EP0943867B1 - Keramische Auskleidung einer Brennkammer - Google Patents
Keramische Auskleidung einer Brennkammer Download PDFInfo
- Publication number
- EP0943867B1 EP0943867B1 EP19980810220 EP98810220A EP0943867B1 EP 0943867 B1 EP0943867 B1 EP 0943867B1 EP 19980810220 EP19980810220 EP 19980810220 EP 98810220 A EP98810220 A EP 98810220A EP 0943867 B1 EP0943867 B1 EP 0943867B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wall
- ceramic
- combustion chamber
- hollow chambers
- lining
- 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
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Images
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, z. 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)
Description
- Fig. 1
- einen schematischen Längsschnitt der Brennkammer in einer ersten Ausführungsvariante;
- Fig. 2
- einen Querschnitt der Brennkammer entlang der Linie II-II in Fig. 1;
- Fig. 3
- eine perspektivische Teilansicht einer Brennkammer in einer zweiten Ausführungsvariante;
- Fig. 4
- eine perspektivische Teilansicht der Brennkammer in einer dritten Ausführungsvariante der Erfindung;
- Fig. 5
- einen Schnitt im Bereich der Befestigung der Auskleidung an der metallischen Tragwand.
- 1
- Brennkammer
- 2
- metallische Tragwand
- 3
- Hohlkammer
- 4
- innere Wand von Pos. 3
- 5
- äussere Wand von Pos. 3
- 6
- Spalt
- 7
- Kühlluft
- 8
- Isoliermaterial
- 9
- Schraube
- 10
- Tellerfeder
Claims (5)
- Keramische Auskleidung für Brennräume, welche an der Innenseite einer thermisch hochbeanspruchten metallischen Tragwand (2) befestigt ist, wobei das Material der Auskleidung Faserkeramik ist, dadurch gekennzeichnet, dass die Auskleidung aus einzelnen nebeneinander angeordneten Segmenten in Form von Hohlkammern (3) mit einer dem Brennrauminneren zugewandten inneren (4) und einer direkt auf der metallischen Tragwand (2) aufliegenden äusseren Wand (5) besteht.
- Keramische Auskleidung nach Anspruch 1, dadurch gekennzeichnet, dass die Hohlkammern (3) eine Längsausdehnung aufweisen, welche der Längsausdehnung des Brennraumes (1) angepasst ist.
- Keramische Auskleidung nach Anspruch 1 und 2, dadurch gekennzeichnet, dass die Hohlkammern (3) zur Führung von Kühlluft (7) vorgesehen sind.
- Keramische Auskleidung nach Anspruch 1 und 2, dadurch gekennzeichnet, dass die Hohlkammern (3) mit Isoliermaterial (8) gefüllt sind.
- Keramische Auskleidung nach einem der Ansprüchen 1 bis 4, dadurch gekennzeichnet, dass die äussere Wand (5) jeder Hohlkammer (3) mittels hochtemperaturfester Schrauben (9) und elastischer Elemente, vorzugsweise Tellerfedern (10), an der metallischen Tragwand (2) fixiert ist.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP19980810220 EP0943867B1 (de) | 1998-03-17 | 1998-03-17 | Keramische Auskleidung einer Brennkammer |
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 (de) | 1998-03-17 | 1998-03-17 | Keramische Auskleidung einer Brennkammer |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0943867A1 EP0943867A1 (de) | 1999-09-22 |
EP0943867B1 true EP0943867B1 (de) | 2002-12-18 |
Family
ID=8235987
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19980810220 Expired - Lifetime EP0943867B1 (de) | 1998-03-17 | 1998-03-17 | Keramische Auskleidung einer Brennkammer |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0943867B1 (de) |
DE (1) | DE59806717D1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1939529A1 (de) | 2006-12-22 | 2008-07-02 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | CMC-Brennkammerauskleidung in Doppelschichtbauweise |
EP2075506A2 (de) | 2007-12-27 | 2009-07-01 | Rolls-Royce Deutschland Ltd & Co KG | Brennkammerauskleidung |
Families Citing this family (8)
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 |
FR2929689B1 (fr) * | 2008-04-03 | 2013-04-12 | Snecma Propulsion Solide | Chambre de combustion de turbine a gaz a parois interne et externe sectorisees |
FR2929690B1 (fr) * | 2008-04-03 | 2012-08-17 | Snecma Propulsion Solide | Chambre de combustion sectorisee en cmc pour turbine a gaz |
EP2233835A1 (de) * | 2009-03-23 | 2010-09-29 | Siemens Aktiengesellschaft | Mit Keramikeinsätzen hartgelötete Brennkammer |
WO2015036430A1 (de) | 2013-09-11 | 2015-03-19 | Siemens Aktiengesellschaft | Keilförmiges keramisches hitzeschild einer gasturbinenbrennkammer |
DE102014204468A1 (de) * | 2014-03-11 | 2015-10-01 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung |
EP3540314B1 (de) * | 2016-11-11 | 2023-07-12 | Kawasaki Jukogyo Kabushiki Kaisha | Brennkammerwand für eine gasturbine |
IT201600130851A1 (it) * | 2016-12-23 | 2018-06-23 | Ansaldo Energia Spa | Piastrella termoisolante per camere di combustione di turbine a gas |
Family Cites Families (8)
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 |
BE790956A (fr) * | 1971-11-05 | 1973-03-01 | Penny Robert N | Tube de flamme pour chambre de combustion de moteur a turbine agaz |
DE2364258C3 (de) * | 1973-12-22 | 1981-01-29 | Lucas Industries Ltd., Birmingham, West Midlands (Ver. Koenigreich) | Flammrohr für eine Gasturbine |
DE3031689A1 (de) * | 1980-08-22 | 1982-03-04 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Keramische brennkammer |
US4422300A (en) * | 1981-12-14 | 1983-12-27 | United Technologies Corporation | Prestressed combustor liner for gas turbine engine |
DE3823510A1 (de) * | 1988-07-12 | 1990-01-18 | Kernforschungsanlage Juelich | Keramische auskleidung fuer einen brennraum |
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 |
-
1998
- 1998-03-17 EP EP19980810220 patent/EP0943867B1/de not_active Expired - Lifetime
- 1998-03-17 DE DE59806717T patent/DE59806717D1/de not_active Expired - Lifetime
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1939529A1 (de) | 2006-12-22 | 2008-07-02 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | CMC-Brennkammerauskleidung in Doppelschichtbauweise |
DE102006060857B4 (de) * | 2006-12-22 | 2014-02-13 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | CMC-Brennkammerauskleidung in Doppelschichtbauweise |
EP2075506A2 (de) | 2007-12-27 | 2009-07-01 | Rolls-Royce Deutschland Ltd & Co KG | Brennkammerauskleidung |
DE102007062699A1 (de) | 2007-12-27 | 2009-07-02 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammerauskleidung |
Also Published As
Publication number | Publication date |
---|---|
EP0943867A1 (de) | 1999-09-22 |
DE59806717D1 (de) | 2003-01-30 |
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