary play on the metal fasteners. Furthermore, the production of the entire flame tube from one piece involves high costs, since the volume of an autoclave is not fully utilized due to the hollow cylinder shape.
  • the invention has for its object to provide a gas turbine combustor of the type mentioned, which allows the use of fiber-reinforced ceramic materials with a simple structure and simple, cost-effective manufacturability.
  • the flame tube is made of a ceramic material and divided in the circumferential direction into a plurality of peripheral elements.
  • the peripheral elements are connected to each other by axial flanges.
  • the axial flanges are preferably connected or coupled by means of articulated coupling elements with the associated components, so that, on the one hand, a statically unambiguous assignment is created and, on the other hand, thermal expansion can be absorbed without damaging the components.
  • the extended center lines of the coupling elements preferably intersect with the engine axis.
  • a flame tube 2 of a combustion chamber of a fiber-reinforced ceramic ceramic material
  • the combustion chamber is composed of an outer flame tube 2, an inner flame tube 8, and the combustion chamber head 7. Outer and inner flame tubes are divided circumferentially into three or more parts.
  • the flame tube 2 is divided circumferentially into three or more parts.
  • the individual segments are connected to each other by axial flanges 1, 9, 201 by means of fastening elements 106.
  • the holder of the flame tube 2 to a combustion chamber housing 3 is carried out with a hinged rigid support in the form of a chain link 104, which with the axial flange 1 on Flame tube 2 and a projection for attachment to the combustion chamber housing 3 is connected.
  • the imaginary extensions 304 of the chain links 104 intersect on an engine axis 301 at an angle that is greater than 0 ° and less than 180 °.
  • the flame tube 2 is guided and positioned on an angled bearing surface 208.
  • the flame tube 2 can rest on the support surface 208, so that the holder allows a constant clamping force during operation, or it can be set to a desired cooling gap, which is held constant during operation by the holder.
  • a flexible high temperature resistant sealing element 209 may additionally be positioned.
  • connection between the flame tube 2 and the combustion chamber head 7 also takes place via an articulated support 4, 204, which attaches both to the axial flange 1, 201 of the flame tube 2 and to a projection 101, 203 for attachment to the combustion chamber housing 3, 101.
  • the extensions 302, 303 of the chain links 104 intersect on the engine axis 301 at an angle greater than 0 ° and less than 180 °.
  • the projections 101, 203 may be integrally formed or joined with the combustion chamber head 7.
  • the projection 103 may be integrally formed or joined to the combustion chamber housing 3.
  • the function of the holder 4, 204 and the projections 103, 203 is independent of their shape.
  • the connecting elements may be made of metallic or ceramic materials.
  • the holder according to the invention makes it possible, at high temperatures, to move the ceramic housing relative to the combustion chamber housing and the combustion chamber head in a stress-free manner.
  • the relative movements are intercepted by the articulated mounting of the flame tube.
  • the segmentation of the flame tube makes it possible to keep the manufacturing costs low compared to a full-ring design, since the volume of an autoclave is better utilized by stacking the individual segments. Nevertheless, the introduction of the Axialflanschs no leaks, as in shingles after GB-A 1 450 894 are common, up.
  • Fig. 6 shows a schematic overall view of a combustion chamber according to the invention in a gas turbine.
  • a combustion chamber 401 a burner 402 with arm and head, bypass 403, fan 404, compressor 405, inner and outer combustion chamber housing 407 and 408, Turbinenleitrad 409, turbine runner 410, drive shaft 411 and 412 combustion chamber head are provided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09002226.0A 2008-02-21 2009-02-17 Arrangement avec une chambre de combustion de turbine à gaz avec un tube de flamme céramique pour un moteur Not-in-force EP2093487B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102008010294A DE102008010294A1 (de) 2008-02-21 2008-02-21 Gasturbinenbrennkammer mit keramischem Flammenrohr

Publications (3)

Publication Number Publication Date
EP2093487A2 true EP2093487A2 (fr) 2009-08-26
EP2093487A3 EP2093487A3 (fr) 2013-11-27
EP2093487B1 EP2093487B1 (fr) 2016-08-17

Family

ID=40512449

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09002226.0A Not-in-force EP2093487B1 (fr) 2008-02-21 2009-02-17 Arrangement avec une chambre de combustion de turbine à gaz avec un tube de flamme céramique pour un moteur

