GB790292A - Improvements in or relating to gas-turbine engine combustion equipment - Google Patents

Improvements in or relating to gas-turbine engine combustion equipment

Info

Publication number
GB790292A
GB790292A GB5813/54A GB581354A GB790292A GB 790292 A GB790292 A GB 790292A GB 5813/54 A GB5813/54 A GB 5813/54A GB 581354 A GB581354 A GB 581354A GB 790292 A GB790292 A GB 790292A
Authority
GB
United Kingdom
Prior art keywords
pieces
wall
mosaic
series
webs
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
Application number
GB5813/54A
Inventor
Lionel Haworth
Ralph John Shire
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of GB790292A publication Critical patent/GB790292A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78Other construction of jet pipes
    • F02K1/82Jet pipe walls, e.g. liners
    • F02K1/822Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002Wall structures
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/16Two dimensionally sectional layer
    • Y10T428/163Next to unitary web or sheet of equal or greater extent
    • Y10T428/164Continuous two dimensionally sectional layer
    • Y10T428/166Glass, ceramic, or metal sections [e.g., floor or wall tile, etc.]

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)
  • Gasket Seals (AREA)

Abstract

790,292. Generating combustion products under pressure; combustion chamber walls. ROLLS-ROYCE, Ltd. Jan. 26, 1955 [Feb. 26, 1954], No. 5813/54. Class 51 (1). Gas-turbine engine combustion equipment comprises a first wall which defines a combustion space and a second wall spaced from the first on the side thereof remote from the combustion space, pressure cooling air being fed to the space between the walls, the first wall being formed of a multiplicity of relatively small pieces arranged mosaic-wise with their edges unjoined but close to one another. At least those edges of adjacent pieces which extend in directions transverse to the direction of gas flow through the equipment afford between them restricted air leakage flow passages into the combustion space whereby the leakage flow of air flows over substantially the whole of the interior surface of the first wall. The combustion equipment shown in Fig. 1 comprises an air casing 10a and a flame tube disposed therein, the flame tube wall comprising an outer wall 10 and an inner wall formed by a number of small mosaic pieces 12 which are formed with integral stems 13 which pass through apertures in the outer wall 10 and are welded or riveted thereto. The stems may be solid or may have air inlet bores 16 through them; the bores may be of venturi shape. The mosaic pieces may be of rectangular, triangular or hexagonal shape, and openings through the flame tube wall may be formed by apertures such as 11 in the outer wall 10 and by omitting the mosaic pieces in line therewith. In a second embodiment, Fig. 2, series of holes are drilled at right angles to each other in a thick plate and one surface of the plate is formed with series of slots 23, 24 in line with the axes of the drilled holes, thereby forming small mosaic pieces 25 which are supported by the stem pieces 22 from the continuous outer wall 26. In Fig. 3 a series of H- section metal strips are disposed side-by-side and the flanges 30 at one side are connected together by welding while a series of saw cuts 32 are made across the flanges 31 at the other side thereby forming a number of mosaic pieces 33. A series of holes 36 are drilled through the webs 35 of the H-section strips which thus divide the webs into a number of pieces, each supporting a mosaic piece 33 from the outer wall formed by the flanges 30. In Fig. 4 a plate 40 has a series of parallel fins thereon, the fins being slotted at 41 to produce a series of short webs 42. A second sheet 43 is attached by welding to the webs 42 and series of slots 44 are formed in the plate 40 to produce a number of mosaic pieces 45, each supported by a web 42. In Fig. 5a a flame tube wall is formed by winding a single strip of H-section spirally, the mosaic pieces 33 being formed as in the embodiment of Fig. 3. Fig. 6 shows a flame tube in which mosaic pieces are supported on a structure comprising longitudinal rods 62 mounted in end rings 63, 64, intermediate rings 65 being disposed between the end rings. The mosaic pieces comprise sheet metal pieces 66 having tabs at their circumferential ends, the tabs being hooked over the rods 62. In a similar construction the mosaic pieces are formed by casting, one end of each piece having a bore by which it is mounted on a rod 62, and the other end having a tongue which engages a groove formed in the end of the adjacent mosaic piece. The flame tube shown in Fig. 8, is formed by a number of H-section strips disposed longitudinally, similar to the construction of Fig. 3. Circumferentiallyextending slots 32a are formed in the inner flanges to provide the mosaic pieces 33, while similar slots formed in the outer flanges 30 and webs 35 have ring members 38 welded therein to divide the passages between the webs 35 into a number of axially separated sections. Air is admitted to the spaces between the webs 35 through holes 37. It is stated in the Provisional Specification that the constructions are applicable to furnace walls and combustion chambers generally. Specification 790,293 is referred to.
GB5813/54A 1954-02-26 1954-02-26 Improvements in or relating to gas-turbine engine combustion equipment Expired GB790292A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB331954X 1954-02-26
GB260155X 1955-01-26

