CH268030A - Combustion chamber. - Google Patents
Combustion chamber.Info
- Publication number
- CH268030A CH268030A CH268030DA CH268030A CH 268030 A CH268030 A CH 268030A CH 268030D A CH268030D A CH 268030DA CH 268030 A CH268030 A CH 268030A
- Authority
- CH
- Switzerland
- Prior art keywords
- combustion chamber
- ribs
- wall
- chamber according
- partition
- Prior art date
Links
Classifications
-
- 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
- F23M5/08—Cooling thereof; Tube walls
- F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S60/00—Power plants
- Y10S60/909—Reaction motor or component composed of specific material
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
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)
Description
Chambre de combustion. L'invention a pour objet une chambre de combustion, par exemple une chambre de combustion de turbine à gaz.
Cette chambre de combustion est caracté risée selon l'invention en ce que l'en ceinte de combustion est limitée par une paroi eornprenarrt une cloison présentant du côté intérieur des nervures de fa çon à former des logements dans lesquels sont placées des bandes de matière réfrac taire, ces nervures étant creuses et engageant les bandes de matière réfractaire de façon à retenir eelles-ei dans leurs logements, les ner vures présentant chacune au moins un orifice par lequel de l'air de refroidissement passe dans l'enceinte de combustion,
et la cloison susmentionnée étant munie de trous qui com- muniquerit avec l'intérieur des nervures creuses.
Le dessin représente selrématiquement, à titre (l'exeiyrl)le, deux formes d'exécution de la chambre de combustion selon l'invention, ainsi qu'une variante de détail.
La fig. 1 montre, en coupe transversale, une partie d'une première forme d'exécution. La fig. 2 montre l'aspect intérieur de l'en ceinte de combustion de cette forme d'exécu tion.
La fig. 3 montre, en coupe transversale, une partie d'une deuxième forme d'exécution, et la fig. 4 montre, en coupe transversale, une nervure d'une variante de ces formes d'exécution.
Dans la forme d'exécution représentée à la fig. 1, une chemise evlindrique 1 entoure un espace de section annulaire 2 pour le pas sage de l'air de refroidissement, cet. espace entourant la paroi cylindrique de l'enceinte de combustion. Cette paroi comprend une cloi son cylindrique de révolution en métal 3 pré sentant du, côté intérieur des nervures métal liques 4 également espacées et soudées ou réu nies autrement à la cloison 3.
Dans les loge ments formés par la cloison 3 et les nervures 4 sont placées des bandes de matière réfrac taire 5, par exemple à base de zircone ou de carbure de silicium, qui s'étendent vers l'intérieur de l'enceinte de combustion au de là des bords libres des nervures. Les nervures 4 sont disposées suivant des plans radiaux et ont en section transversale la forme de coins allant en s'élargissant vers l'intérieur de l'en ceinte de combustion. De cette façon, les ban des 5, qui ont une section trapézoïdale, sont retenues dans leurs logements par engagement avec les nervures 4.
Ces nervures 4 sont creu ses et présentent des troue d'air 6 espacés con venablement le long de leur bord libre. Des trous d'air dans la cloison 3 permettent à l'air de passer dans l'enceinte de combustion par la voie des nervures creuses 4, cet air provenant de l'espace de section annulaire 2.
Dans la forme d'exécution de 1a fig. 3, la paroi limitant l'enceinte de combustion est constituée comme dans la chambre de coin- bastion de la fig. 1, sauf que les bandes de matière réfractaire 5 ne débordent pas les ner vures 4 et qu'un revêtement cylindrique 8 en métal résistant aux températures élevées, par exemple du molybdène ou un de ses alliages, s'appuie saur les surfaces internes de ces ban des 5.
L'espace entre la paroi limitant l'en ceinte de combustion et la chemise 1 est sub- divisé en deux parties de section annulaire coaxiales 9 et 10 au, moyen d'un écran cylin drique 11 de protection contre les radiations. Dansî l'espace 9 font saillie un certain nombre d'ailettes de refroidissement 12, disposées ra- dialement, espacées convenablement et fixées à la cloison 3 de la paroi limitant l'enceinte de combustion par soudure ou autrement.
De l'air de refroidissement provenant de l'es pace 9 pénètre dans les nervures creuses 4 par les trous 7 de la cloison 3 et s'échappe dans l'enceinte de combustion par les trous 6 de ces nervures qui correspondent à des trous du revêtement 8.