Country Status (3)

Country Link
US (1) US8281598B2 (fr)
EP (1) EP2093487B1 (fr)
DE (1) DE102008010294A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014149108A1 (fr) 2013-03-15 2014-09-25 Graves Charles B Agencement d'enceinte et de chemisage à dalles pour une chambre de combustion
US10100737B2 (en) 2013-05-16 2018-10-16 Siemens Energy, Inc. Impingement cooling arrangement having a snap-in plate
RU2598964C2 (ru) * 2014-12-12 2016-10-10 Федеральное агентство научных организаций Федеральное Государственное Бюджетное Научное Учреждение Всероссийский научно-исследовательский институт электрификации сельского хозяйства (ФГБНУ ВИЭСХ) Устройство камеры сгорания с регулируемым зазором подачи охлаждающего воздуха для микрогазотурбинного двигателя
US10533740B2 (en) 2015-07-09 2020-01-14 Carrier Corporation Inward fired ultra low NOX insulating burner flange
CN205016725U (zh) * 2015-09-10 2016-02-03 欧品电子(昆山)有限公司 电源插座端子
DE102015226079A1 (de) * 2015-12-18 2017-06-22 Dürr Systems Ag Brennkammervorrichtung und Gasturbinenvorrichtung
US11015812B2 (en) * 2018-05-07 2021-05-25 Rolls-Royce North American Technologies Inc. Combustor bolted segmented architecture
CN110107402B (zh) * 2019-04-29 2021-06-08 中国航空工业集团公司金城南京机电液压工程研究中心 一种陶瓷涡轮发动机
CN114484505B (zh) * 2022-01-27 2023-05-16 西安鑫垚陶瓷复合材料有限公司 陶瓷基复合材料全环型火焰筒、定型模具及其制备方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1450894A (en) 1972-11-01 1976-09-29 Lucas Industries Ltd Flame tubes
US6397603B1 (en) 2000-05-05 2002-06-04 The United States Of America As Represented By The Secretary Of The Air Force Conbustor having a ceramic matrix composite liner

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1346600A (en) * 1913-10-10 1920-07-13 Stock Motorpflug Gmbh Moldboard for plows
GB543918A (en) * 1939-09-29 1942-03-19 Bbc Brown Boveri & Cie Improvements and relating to combustion chambers
US2686655A (en) * 1949-09-02 1954-08-17 Maschf Augsburg Nuernberg Ag Joint between ceramic and metallic parts
US3854503A (en) * 1971-08-05 1974-12-17 Lucas Industries Ltd Flame tubes
US3956886A (en) * 1973-12-07 1976-05-18 Joseph Lucas (Industries) Limited Flame tubes for gas turbine engines
DE4114768A1 (de) * 1990-05-17 1991-11-21 Siemens Ag Keramischer hitzeschild fuer eine heissgasfuehrende struktur
US5333443A (en) * 1993-02-08 1994-08-02 General Electric Company Seal assembly
US5636508A (en) * 1994-10-07 1997-06-10 Solar Turbines Incorporated Wedge edge ceramic combustor tile
DE59806717D1 (de) * 1998-03-17 2003-01-30 Alstom Switzerland Ltd Keramische Auskleidung einer Brennkammer
US7665307B2 (en) * 2005-12-22 2010-02-23 United Technologies Corporation Dual wall combustor liner
DE102006060857B4 (de) * 2006-12-22 2014-02-13 Deutsches Zentrum für Luft- und Raumfahrt e.V. CMC-Brennkammerauskleidung in Doppelschichtbauweise
US7861535B2 (en) * 2007-09-24 2011-01-04 United Technologies Corporation Self-aligning liner support hanger

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1450894A (en) 1972-11-01 1976-09-29 Lucas Industries Ltd Flame tubes
US6397603B1 (en) 2000-05-05 2002-06-04 The United States Of America As Represented By The Secretary Of The Air Force Conbustor having a ceramic matrix composite liner

Also Published As

Publication number Publication date
EP2093487B1 (fr) 2016-08-17
US8281598B2 (en) 2012-10-09
DE102008010294A1 (de) 2009-08-27
EP2093487A3 (fr) 2013-11-27
US20090235667A1 (en) 2009-09-24

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