Publications (1)

Publication Number Publication Date
GB790292A true GB790292A (en) 1958-02-05

Family

ID=26258006

Family Applications (2)

Application Number Title Priority Date Filing Date
GB4219/57A Expired GB790293A (en) 1954-02-26 1954-02-26 Improvements in or relating to heat-resisting wall structures for gas-turbine enginecombustion equipment
GB5813/54A Expired GB790292A (en) 1954-02-26 1954-02-26 Improvements in or relating to gas-turbine engine combustion equipment

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GB4219/57A Expired GB790293A (en) 1954-02-26 1954-02-26 Improvements in or relating to heat-resisting wall structures for gas-turbine enginecombustion equipment

Country Status (6)

Country Link
US (1) US2919549A (en)
BE (1) BE535497A (en)
CH (1) CH331954A (en)
DE (1) DE1052750B (en)
FR (1) FR1122030A (en)
GB (2) GB790293A (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3082601A (en) * 1958-05-08 1963-03-26 Daimler Benz Ag Rocket combustion chamber
DE1211441B (en) * 1961-12-05 1966-02-24 Ass Elect Ind Combustion chamber, especially for gas turbine systems
FR2418867A1 (en) * 1978-03-01 1979-09-28 Gen Electric LOW CALORIFIC GAS COMBUSTION CHAMBER
FR2479951A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp INTERIOR TRIM OF COMBUSTION CHAMBER
FR2479900A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp INTERIOR TRIM OF COMBUSTION CHAMBER
FR2493920A1 (en) * 1980-11-08 1982-05-14 Rolls Royce AIR CIRCULATION COOLING WALL FOR A GAS TURBINE ENGINE COMBUSTION CHAMBER
GB2117506A (en) * 1982-03-25 1983-10-12 Nu Way Energy Ltd Burner for gaseous fuels
GB2173891A (en) * 1985-04-05 1986-10-22 Agency Ind Science Techn Gas turbine combustor
EP0204988A1 (en) * 1985-06-04 1986-12-17 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Flame tube
EP0224817A1 (en) * 1985-12-02 1987-06-10 Siemens Aktiengesellschaft Heat shield arrangement, especially for the structural components of a gas turbine plant
GB2193564A (en) * 1986-07-24 1988-02-10 W B Black & Sons Improvements in lining a furnace with a refractory material
EP0741268A1 (en) * 1995-05-03 1996-11-06 United Technologies Corporation Liner panel for a gas turbine combustor wall
FR2752916A1 (en) * 1996-09-05 1998-03-06 Snecma THERMAL PROTECTIVE SHIRT FOR TURBOREACTOR COMBUSTION CHAMBER
EP0895027A1 (en) * 1997-07-28 1999-02-03 Abb Research Ltd. Ceramic lining

