EP0943867A1 - Revêtement céramique pour une chambre de combustion - Google Patents

Revêtement céramique pour une chambre de combustion Download PDF

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Publication number
EP0943867A1
EP0943867A1 EP98810220A EP98810220A EP0943867A1 EP 0943867 A1 EP0943867 A1 EP 0943867A1 EP 98810220 A EP98810220 A EP 98810220A EP 98810220 A EP98810220 A EP 98810220A EP 0943867 A1 EP0943867 A1 EP 0943867A1
Authority
EP
European Patent Office
Prior art keywords
wall
combustion chamber
hollow chambers
hollow
ceramic
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
EP98810220A
Other languages
German (de)
English (en)
Other versions
EP0943867B1 (fr
Inventor
Manfred Dr. Aigner
Peter Dubach
Armin Dr. Heger
Andreas Dr. Pfeiffer
Ludwig Dr. Weiler
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.)
General Electric Switzerland GmbH
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 ABB Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Priority to EP19980810220 priority Critical patent/EP0943867B1/fr
Priority to DE59806717T priority patent/DE59806717D1/de
Publication of EP0943867A1 publication Critical patent/EP0943867A1/fr
Application granted granted Critical
Publication of EP0943867B1 publication Critical patent/EP0943867B1/fr
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
    • F23R3/007—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
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used

Definitions

  • the invention relates to a ceramic lining for thermally highly stressed Walls of combustion chambers according to the preamble of claim 1.
  • Such Linings are used in particular as inner wall insulation for metallic combustion chambers, for example for gas turbines.
  • a ceramic lining of a combustion chamber is known from DE 195 02 730 A1, which an uncooled removable lining of a combustion chamber with ceramic Elements that meet the high thermal and mechanical Stresses in a modern commercial, highly stressed gas turbine combustor Holds up.
  • the lining consists of at least one wall plate made of high temperature resistant Structural ceramics, also called monolithic ceramics, with at least a through opening and one fastener per Opening.
  • the fastener is in one with the foot on the metallic Fastened wall-mounted metallic holding device, the Head of the fastener rests in the opening of the wall plate.
  • the fastener also consists of high temperature resistant structural ceramics and is resiliently connected to the holding device. Between the metallic Wall and the ceramic wall plate is an insulation layer made of fiber ceramic intended.
  • the lining consists of many individual There are wall elements that must be attached separately that the Attaching the lining to the metallic support structure is quite complex, and that the lining is complicated due to the need for multiple layers is. In addition, it has been shown in practice that monolithic ceramics a shock or impact stress are very sensitive and often too Break go.
  • the invention tries to avoid all of these disadvantages. You have the task based on a ceramic lining made of fiber ceramics for combustion chambers develop which is suitable for large combustion chamber dimensions, the simple is to be attached to the metallic supporting wall and its heat transfer mainly done by radiation.
  • the advantages of the invention are that there is no additional insulating material it is necessary that the ceramic fiber material is resistant to thermal shock and is fault tolerant and the lining consists of only a few individual parts.
  • the hollow chambers have a longitudinal expansion, which is adapted to the longitudinal extent of the combustion chamber.
  • the hollow chambers can also run transversely.
  • the limitations in temperature resistance The fiber-ceramic materials can be removed maintained by guiding cooling air inside the hollow chambers be, so that the hollow chambers then in addition to their function as heat shields also perform the function of cooling air ducts.
  • the hollow chambers are filled with insulating material on the inside. In this way, the temperature of the metallic supporting wall can be further dismantled.
  • each hollow chamber is advantageously made more resistant to high temperatures Screws and elastic elements, preferably disc springs fixed to the metallic supporting wall. This attachment is compared to that of monolithic ceramic components much easier. Because of the hollow chamber only needs to be fixed to the wall resting on the metal support the low thermal expansion of a wall thickness with the elastic elements be balanced.
  • an embodiment of the invention is based on a thermal shown highly loaded gas turbine combustion chamber.
  • Fig. 1 shows a longitudinal section
  • Fig. 2 shows a cross section of the combustion chamber in schematic representation in a first embodiment of the invention.
  • the Combustion chamber 1 consists of a metallic support wall 2, on the inside several segments in the form of hollow chambers 3 are arranged side by side. These hollow chambers 3 are made from fault-tolerant ceramic fiber material, which also has a very good thermal shock resistance.
  • the inner wall 4 of each hollow chamber 3 is the interior of the combustion chamber 1 facing, while the outer wall 5 of each hollow chamber directly on the metallic Support wall 2 is applied. Between the individual in the circumferential direction juxtaposed hollow chambers 3 should only have the narrowest possible gap 6 (see FIG. 2) so that only a small convection flow occurs.
  • Convection-free hollow chambers 3 are aimed at, so that the heat transfer from the hot combustion chamber to the (cooled) metallic support structure must mainly be done by radiation.
  • the hollow chamber 3 thus forms even an insulating layer, it is not an additional insulating material, such as necessary when using linings with monolithic structural ceramics.
  • the hollow chambers 3 extend over the entire Length of the combustion chamber 1, its longitudinal extent is the longitudinal extent adapted to the combustion chamber 1.
  • the hollow chambers 3 are in the circumferential direction arranged side by side. Of course it is in another Embodiment also possible that the hollow chambers 3 transverse to the longitudinal direction run.
  • FIG. 3 is a partial perspective view of a combustion chamber in a second Embodiment of the invention shown.
  • the hollow chambers 3 made of ceramic fiber material on the Metallic support wall 2 applied and serve on the one hand as a heat shield, on the other hand additionally flows through the interior of the hollow chambers 3 cooling air 7. This may be necessary if the material is exposed to extremely high temperatures for a long time is because the ceramic fiber material currently available with respect to Long-term stability at high temperatures does not meet all requirements enough. The solution to this problem is from different sides worked out.
  • the hollow chambers arranged side by side in the circumferential direction 3 are in their longitudinal extent also the longitudinal extent of the Combustion chamber 1 adapted so that advantageously only a few individual parts for the lining are needed.
  • In the entry area into the combustion chamber 1 are vertical to the above Hollow chambers also hollow chambers 3 made of ceramic fiber material arranged, which have an opening for the burner in the middle
  • Fig. 4 shows a third partial perspective view of a combustion chamber Embodiment variant of the invention.
  • the ceramic fiber material Hollow chambers 3 are here directly with their outer wall 5 with the metallic support structure 2 connected, as exemplified with reference to FIG. 5 is explained.
  • the inner wall 4 of the hollow chambers 3 is the interior of the Combustion chamber 1 facing.
  • the hollow chambers 3 are filled with insulating material 8. This too In this way, the temperature acting on the metallic support wall 2 is reduced.
  • Fig. 5 shows an example of a possible type of attachment of the hollow chambers 3 on the metallic support wall 2.
  • the attachment is relatively simple and without large spring elements possible because the thermal expansion takes place in the combustion chamber.
  • the Hollow chamber 3 is on its outer wall lying on the metal support 2 5 fixed. This means that only the slight expansion of a wall thickness (approx. 5 mm) be intercepted.
  • the attachment is done with high temperature resistant screws 9, for example made of fiber ceramics and with external elastic elements, e.g. B. disc springs.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Thermal Insulation (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19980810220 1998-03-17 1998-03-17 Revêtement céramique pour une chambre de combustion Expired - Lifetime EP0943867B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19980810220 EP0943867B1 (fr) 1998-03-17 1998-03-17 Revêtement céramique pour une chambre de combustion
DE59806717T DE59806717D1 (de) 1998-03-17 1998-03-17 Keramische Auskleidung einer Brennkammer

