US2548485A - Combustion chamber lining - Google Patents

Combustion chamber lining Download PDF

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Publication number
US2548485A
US2548485A US720896A US72089647A US2548485A US 2548485 A US2548485 A US 2548485A US 720896 A US720896 A US 720896A US 72089647 A US72089647 A US 72089647A US 2548485 A US2548485 A US 2548485A
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US
United States
Prior art keywords
combustion chamber
ribs
wall
strips
refractory
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
Application number
US720896A
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English (en)
Inventor
Lubbock Isaac
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.)
Shell Development Co
Original Assignee
Shell Development Co
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 Shell Development Co filed Critical Shell Development Co
Application granted granted Critical
Publication of US2548485A publication Critical patent/US2548485A/en
Anticipated expiration legal-status Critical
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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

Definitions

  • This invention concerns improvements in relation to the lining of combustion chambers, such for example as are used for gas turbines where a very high rate of heat release has to be maintained in a comparatively small volume under high pressure conditions.
  • This invention is applicable to various known forms of combustion chambers for the purpose of protecting the walls of the combustion chamber and adjoining parts from being subjected to excessive temperatures.
  • the temperature ruling in the primary zone where the ratio of air to fuel is not far removed from that required stoichiometrically isusually of the order of 1400" C. or more even though the final products of combustion which pass to the turbine are ultimately reduced to approximately 600C. to 1000 0. according to the temperature which the turbine wheel can withstand;
  • a' combustion chamber lining comprises strips of refractory material located in recesses bounded by a wall of the combustion chamber and-ribs whichextend therefrom so as to key the strips-in the recesses.
  • the ribs proj ect inwardly and convergingly, e. g. radially with respect to the curvature of the wall.
  • This walland the ribs may be made of metal and may be welded or. otherwise attached tog-ether.
  • the ribs may bedisposed at comparatively small intervals apart so that therefractory lining will be made in long narrow strips which may be inserted into the recesses by sliding them in from one end, the strips being of trapezoidal cross section so that they are retained in the recesses bounded by the converging opposing sides of adjacent ribs.
  • the refractory strips may extend inwards be By thus making piecesof refractory thicker than the extent of protrusion of the retaining radial ribs a measure of protection for the edge of the ribs, fromthe flame, isprovided.
  • each rib has substantially parallel sides
  • the ribs, in cross-section, widen towards their projection ends.
  • a better looking effect is on the edge nearest the combustion chamber centre line.
  • the cooling medium circulating within the'hollow ribs may be liquid or gas e. g. 'air, and in the latter case the projection ends of the hollow ribs may have ports for the outlet of cooling fluid into the combustion space.
  • the walls of the combustion chamber may have holes communicating with the interior of the hollow ribs so that the cooling fluid is supplied from a cooling space surrounding the external surface of the combustion chamber wall.
  • lining according to the invention may be applied to any shape of combustion chamber which may be of the cylindrical or annular type.
  • Figure 4 is a cross-section of a detail showing a curved form of rib.
  • a cylindrical jacket I surrounds an annular space 2, for the passage of air or liquid cooling medium, bounded on its inner side by a combustion chamber wall 3.
  • Each hollow rib has air holes 6 at suitable intervals along its projection end. Air holes 1 in the wall 3 allow air to pass into the combustion space from the cooling space 2 via the hollow ribs 4.
  • the ribs 4 are of hollow wedgeshaped form, but there are no air holes either in In a further embodiment of the invention, as
  • the inner surface of the refractory lining is wholly or partly covered by a high temperature resisting metal lining, e. g. of molybdenum or its alloys.
  • a high temperature resisting metal lining e. g. of molybdenum or its alloys.