Ainsi que le montre la fig. 4, qui se rap porte à une variante des chambres de com bustion des fig. 1 à 3, les nervures 4 pour raient comprendre chacune deux bandes 13 de section transversale incurvée disposées de faon que leurs faces concaves soient opposées l'une à l'autre. Dans ce cas, l'air de refroi dissement provenant de l'espace 2 pénétrerait par les trous 7 de la cloison 3 dans l'espace compris entre les bandes 13 et s'échapperait dans l'enceinte de combustion entre les bords libres espacés de ces bandes 13.
Combustion chamber. The subject of the invention is a combustion chamber, for example a combustion chamber of a gas turbine.
This combustion chamber is characterized according to the invention in that the combustion chamber is limited by a wall eornprenarrt a partition having on the inner side ribs so as to form housings in which are placed bands of refractory material. silent, these ribs being hollow and engaging the bands of refractory material so as to retain them in their housings, the ribs each having at least one orifice through which the cooling air passes into the combustion chamber,
and the aforementioned partition being provided with holes which will communicate with the interior of the hollow ribs.
The drawing represents selrematically, as (the exeiyrl), two embodiments of the combustion chamber according to the invention, as well as a variant of detail.
Fig. 1 shows, in cross section, part of a first embodiment. Fig. 2 shows the interior appearance of the combustion chamber of this embodiment.
Fig. 3 shows, in cross section, part of a second embodiment, and FIG. 4 shows, in cross section, a rib of a variant of these embodiments.
In the embodiment shown in FIG. 1, an evlindrique jacket 1 surrounds an annular section space 2 for the passage of cooling air, this. space surrounding the cylindrical wall of the combustion chamber. This wall comprises a wall its cylindrical of revolution in metal 3 present on the inside of metal ribs 4 equally spaced and welded or otherwise joined to the wall 3.
In the housings formed by the partition 3 and the ribs 4 are placed strips of refractory material 5, for example based on zirconia or silicon carbide, which extend towards the inside of the combustion chamber at the bottom. hence the free edges of the ribs. The ribs 4 are arranged in radial planes and in cross section have the shape of wedges widening towards the inside of the combustion chamber. In this way, the ban des 5, which have a trapezoidal section, are retained in their housings by engagement with the ribs 4.
These ribs 4 are hollow and have air holes 6 suitably spaced along their free edge. Air holes in the partition 3 allow the air to pass into the combustion chamber via the hollow ribs 4, this air coming from the space of annular section 2.
In the embodiment of 1a fig. 3, the wall limiting the combustion chamber is made as in the corner-bastion chamber of FIG. 1, except that the bands of refractory material 5 do not extend beyond the ribs 4 and that a cylindrical coating 8 of metal resistant to high temperatures, for example of molybdenum or one of its alloys, rests on the internal surfaces of these ban of 5.
The space between the wall limiting the combustion chamber and the jacket 1 is subdivided into two parts of coaxial annular section 9 and 10 by means of a cylindrical shield 11 for protection against radiation. In the space 9 protrude a number of cooling fins 12, arranged radially, suitably spaced and fixed to the partition 3 of the wall bounding the combustion chamber by welding or otherwise.
Cooling air from space 9 enters the hollow ribs 4 through the holes 7 of the partition 3 and escapes into the combustion chamber through the holes 6 of these ribs which correspond to holes in the coating 8.
As shown in fig. 4, which relates to a variant of the combustion chambers of FIGS. 1 to 3, the ribs 4 could each comprise two bands 13 of curved cross section arranged so that their concave faces are opposite to each other. In this case, the cooling air coming from space 2 would penetrate through the holes 7 of the partition 3 into the space between the strips 13 and would escape into the combustion chamber between the free edges spaced apart. these bands 13.