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DE1168929B (en) * 1959-03-06 1964-04-30 Summa Kessel G M B H Und Co K Tubular heat exchanger element
US3154914A (en) * 1959-12-12 1964-11-03 Bolkow Entwicklungen Kg Rocket engine construction
DE1159694B (en) * 1960-08-26 1963-12-19 United Aircraft Corp Injection head for a liquid rocket
CH399075A (en) * 1962-07-26 1966-03-31 Bbc Brown Boveri & Cie Combustion chamber, especially for magnetogasdynamic machines
DE1225331B (en) * 1962-07-26 1966-09-22 Bbc Brown Boveri & Cie Cooled combustion chamber for the highest temperatures
GB1055234A (en) * 1963-04-30 1967-01-18 Hitachi Ltd Ultra-high temperature combustion chambers
US3899876A (en) * 1968-11-15 1975-08-19 Secr Defence Brit Flame tube for a gas turbine combustion equipment
US3545202A (en) * 1969-04-02 1970-12-08 United Aircraft Corp Wall structure and combustion holes for a gas turbine engine
GB1283953A (en) * 1969-06-19 1972-08-02 Rolls Royce Wall for hot fluid streams
US4174608A (en) * 1972-08-15 1979-11-20 Stal-Laval Turbin Ab Combustion chamber for a gas turbine
US4614082A (en) * 1972-12-19 1986-09-30 General Electric Company Combustion chamber construction
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
SE375583B (en) * 1973-05-22 1975-04-21 United Turbine Ab & Co
US3910036A (en) * 1974-04-05 1975-10-07 Gen Motors Corp Igniter installation for combustor with ceramic liner
GB1550368A (en) * 1975-07-16 1979-08-15 Rolls Royce Laminated materials
GB1552132A (en) * 1975-11-29 1979-09-12 Rolls Royce Combustion chambers for gas turbine engines
GB1564608A (en) * 1975-12-20 1980-04-10 Rolls Royce Means for cooling a surface by the impingement of a cooling fluid
US4158949A (en) * 1977-11-25 1979-06-26 General Motors Corporation Segmented annular combustor
GB2049152B (en) * 1979-05-01 1983-05-18 Rolls Royce Perforate laminated material
CH643050A5 (en) * 1979-10-01 1984-05-15 Proizv Ob Nevsky Z Im V I Gas turbine with ring combustion chamber.
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
US4302941A (en) * 1980-04-02 1981-12-01 United Technologies Corporation Combuster liner construction for gas turbine engine
US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
US4664618A (en) * 1984-08-16 1987-05-12 American Combustion, Inc. Recuperative furnace wall
US4642993A (en) * 1985-04-29 1987-02-17 Avco Corporation Combustor liner wall
US5639531A (en) * 1987-12-21 1997-06-17 United Technologies Corporation Process for making a 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
US5233798A (en) * 1991-03-06 1993-08-10 Shaw Clive A Enabling assembly
US5184455A (en) * 1991-07-09 1993-02-09 The United States Of America As Represented By The Secretary Of The Air Force Ceramic blanket augmentor liner
US5216886A (en) * 1991-08-14 1993-06-08 The United States Of America As Represented By The Secretary Of The Air Force Segmented cell wall liner for a combustion chamber
US5331816A (en) * 1992-10-13 1994-07-26 United Technologies Corporation Gas turbine engine combustor fiber reinforced glass ceramic matrix liner with embedded refractory ceramic tiles
US5333443A (en) * 1993-02-08 1994-08-02 General Electric Company Seal assembly
US5605046A (en) * 1995-10-26 1997-02-25 Liang; George P. Cooled liner apparatus
TW360744B (en) * 1996-07-15 1999-06-11 Siemens Ag Equipment for fixing a covering sheet metal in the waste-gas flue of a gas turbine as well as halting
US5758504A (en) * 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner
EP1006315B1 (en) 1998-11-30 2004-01-21 ALSTOM (Switzerland) Ltd Ceramic lining for a combustion chamber
US6213714B1 (en) * 1999-06-29 2001-04-10 Allison Advanced Development Company Cooled airfoil
US6402470B1 (en) * 1999-10-05 2002-06-11 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
GB9926257D0 (en) * 1999-11-06 2000-01-12 Rolls Royce Plc Wall elements for gas turbine engine combustors
EP1284390A1 (en) * 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Thermal shield for a component carrying hot gases, especially for structural components of gas turbines
US6830437B2 (en) * 2002-12-13 2004-12-14 General Electric Company Assembly containing a composite article and assembly method therefor
EP1528343A1 (en) * 2003-10-27 2005-05-04 Siemens Aktiengesellschaft Refractory tile with reinforcing members embedded therein, as liner for gas turbine combustion chamber
DE102004044852A1 (en) * 2004-09-10 2006-03-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Hot gas chamber and shingle for a hot gas chamber
GB0601413D0 (en) * 2006-01-25 2006-03-08 Rolls Royce Plc Wall elements for gas turbine engine combustors
EP2094964A4 (en) * 2006-12-19 2013-05-01 Volvo Aero Corp Wall of a rocket engine
US8435007B2 (en) * 2008-12-29 2013-05-07 Rolls-Royce Corporation Hybrid turbomachinery component for a gas turbine engine
EP2233835A1 (en) * 2009-03-23 2010-09-29 Siemens Aktiengesellschaft Combustion chamber brazed with ceramic inserts
GB0913580D0 (en) * 2009-08-05 2009-09-16 Rolls Royce Plc Combustor tile
US8959886B2 (en) * 2010-07-08 2015-02-24 Siemens Energy, Inc. Mesh cooled conduit for conveying combustion gases
US8894363B2 (en) 2011-02-09 2014-11-25 Siemens Energy, Inc. Cooling module design and method for cooling components of a gas turbine system
US9243801B2 (en) * 2012-06-07 2016-01-26 United Technologies Corporation Combustor liner with improved film cooling
GB201403404D0 (en) * 2014-02-27 2014-04-16 Rolls Royce Plc A combustion chamber wall and a method of manufacturing a combustion chamber wall
GB201501817D0 (en) * 2015-02-04 2015-03-18 Rolls Royce Plc A combustion chamber and a combustion chamber segment
EP3317584A1 (en) * 2015-06-30 2018-05-09 Siemens Energy, Inc. Hybrid component comprising a metal-reinforced ceramic matrix composite material
GB201514390D0 (en) * 2015-08-13 2015-09-30 Rolls Royce Plc A combustion chamber and a combustion chamber segment
US10577944B2 (en) * 2017-08-03 2020-03-03 General Electric Company Engine component with hollow turbulators
US11208899B2 (en) * 2018-03-14 2021-12-28 General Electric Company Cooling assembly for a turbine assembly
US10968750B2 (en) 2018-09-04 2021-04-06 General Electric Company Component for a turbine engine with a hollow pin
US11506383B2 (en) * 2020-10-09 2022-11-22 Pratt & Whitney Canada Corp Combustor liner and method of operating same