  • Such inner lining or shroud or grating of high temperature resisting metal is not required to carry any substantial load, its purpose being merely to prevent broken pieces of refractor material from being carried away in the flame products.
  • refractory The particular nature of the refractory is immaterial so long as it is capable of withstanding satisfactorily for prolongedperiods the temperatures involved. For very high temperatures a refractory having a zirconia base is suitable or a carborundum type of refractory where high conductivity is necessary. r
  • the outer surface of the inner wall of the combustion chamber may be provided with cooling ribs or fins, secured by welding or otherwise, and a radiation shield may be provided between the inner wall and an outer wall or jacket, the space between the inner wall and the outer wall of the jacket being used for the passage of a cooling medium.
  • each rib is composed of two pieces of curved cross-section arranged to have their respectiveconcave faces opposite each other, the sides of thev refractory strips being concave so as to be held 1 drawings, in which;
  • Figure 1 is across-section of a portionpf'a cylindrical combustion chamber according to the embodiment of the invention in which the ribs are hollow-and wedge-shaped.
  • Figure 2 is an underside plan view of Figure 1.
  • Figure 3 is a cross-section of an'embodiment incorporating a pluralityof cooling zones
  • the space between the wall 3 and the jacket i is divided into two concentric annular portions 9 and ID by means of a cylindrical radiation shield H.
  • the space 9 is provided with a number of cooling fins I2 arranged radially at suitable intervals and secured to the wall 3 by welding or otherwise.
  • the cooling zones thus comprise respectively the space 9, the space H], and the interiors of the hollow ribs 4.
  • the rib is composed of two pieces [3 of curved cross-section arranged to have their concave faces opposite each other.
  • a combustion chamber having a chamber wall and a liner comprising a plurality of hollow ribs extending inwardly from said wall, each rib having a pair of side walls, one on either side of an intervening hollow space, the outer surfaces of said side walls diverging gradually from said wall and the adjacent outer surfaces of adjacent ribs converging toward each other away from said wall to define recesses bounded by said wall and said surfaces of the ribs; and strips of refractory material located in said recesses and shaped to be retainingly keyed within the respective recesses throughout a substantial thickness of said strips.
  • combustion chamber and liner according to claim 1 wherein the said combustion chamber wall is curved cylindrically and the said hollow ribs extend radially to said wall curvature and extend substantially lengthwise with respect to the cylinder.
  • a combustion chamber and liner according to claim 1 having a high temperature resisting metal lining covering to a substantial extent the inner, exposed surfaces of the refractory lining strips.
  • a combustion chamber comprising an outer chamber wall; an inner chamber wall spaced therefrom to provide a space for the passage of cooling fluid; cooling fins on the outer surface of the inner wall; and a liner comprising a plurality of hollow ribs extending inwardly from said inner wall, the adjacent outer surfaces of adjacent ribs convergin toward each other away from said inner wall to define recesses bounded by said surfaces of the ribs and by said inner wall; and a plurality of strips of refractory material extending substantially parallel to the axis of said chamber located in said recesses and shaped to be retainingly keyed therein by the said surfaces of the ribs.
  • a combustion chamber having a combustion chamber wall and a liner comprising a plurality of ribs projecting inwardly and convergingly from said chamber wall, said ribs being hollow and the combustion chamber wall having holes extending therethrough communicating with the interiors of the hollow ribs; and a plurality of strips of refractory material retainingly keyed in the recesses formed between said ribs.
  • a combustion chamber and liner as claimed in claim 7 in which the chamber wall is curved concavely inwards and the ribs are radial to the curvature of the wall.
  • a combustion chamber and liner as claimed in claim 7 in which the chamber wall and the ribs are of metal and are welded together.
  • a combustion chamber and liner as claimed in claim 7 in which the refractory strips extend inwardly beyond the ends of the ribs.
  • a combustion chamber and liner as claimed in claim 7 in which the ribs have cross sections that widen from the chamber wall towards their projecting ends.