Claims (1)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB830/46A GB602149A (en) | 1946-01-09 | 1946-01-09 | Improvements in and relating to combustion chamber linings |
Publications (1)
Publication Number | Publication Date |
---|---|
CH268030A true CH268030A (en) | 1950-04-30 |
Family
ID=9711219
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CH268030D CH268030A (en) | 1946-01-09 | 1947-01-09 | Combustion chamber. |
Country Status (5)
Country | Link |
---|---|
US (1) | US2548485A (en) |
CH (1) | CH268030A (en) |
FR (1) | FR939630A (en) |
GB (1) | GB602149A (en) |
NL (1) | NL69245C (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1021647B (en) * | 1954-03-03 | 1957-12-27 | Parsons & Marine Eng Turbine | Cylindrical heating or combustion space, especially for gas turbines |
Families Citing this family (44)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2686655A (en) * | 1949-09-02 | 1954-08-17 | Maschf Augsburg Nuernberg Ag | Joint between ceramic and metallic parts |
US2658332A (en) * | 1951-03-21 | 1953-11-10 | Carborundum Co | Fluid cooled, refractory, ceramic lined rocket structure |
US2823103A (en) * | 1952-04-02 | 1958-02-11 | Koppers Co Inc | High pressure gas producers |
BE535497A (en) * | 1954-02-26 | |||
US2787457A (en) * | 1954-05-14 | 1957-04-02 | Westinghouse Electric Corp | High temperature furnace |
US3229359A (en) * | 1962-07-05 | 1966-01-18 | Bruce E Kramer | Method of forming a refractory metal rocket nozzle |
US3170289A (en) * | 1962-07-05 | 1965-02-23 | Bruce E Kramer | Lightweight refractory metal structure |
DE1173734B (en) * | 1962-10-11 | 1964-07-09 | Siemens Ag | Combustion chamber, especially for gas turbines, with a lining made of refractory bricks |
US3321922A (en) * | 1964-10-29 | 1967-05-30 | Jr William T Latto | Small rocket engine |
US3429973A (en) * | 1965-09-02 | 1969-02-25 | Frederick H N Carter | Furnace construction |
GB1320482A (en) * | 1971-01-25 | 1973-06-13 | Secr Defence | Cooling of hot fluid ducts |
US3797236A (en) * | 1971-06-11 | 1974-03-19 | Rolls Royce | Annular combustion chamber with ceramic annular ring |
US3897200A (en) * | 1974-03-04 | 1975-07-29 | Howe Baker Eng | Cyclonic multi-fuel burner |
FR2400681A1 (en) * | 1977-08-18 | 1979-03-16 | Nord Pas Calais Houilleres | NEW OVEN WALLS USED AT HIGH TEMPERATURES |
JPS5857658B2 (en) * | 1980-04-02 | 1983-12-21 | 工業技術院長 | Heat shielding structure for walls exposed to high heat using ceramics |
US4499946A (en) * | 1981-03-10 | 1985-02-19 | Mason & Hanger-Silas Mason Co., Inc. | Enhanced oil recovery process and apparatus |
US4490110A (en) * | 1983-05-20 | 1984-12-25 | Jones William R | Plenum arrangement |
US4664618A (en) * | 1984-08-16 | 1987-05-12 | American Combustion, Inc. | Recuperative furnace wall |
US4637550A (en) * | 1985-10-01 | 1987-01-20 | The United States Of America As Represented By The Secretary Of The Air Force | Dual material exhaust nozzle flap |
US4898000A (en) * | 1986-04-14 | 1990-02-06 | Allied-Signal Inc. | Emergency power unit |
US5553455A (en) * | 1987-12-21 | 1996-09-10 | United Technologies Corporation | Hybrid ceramic article |
US5113660A (en) * | 1990-06-27 | 1992-05-19 | The United States Of America As Represented By The Secretary Of The Air Force | High temperature combustor liner |
RU2076275C1 (en) * | 1990-07-17 | 1997-03-27 | Сименс АГ | Length of pipe, flame tube in particular, with inner volume for direction of hot gas and thermal shield |
US5431020A (en) * | 1990-11-29 | 1995-07-11 | Siemens Aktiengesellschaft | Ceramic heat shield on a load-bearing structure |
US5224539A (en) * | 1991-06-14 | 1993-07-06 | Coen Company, Inc. | Cooling system for air heaters and the like |
CA2089285C (en) * | 1992-03-30 | 2002-06-25 | Stephen Winthrop Falls | Segmented centerbody for a double annular combustor |
DE4343319A1 (en) * | 1993-12-18 | 1995-06-22 | Abb Patent Gmbh | Combustion chamber with a ceramic lining |
