EP3707435A1 - Tubular combustion chamber with ceramic cladding - Google Patents
Tubular combustion chamber with ceramic claddingInfo
- Publication number
- EP3707435A1 EP3707435A1 EP18810907.8A EP18810907A EP3707435A1 EP 3707435 A1 EP3707435 A1 EP 3707435A1 EP 18810907 A EP18810907 A EP 18810907A EP 3707435 A1 EP3707435 A1 EP 3707435A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- jacket
- ceramic tube
- ceramic
- heat shield
- 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
Links
- 239000000919 ceramic Substances 0.000 title claims abstract description 49
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 33
- 238000005253 cladding Methods 0.000 title 1
- 239000002131 composite material Substances 0.000 claims description 10
- 239000000543 intermediate Substances 0.000 claims description 10
- 238000013016 damping Methods 0.000 claims description 5
- 239000011819 refractory material Substances 0.000 claims description 3
- 230000008961 swelling Effects 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims 2
- 239000007789 gas Substances 0.000 description 7
- 239000002184 metal Substances 0.000 description 7
- 238000010276 construction Methods 0.000 description 3
- 230000013011 mating Effects 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000005304 joining Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002905 metal composite material Substances 0.000 description 2
- 239000011214 refractory ceramic Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 101100345589 Mus musculus Mical1 gene Proteins 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 210000001061 forehead Anatomy 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000002557 mineral fiber Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- BULVZWIRKLYCBC-UHFFFAOYSA-N phorate Chemical compound CCOP(=S)(OCC)SCSCC BULVZWIRKLYCBC-UHFFFAOYSA-N 0.000 description 1
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
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
- F23C3/002—Combustion apparatus characterised by the shape of the combustion chamber the chamber having an elongated tubular form, e.g. for a radiant tube
-
- 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
- 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
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
-
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
-
- 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
-
- 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
- F23D2212/103—Fibres
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/00018—Means for protecting parts of the burner, e.g. ceramic lining outside of the flame tube
-
- 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
- F23R2900/00017—Assembling combustion chamber liners or subparts
Definitions
- the invention relates to a tube combustion chamber with a ceramic lining.
- the object of the invention is to carefully install such a ceramic A set in the metallic shell a combustion chamber and, if necessary, an interface geometry of ceramic segments of such a combustion chamber with one another to ge so that thermal expansions are not hindered.
- the interface geometry must fulfill various additional functions, such as the transmission of axial and radial elastic composite loads, the unambiguous definition of the position and rotation of the individual elements, the seal between Hot and cold gas side and the avoidance of tensile stresses in the interface area.
- the invention solves the task directed to a combustion chamber by providing that in such a Brennkam mer, comprising a arranged around a main axis of the combustion chamber jacket and a disposed within the shell ceramic tube, an intermediate layer is disposed between the shell and ceramic tube, the jacket is at least partially co nical and the ceramic tube is axially braced along the main axis in the shell, wherein the ceramic tube is a composite of several heat shield segments and wherein individual hit zeschildsegmente a segment row, each of which can be acted upon by a hot medium hot side, one of
- Thermal expansion differences occur in particular between hot and cold side of the ceramic segments. It is particularly advantageous if the column are sickle-shaped.
- the cold-side contact surfaces of the individual segments serve to transmit power in the tangential and axial directions.
- the open to the hot side crescent-shaped column similar to a tongue and groove connection, ensure for a unbehinder te thermal expansions and on the other a positive connection and thus a position definition in the radial direction.
- the side and end face geometry must be designed in such a way that their gap geometry is stretch-adapted and thus minimizes tion of the column realized during operation to avoid the penetration of hot gas as far as possible.
- the jacket is metallic.
- the ceramic tube made of refractory material.
- the intermediate layer is a ceramic swelling mat.
- Swelling mats are mineral fiber mats containing expandable particles. Due to their elastic restoring forces they exert a holding force on the ceramic tube. About the axial distortion of the heat shield segments who generates the radial forces that are reliably transmitted to the ceramic outer surface via these resilient elements.
- the intermediate layer comprises Fe and / or damping elements. These can be kera mixed or metallic.
- the jacket at the opening with the largest opening diameter attachment means can be pulled against the opening.
- the axial Verspan nen by a force and / or form-fitting joined Me tallring done.