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)
US720896A 1946-01-09 1947-01-08 Combustion chamber lining Expired - Lifetime US2548485A (en)

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
US2548485A true US2548485A (en) 1951-04-10

Family

ID=9711219

Family Applications (1)

Application Number Title Priority Date Filing Date
US720896A Expired - Lifetime US2548485A (en) 1946-01-09 1947-01-08 Combustion chamber lining

Country Status (5)

Country Link
US (1) US2548485A (de)
CH (1) CH268030A (de)
FR (1) FR939630A (de)
GB (1) GB602149A (de)
NL (1) NL69245C (de)

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2658332A (en) * 1951-03-21 1953-11-10 Carborundum Co Fluid cooled, refractory, ceramic lined rocket structure
US2787457A (en) * 1954-05-14 1957-04-02 Westinghouse Electric Corp High temperature furnace
US2823103A (en) * 1952-04-02 1958-02-11 Koppers Co Inc High pressure gas producers
DE1052750B (de) * 1954-02-26 1959-03-12 Rolls Royce Wand einer Brennkammer fuer fluessigen Kraftstoff, insbesondere in Gasturbinen
US2915877A (en) * 1954-03-03 1959-12-08 Parsons & Marine Eng Turbine Cylindrical furnaces
DE1173734B (de) * 1962-10-11 1964-07-09 Siemens Ag Brennkammer, insbesondere fuer Gasturbinen, mit einer aus feuerfesten Steinen aufgebauten Auskleidung
US3170289A (en) * 1962-07-05 1965-02-23 Bruce E Kramer Lightweight refractory metal structure
US3229359A (en) * 1962-07-05 1966-01-18 Bruce E Kramer Method of forming a refractory metal rocket nozzle
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
US3737152A (en) * 1971-01-25 1973-06-05 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
US4193355A (en) * 1977-04-18 1980-03-18 Houilleres Du Bassin Du Nord Et Du Pas De Calais Furnace walls which can be used at high temperatures
US4441324A (en) * 1980-04-02 1984-04-10 Kogyo Gijutsuin Thermal shield structure with ceramic wall surface exposed to high temperature
US4490110A (en) * 1983-05-20 1984-12-25 Jones William R Plenum arrangement
US4499946A (en) * 1981-03-10 1985-02-19 Mason & Hanger-Silas Mason Co., Inc. Enhanced oil recovery process and apparatus
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
US4664618A (en) * 1984-08-16 1987-05-12 American Combustion, Inc. Recuperative furnace wall
US4898000A (en) * 1986-04-14 1990-02-06 Allied-Signal Inc. Emergency power unit
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
US5224539A (en) * 1991-06-14 1993-07-06 Coen Company, Inc. Cooling system for air heaters and the like
US5375420A (en) * 1992-03-30 1994-12-27 General Electric Company Segmented centerbody for a double annular combustor
DE4343319A1 (de) * 1993-12-18 1995-06-22 Abb Patent Gmbh Brennkammer mit keramischer Auskleidung
US5431020A (en) * 1990-11-29 1995-07-11 Siemens Aktiengesellschaft Ceramic heat shield on a load-bearing structure
US5553455A (en) * 1987-12-21 1996-09-10 United Technologies Corporation Hybrid ceramic article
US5636508A (en) * 1994-10-07 1997-06-10 Solar Turbines Incorporated Wedge edge ceramic combustor tile
US5899060A (en) * 1996-01-26 1999-05-04 Daimler-Benz Aerospace Ag Wall structure for fuel-cooled rocket engine walls
US6021570A (en) * 1997-11-20 2000-02-08 Caterpillar Inc. Annular one piece combustor liner
EP1288601A1 (de) * 2001-08-28 2003-03-05 Siemens Aktiengesellschaft Hitzeschildstein sowie Verwendung eines Hitzeschildsteins in einer Brennkammer
US20030079475A1 (en) * 2001-10-15 2003-05-01 Milan Schmahl Lining for inner walls of combustion chambers
EP1422479A1 (de) * 2002-11-22 2004-05-26 Siemens Aktiengesellschaft Brennkammer zur Verbrennung eines brennbaren Fluidgemisches
US20040172948A1 (en) * 2003-03-05 2004-09-09 Valter Bellucci Method and device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations
US20090282832A1 (en) * 2004-11-23 2009-11-19 United Technologies Corporation Cold gas dynamic spraying of high strength copper
WO2015022222A1 (de) * 2013-08-15 2015-02-19 Siemens Aktiengesellschaft Hitzeschild mit mindestens einem helmholtzresonator
EP2354660A3 (de) * 2010-02-04 2015-03-18 United Technologies Corporation Abdichtungselement für Brennkammerwandsegment
US9494081B2 (en) 2013-05-09 2016-11-15 Siemens Aktiengesellschaft Turbine engine shutdown temperature control system with an elongated ejector
EP3104079A1 (de) * 2015-06-08 2016-12-14 A.S.EN. Ansaldo Sviluppo Energia S.r.l. Verankerungsvorrichtung für wärmeisolierende kacheln von brennkammern von gasturbinen
US20170184306A1 (en) * 2015-12-29 2017-06-29 United Technologies Corporation Combustor panels having angled rail
EP3330612A1 (de) * 2016-11-30 2018-06-06 United Technologies Corporation System und verfahren für eine brennkammerplatte
US11204204B2 (en) * 2019-03-08 2021-12-21 Toyota Motor Engineering & Manufacturing North America, Inc. Acoustic absorber with integrated heat sink

Families Citing this family (4)

* Cited by examiner, † Cited by third party
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
RU2076275C1 (ru) * 1990-07-17 1997-03-27 Сименс АГ Отрезок трубы, в частности жаровая труба с внутренним объемом для направления горячего газа и теплозащитным экраном
DE19704976C2 (de) * 1997-01-29 1999-02-25 Siemens Ag Gasturbinenanlage mit einem mit Keramiksteinen ausgekleideten Brennkammergehäuse
EP1072573A1 (de) 1999-07-30 2001-01-31 Siemens Aktiengesellschaft Verfahren zur Herstellung eines feuerfesten Bauteils und keramischer Brennkammerstein

Citations (8)

* Cited by examiner, † Cited by third party
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

Patent Citations (8)

* Cited by examiner, † Cited by third party
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