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19980810220 EP0943867B1 (fr) 1998-03-17 1998-03-17 Revêtement céramique pour une chambre de combustion

Publications (2)

Publication Number Publication Date
EP0943867A1 true EP0943867A1 (fr) 1999-09-22
EP0943867B1 EP0943867B1 (fr) 2002-12-18

Family

ID=8235987

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19980810220 Expired - Lifetime EP0943867B1 (fr) 1998-03-17 1998-03-17 Revêtement céramique pour une chambre de combustion

Country Status (2)

Country Link
EP (1) EP0943867B1 (fr)
DE (1) DE59806717D1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008010294A1 (de) * 2008-02-21 2009-08-27 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit keramischem Flammenrohr
EP2107307A1 (fr) * 2008-04-03 2009-10-07 Snecma Propulsion Solide Chambre de combustion de turbine à gaz à parois interne et externe sectorisées
EP2107308A1 (fr) * 2008-04-03 2009-10-07 Snecma Propulsion Solide Chambre de combustion sectorisée en CMC pour turbine à gaz
EP2233835A1 (fr) * 2009-03-23 2010-09-29 Siemens Aktiengesellschaft Chambre de combustion brasée avec des inserts en céramique
DE102014204468A1 (de) * 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
US10408451B2 (en) 2013-09-11 2019-09-10 Siemens Aktiengesellschaft Wedge-shaped ceramic heat shield of a gas turbine combustion chamber
EP3339737B1 (fr) * 2016-12-23 2019-10-23 Ansaldo Energia S.p.A. Tuile thermo-isolante pour la chambre de combustion d'une turbine à gaz
EP3540314A4 (fr) * 2016-11-11 2020-06-03 Kawasaki Jukogyo Kabushiki Kaisha Chemise de chambre de combustion

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006060857B4 (de) 2006-12-22 2014-02-13 Deutsches Zentrum für Luft- und Raumfahrt e.V. CMC-Brennkammerauskleidung in Doppelschichtbauweise
DE102007062699A1 (de) 2007-12-27 2009-07-02 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerauskleidung

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1038661A (en) * 1961-12-05 1966-08-10 Ass Elect Ind Improvements relating to metallic gas turbine combustion chambers
FR2158572A1 (fr) * 1971-11-05 1973-06-15 Penny Robert
DE2364258A1 (de) * 1973-12-22 1975-06-26 Lucas Aerospace Ltd Flammrohr fuer eine gasturbine
EP0046520A1 (fr) * 1980-08-22 1982-03-03 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Chambre de combustion en céramique
US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
US4988290A (en) * 1988-07-12 1991-01-29 Forschungszentrum Julich Gmbh Combustion space with a ceramic lining such as in the combustion chamber of an internal combustion engine or the combustion space in a rotary kiln furnace
DE19502730A1 (de) 1995-01-28 1996-08-01 Abb Management Ag Keramische Auskleidung
US5592814A (en) * 1994-12-21 1997-01-14 United Technologies Corporation Attaching brittle composite structures in gas turbine engines for resiliently accommodating thermal expansion

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1038661A (en) * 1961-12-05 1966-08-10 Ass Elect Ind Improvements relating to metallic gas turbine combustion chambers
FR2158572A1 (fr) * 1971-11-05 1973-06-15 Penny Robert
DE2364258A1 (de) * 1973-12-22 1975-06-26 Lucas Aerospace Ltd Flammrohr fuer eine gasturbine
EP0046520A1 (fr) * 1980-08-22 1982-03-03 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Chambre de combustion en céramique
US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
US4988290A (en) * 1988-07-12 1991-01-29 Forschungszentrum Julich Gmbh Combustion space with a ceramic lining such as in the combustion chamber of an internal combustion engine or the combustion space in a rotary kiln furnace
US5592814A (en) * 1994-12-21 1997-01-14 United Technologies Corporation Attaching brittle composite structures in gas turbine engines for resiliently accommodating thermal expansion
DE19502730A1 (de) 1995-01-28 1996-08-01 Abb Management Ag Keramische Auskleidung

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
K. SMITH, A.FAHME: "Testing of Full Scale Low Emissions Ceramic Gas Turbine Combustor", ASME, 2 June 1997 (1997-06-02), ORLANDO, FLORIDA

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8281598B2 (en) 2008-02-21 2012-10-09 Rolls-Royce Deutchland Ltd & Co Kg Gas-turbine combustion chamber with ceramic flame tube
DE102008010294A1 (de) * 2008-02-21 2009-08-27 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit keramischem Flammenrohr
CN101551122B (zh) * 2008-04-03 2012-10-17 斯奈克玛动力部件公司 陶瓷基复合材料制成且细分为多区域的燃气涡轮机燃烧室
FR2929690A1 (fr) * 2008-04-03 2009-10-09 Snecma Propulsion Solide Sa Chambre de combustion sectorisee en cmc pour turbine a gaz
JP2009293914A (ja) * 2008-04-03 2009-12-17 Snecma Propulsion Solide Ｃｍｃ材料で作られ且つセクターに更に分割されたガス・タービンの燃焼チャンバ
EP2107308A1 (fr) * 2008-04-03 2009-10-07 Snecma Propulsion Solide Chambre de combustion sectorisée en CMC pour turbine à gaz
EP2107307A1 (fr) * 2008-04-03 2009-10-07 Snecma Propulsion Solide Chambre de combustion de turbine à gaz à parois interne et externe sectorisées
FR2929689A1 (fr) * 2008-04-03 2009-10-09 Snecma Propulsion Solide Sa Chambre de combustion de turbine a gaz a parois interne et externe sectorisees
EP2233835A1 (fr) * 2009-03-23 2010-09-29 Siemens Aktiengesellschaft Chambre de combustion brasée avec des inserts en céramique
US10408451B2 (en) 2013-09-11 2019-09-10 Siemens Aktiengesellschaft Wedge-shaped ceramic heat shield of a gas turbine combustion chamber
DE102014204468A1 (de) * 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
US9803869B2 (en) 2014-03-11 2017-10-31 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber and method for manufacturing the same
EP3540314A4 (fr) * 2016-11-11 2020-06-03 Kawasaki Jukogyo Kabushiki Kaisha Chemise de chambre de combustion
US11543132B2 (en) 2016-11-11 2023-01-03 Kawasaki Jukogyo Kabushiki Kaisha Combustor liner
US11873992B2 (en) 2016-11-11 2024-01-16 Kawasaki Jukogyo Kabushiki Kaisha Combustor liner
EP3339737B1 (fr) * 2016-12-23 2019-10-23 Ansaldo Energia S.p.A. Tuile thermo-isolante pour la chambre de combustion d'une turbine à gaz

Also Published As

Publication number Publication date
EP0943867B1 (fr) 2002-12-18
DE59806717D1 (de) 2003-01-30

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