- the adhesion is made from the metal ring on the ceramic column and springs on the metallic conical counter surface.
- the ceramic tube itself may conveniently be a Vollzylin or a full cone.
- the end faces are not flat, but to be designed so that a positive connection between the Kerami rule individual segments is formed in the circumferential direction.
- the interface geometry is preferably carried out in a wellenför shaped geometry or any other form gleichge devisrologyn the geometry. Again, preferably stump fe angles and comparatively large radii are used.
- a ceramic composite of several refractory heat shield segments is therefore provided according to the invention.
- the resulting ring or cone made of refractory ceramics is supported by means of a resilient inter mediate layer in a metallic housing.
- the fastening of the ceramic segments is realized via the external pressure, so that a construction without gaps is created.
- FIG. 1 shows a detail of a composite solution for a combustion chamber of the elements sheath, ceramic tube and inter mediate layer
- Figure 2 is a representation of the forces acting on the composite solution of Figure 1 in the side view and
- FIG. 3 a representation of the acting forces of the composite solution of FIG. 1 in the longitudinal direction
- FIG. 5 axial clamping on the example of a metal ring in the closed state
- Figure 6 shows the principle of two conical components with central
- Figure 8 is a tongue and groove-like compound of heat
- Figure 9 is a tongue and groove-like compound of heat
- FIG. 10 shows a wave-shaped geometry between different ones
- Figure 1 shows schematically and by way of example a composite solution of three elements for a combustion chamber 1 with jacket 3, a arranged in the jacket 3 ceramic tube 4 made of refractory material and a high temperature resistant intermediate layer 5, which is disposed between the shell 3 and ceramic tube 4.
- Figure 2 illustrates here to the inventive axial bracing 18 of the ceramic tube 4 in the shell 3.
- axial clamping 18 of the ceramic tube in the direction of the main axis 2 of a conical metalli's mating surface, ie the shell, radial forces are 19th generated, which are transmitted via resilient elements, ie the intermediate layer 5, on the ceramic outer surface.
- resilient elements ie the intermediate layer 5
- Figures 4 and 5 show an example of how the axial Ver span 18 can be done by a force and / or form-fitting geglag th metal ring as a fastener 7 in the region of size ren opening 6 of the cone.
- the frictional connection he follows from the metal ring on the ceramic column and springs on the metallic conical mating surface of the shell.
- the metallic component can be separated into two conical components (for example with a dividing plane 20 shifted in the middle, as shown in FIG. 6).
- the other part of the jacket 9 with the ent speaking ceramic tube 4 acts here as a counterpart 8 for the axial tension 18th
- Figure 7 shows a longitudinally cut tube combustion chamber 1 with transition piece 21, in which a clothing, as shown in Figure 6, offers.
- FIGS. 8 to 10 show details of the geometry between individual ceramic heat shield segments 10 in a ceramic-metal composite under external pressure.
- FIG. 8 shows two adjacent heat shield segments 10 in the installed state.
- the heat shield segments 10 each have a hot side 11 which can be acted upon by a hot medium, one of the hot side 11 opposite the jacket 3 facing Cold side 12 and a between hot side 11 and cold side 12 encircling edge 13.
- the heat shield segments 10 have on the edge 13 to the cold side 12 subsequent izoflä surfaces 15, which serve for transmitting power in the tangential and axial direction, and the hot gas side 11 toward opening column 16.
- the opening to the hot gas side column 16 are sickle-shaped, similar to the function of a groove and Fe derharm.
- the gap 16 itself ensures an unhindered thermal expansion, the shape of the gap 16 allows ei nen positive locking and thus a position definition in the radial direction.
- Figure 9 shows the same two heat shield segments 10, as Figure 8. The difference is that the heat shield segments 10 of Figure 8 in cold, he 9 are in a hot state and the gap 16 due to the heat expansion 22 is closed.
- the end faces 17 of the heat shield segments 10 are not flat but to be designed so that a positive connection between the individual ceramic heat shield segments 10 is formed in the circumferential direction.
- the interface geometry is preferably carried out in a wave-shaped geometry, as shown in Figure 10, or any other form gleichge Techrleistenden geometry.
- Figure 10 shows a section through a combustion chamber 1 with two Seg ment rows 14. The flow direction 23 of the hot gases in loading operation is also indicated.