Cited By (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
DE1052750B (de) * 1954-02-26 1959-03-12 Rolls Royce Wand einer Brennkammer fuer fluessigen Kraftstoff, insbesondere in Gasturbinen
US2919549A (en) * 1954-02-26 1960-01-05 Rolls Royce Heat-resisting wall structures
US2915877A (en) * 1954-03-03 1959-12-08 Parsons & Marine Eng Turbine Cylindrical furnaces
US2787457A (en) * 1954-05-14 1957-04-02 Westinghouse Electric Corp High temperature furnace
US3170289A (en) * 1962-07-05 1965-02-23 Bruce E Kramer Lightweight refractory metal structure
US3229359A (en) * 1962-07-05 1966-01-18 Bruce E Kramer Method of forming a refractory metal rocket nozzle
DE1173734B (de) * 1962-10-11 1964-07-09 Siemens Ag Brennkammer, insbesondere fuer Gasturbinen, mit einer aus feuerfesten Steinen aufgebauten Auskleidung
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
US3737152A (en) * 1971-01-25 1973-06-05 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
US4193355A (en) * 1977-04-18 1980-03-18 Houilleres Du Bassin Du Nord Et Du Pas De Calais Furnace walls which can be used at high temperatures
US4441324A (en) * 1980-04-02 1984-04-10 Kogyo Gijutsuin Thermal shield structure with ceramic wall surface exposed to high temperature
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
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
US5375420A (en) * 1992-03-30 1994-12-27 General Electric Company Segmented centerbody for a double annular combustor
DE4343319A1 (de) * 1993-12-18 1995-06-22 Abb Patent Gmbh Brennkammer mit keramischer Auskleidung
US5636508A (en) * 1994-10-07 1997-06-10 Solar Turbines Incorporated Wedge edge ceramic combustor tile
US5899060A (en) * 1996-01-26 1999-05-04 Daimler-Benz Aerospace Ag Wall structure for fuel-cooled rocket engine walls
US6021570A (en) * 1997-11-20 2000-02-08 Caterpillar Inc. Annular one piece combustor liner
US6711899B2 (en) * 2001-08-28 2004-03-30 Siemens Aktiengesellschaft Heat shield block and use of a heat shield block in a combustion chamber
EP1288601A1 (de) * 2001-08-28 2003-03-05 Siemens Aktiengesellschaft Hitzeschildstein sowie Verwendung eines Hitzeschildsteins in einer Brennkammer
US20030056515A1 (en) * 2001-08-28 2003-03-27 Ulrich Bast Heat shield block and use of a heat shield block in a cobustion chamber
US20030079475A1 (en) * 2001-10-15 2003-05-01 Milan Schmahl Lining for inner walls of combustion chambers
US6840047B2 (en) * 2001-10-15 2005-01-11 Siemens Aktiengesellschaft Lining for inner walls of combustion chambers
US20050097894A1 (en) * 2002-11-11 2005-05-12 Peter Tiemann Combustion chamber for combusting a combustible fluid mixture
EP1422479A1 (de) * 2002-11-22 2004-05-26 Siemens Aktiengesellschaft Brennkammer zur Verbrennung eines brennbaren Fluidgemisches
CN100370177C (zh) * 2002-11-22 2008-02-20 西门子公司 用于燃烧一种可燃烧的液态混合燃料的燃烧室
US7322196B2 (en) 2002-11-22 2008-01-29 Siemens Aktiengesellschaft Combustion chamber for combusting a combustible fluid mixture
US7065971B2 (en) * 2003-03-05 2006-06-27 Alstom Technology Ltd. Device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations
US20040172948A1 (en) * 2003-03-05 2004-09-09 Valter Bellucci Method and device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations
US20090282832A1 (en) * 2004-11-23 2009-11-19 United Technologies Corporation Cold gas dynamic spraying of high strength copper
EP2354660A3 (de) * 2010-02-04 2015-03-18 United Technologies Corporation Abdichtungselement für Brennkammerwandsegment
US9494081B2 (en) 2013-05-09 2016-11-15 Siemens Aktiengesellschaft Turbine engine shutdown temperature control system with an elongated ejector
WO2015022222A1 (de) * 2013-08-15 2015-02-19 Siemens Aktiengesellschaft Hitzeschild mit mindestens einem helmholtzresonator
EP3104079A1 (de) * 2015-06-08 2016-12-14 A.S.EN. Ansaldo Sviluppo Energia S.r.l. Verankerungsvorrichtung für wärmeisolierende kacheln von brennkammern von gasturbinen
US20170184306A1 (en) * 2015-12-29 2017-06-29 United Technologies Corporation Combustor panels having angled rail
US10260750B2 (en) * 2015-12-29 2019-04-16 United Technologies Corporation Combustor panels having angled rail
EP3330612A1 (de) * 2016-11-30 2018-06-06 United Technologies Corporation System und verfahren für eine brennkammerplatte
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

Also Published As

Publication number Publication date
CH268030A (fr) 1950-04-30
NL69245C (de)
GB602149A (en) 1948-05-20
FR939630A (fr) 1948-11-19

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