US5636508A (en) * | 1994-10-07 | 1997-06-10 | Solar Turbines Incorporated | Wedge edge ceramic combustor tile |
DE19602731C1 (en) * | 1996-01-26 | 1997-07-10 | Daimler Benz Aerospace Ag | Reduced thermal stress wall structure for a rocket drive mechanism |
DE19704976C2 (en) * | 1997-01-29 | 1999-02-25 | Siemens Ag | Gas turbine system with a combustion chamber casing lined with ceramic stones |
US6021570A (en) * | 1997-11-20 | 2000-02-08 | Caterpillar Inc. | Annular one piece combustor liner |
EP1072573A1 (en) | 1999-07-30 | 2001-01-31 | Siemens Aktiengesellschaft | Method of making a refractory body and ceramic combustion chamber stone |
EP1288601B1 (en) * | 2001-08-28 | 2006-10-25 | Siemens Aktiengesellschaft | Heat shield brick and its use in a combustion chamber |
EP1302723A1 (en) * | 2001-10-15 | 2003-04-16 | Siemens Aktiengesellschaft | Lining for combustion chamber inside walls |
EP1422479B1 (en) * | 2002-11-22 | 2008-08-13 | Siemens Aktiengesellschaft | Chamber for the combustion of a fluid combustible mixture |
GB0305025D0 (en) * | 2003-03-05 | 2003-04-09 | Alstom Switzerland Ltd | Method and device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations |
US7553385B2 (en) * | 2004-11-23 | 2009-06-30 | United Technologies Corporation | Cold gas dynamic spraying of high strength copper |
US8359865B2 (en) * | 2010-02-04 | 2013-01-29 | United Technologies Corporation | Combustor liner segment seal member |
US9494081B2 (en) | 2013-05-09 | 2016-11-15 | Siemens Aktiengesellschaft | Turbine engine shutdown temperature control system with an elongated ejector |
WO2015022222A1 (en) * | 2013-08-15 | 2015-02-19 | Siemens Aktiengesellschaft | Heat shield having at least one helmholtz resonator |
EP3104079B1 (en) * | 2015-06-08 | 2018-10-31 | ANSALDO ENERGIA S.p.A. | Gas turbine combustion chamber having an anchorage device for heat-insulating tiles |
US10260750B2 (en) * | 2015-12-29 | 2019-04-16 | United Technologies Corporation | Combustor panels having angled rail |
US10619854B2 (en) | 2016-11-30 | 2020-04-14 | United Technologies Corporation | Systems and methods for combustor panel |
US11204204B2 (en) * | 2019-03-08 | 2021-12-21 | Toyota Motor Engineering & Manufacturing North America, Inc. | Acoustic absorber with integrated heat sink |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US792667A (en) * | 1902-11-01 | 1905-06-20 | J S Rogers | Process of burning hydrocarbons or other combustibles. |
US1757698A (en) * | 1927-08-15 | 1930-05-06 | Allen Sherman Hoff Co | Side-wall seal |
US2092537A (en) * | 1935-10-14 | 1937-09-07 | Andrew H Stewart | Furnace wall |
US2183313A (en) * | 1938-07-07 | 1939-12-12 | Robert H Goddard | Combustion chamber for aircraft |
US2186740A (en) * | 1939-02-17 | 1940-01-09 | Teeters Thomas | Furnace construction |
US2348754A (en) * | 1942-08-06 | 1944-05-16 | Allis Chalmers Mfg Co | Turbine apparatus |
US2451146A (en) * | 1944-06-05 | 1948-10-12 | Kellogg M W Co | Internally insulation lined vessel |
US2468902A (en) * | 1944-10-20 | 1949-05-03 | Tech Studien Ag | Double-walled body for hot gases or vapors under superatmospheric pressure |
-
0
- NL NL69245D patent/NL69245C/xx active
-
1946
- 1946-01-09 GB GB830/46A patent/GB602149A/en not_active Expired
-
1947
- 1947-01-08 US US720896A patent/US2548485A/en not_active Expired - Lifetime
- 1947-01-09 CH CH268030D patent/CH268030A/en unknown
- 1947-01-09 FR FR939630D patent/FR939630A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1021647B (en) * | 1954-03-03 | 1957-12-27 | Parsons & Marine Eng Turbine | Cylindrical heating or combustion space, especially for gas turbines |
Also Published As
Publication number | Publication date |
---|---|
NL69245C (en) | |
FR939630A (en) | 1948-11-19 |
US2548485A (en) | 1951-04-10 |
GB602149A (en) | 1948-05-20 |
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