- the side and end face geometry is of course designed to be stretch adapted, so that a minimization of the column 16 and also between the rows of segments 14 is realized during operation in order to avoid the ingress of hot gas whatsoever.
- preferably obtuse angles and large radii are to be used in order to avoid zugêtsbean sprayed zones.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP17206622.7A EP3499125A1 (en) | 2017-12-12 | 2017-12-12 | Pipe combustion chamber with ceramic cladding |
PCT/EP2018/081305 WO2019115129A1 (en) | 2017-12-12 | 2018-11-15 | Tubular combustion chamber with ceramic cladding |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3707435A1 true EP3707435A1 (en) | 2020-09-16 |
EP3707435B1 EP3707435B1 (en) | 2021-09-15 |
Family
ID=60673474
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17206622.7A Withdrawn EP3499125A1 (en) | 2017-12-12 | 2017-12-12 | Pipe combustion chamber with ceramic cladding |
EP18810907.8A Active EP3707435B1 (en) | 2017-12-12 | 2018-11-15 | Pipe combustion chamber with ceramic cladding |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17206622.7A Withdrawn EP3499125A1 (en) | 2017-12-12 | 2017-12-12 | Pipe combustion chamber with ceramic cladding |
Country Status (4)
Country | Link |
---|---|
US (1) | US20210190319A1 (en) |
EP (2) | EP3499125A1 (en) |
KR (1) | KR102364131B1 (en) |
WO (1) | WO2019115129A1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102019204544A1 (en) | 2019-04-01 | 2020-10-01 | Siemens Aktiengesellschaft | Tube combustion chamber system and gas turbine system with such a tube combustion chamber system |
DE102020203017A1 (en) | 2020-03-10 | 2021-09-16 | Siemens Aktiengesellschaft | Combustion chamber with ceramic heat shield and seal |
CN112228903B (en) * | 2020-09-18 | 2022-07-01 | 西北工业大学 | Three-channel type combustion chamber flame tube wall surface structure with longitudinal vortex generator |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4838030A (en) * | 1987-08-06 | 1989-06-13 | Avco Corporation | Combustion chamber liner having failure activated cooling and dectection system |
DE4343319A1 (en) * | 1993-12-18 | 1995-06-22 | Abb Patent Gmbh | Combustion chamber with a ceramic lining |
US9127565B2 (en) * | 2008-04-16 | 2015-09-08 | Siemens Energy, Inc. | Apparatus comprising a CMC-comprising body and compliant porous element preloaded within an outer metal shell |
DE102012204162A1 (en) * | 2012-03-16 | 2013-09-19 | Siemens Aktiengesellschaft | Ring combustor bypass |
WO2015038293A1 (en) * | 2013-09-11 | 2015-03-19 | United Technologies Corporation | Combustor liner |
GB2540769A (en) * | 2015-07-27 | 2017-02-01 | Rolls Royce Plc | Combustor for a gas turbine engine |
DE102015215208B3 (en) * | 2015-08-10 | 2016-11-03 | Siemens Aktiengesellschaft | A combustor for a gas turbine and method for detecting heat shield element loss in the combustor |
US10648669B2 (en) * | 2015-08-21 | 2020-05-12 | Rolls-Royce Corporation | Case and liner arrangement for a combustor |
-
2017
- 2017-12-12 EP EP17206622.7A patent/EP3499125A1/en not_active Withdrawn
-
2018
- 2018-11-15 US US16/771,060 patent/US20210190319A1/en not_active Abandoned
- 2018-11-15 KR KR1020207019703A patent/KR102364131B1/en active IP Right Grant
- 2018-11-15 WO PCT/EP2018/081305 patent/WO2019115129A1/en unknown
- 2018-11-15 EP EP18810907.8A patent/EP3707435B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
KR102364131B1 (en) | 2022-02-18 |
WO2019115129A1 (en) | 2019-06-20 |
EP3499125A1 (en) | 2019-06-19 |
KR20200093045A (en) | 2020-08-04 |
US20210190319A1 (en) | 2021-06-24 |
EP3707435B1 (en) | 2021-09-15 |
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Inventor name: GRALKI, MATTHIAS Inventor name: GROTE, HOLGER Inventor name: TERTILT, MARC Inventor name: SCHMIDT, DANIEL Inventor name: KRUSCH, CLAUS Inventor name: HUEMBS, MARVIN |
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