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US814949A (en) * 1903-10-27 1906-03-13 Ellis F Edgar Boiler-furnace.
US2061822A (en) * 1935-04-12 1936-11-24 Chicago Retort & Fire Brick Co Furnace wall and block unit for making the same
GB597151A (en) * 1943-03-13 1948-01-20 Claude Albert Bonvillian Improvements in apparatus for the combustion of fuel
NL69245C (en) * 1946-01-09
CH255541A (en) * 1947-05-12 1948-06-30 Bbc Brown Boveri & Cie Cooled metal combustion chamber for generating heating and propellant gases.
US2564497A (en) * 1947-11-26 1951-08-14 Gen Electric Combustion chamber liner
US2544538A (en) * 1948-12-01 1951-03-06 Wright Aeronautical Corp Liner for hot gas chambers
GB680641A (en) * 1949-12-08 1952-10-08 George Jendrassik Improvements relating to gas pressure exchangers
GB700004A (en) * 1949-12-12 1953-11-25 Babcock & Wilcox Ltd Improvements in or relating to combustion apparatus
CH284190A (en) * 1950-09-04 1952-07-15 Bbc Brown Boveri & Cie Metal combustion chamber for generating hot gases, especially propellants for gas turbine systems.
US2651912A (en) * 1950-10-31 1953-09-15 Gen Electric Combustor and cooling means therefor
FR1053232A (en) * 1952-03-31 1954-02-01 Oven wall

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3082601A (en) * 1958-05-08 1963-03-26 Daimler Benz Ag Rocket combustion chamber
DE1211441B (en) * 1961-12-05 1966-02-24 Ass Elect Ind Combustion chamber, especially for gas turbine systems
FR2418867A1 (en) * 1978-03-01 1979-09-28 Gen Electric LOW CALORIFIC GAS COMBUSTION CHAMBER
FR2479951A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp INTERIOR TRIM OF COMBUSTION CHAMBER
FR2479900A1 (en) * 1980-04-02 1981-10-09 United Technologies Corp INTERIOR TRIM OF COMBUSTION CHAMBER
FR2493920A1 (en) * 1980-11-08 1982-05-14 Rolls Royce AIR CIRCULATION COOLING WALL FOR A GAS TURBINE ENGINE COMBUSTION CHAMBER
GB2117506A (en) * 1982-03-25 1983-10-12 Nu Way Energy Ltd Burner for gaseous fuels
US4695247A (en) * 1985-04-05 1987-09-22 Director-General Of The Agency Of Industrial Science & Technology Combustor of gas turbine
GB2173891A (en) * 1985-04-05 1986-10-22 Agency Ind Science Techn Gas turbine combustor
EP0204988A1 (en) * 1985-06-04 1986-12-17 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Flame tube
EP0224817A1 (en) * 1985-12-02 1987-06-10 Siemens Aktiengesellschaft Heat shield arrangement, especially for the structural components of a gas turbine plant
US4749029A (en) * 1985-12-02 1988-06-07 Kraftwerk Union Aktiengesellschaft Heat sheild assembly, especially for structural parts of gas turbine systems
GB2193564A (en) * 1986-07-24 1988-02-10 W B Black & Sons Improvements in lining a furnace with a refractory material
US4773356A (en) * 1986-07-24 1988-09-27 W B Black & Sons Limited Lining a furnace with a refractory material
GB2193564B (en) * 1986-07-24 1990-01-24 W B Black & Sons Improvements in lining a furnace with a refractory material
EP0741268A1 (en) * 1995-05-03 1996-11-06 United Technologies Corporation Liner panel for a gas turbine combustor wall
FR2752916A1 (en) * 1996-09-05 1998-03-06 Snecma THERMAL PROTECTIVE SHIRT FOR TURBOREACTOR COMBUSTION CHAMBER
US6029455A (en) * 1996-09-05 2000-02-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Turbojet engine combustion chamber with heat protecting lining
EP0895027A1 (en) * 1997-07-28 1999-02-03 Abb Research Ltd. Ceramic lining
US5957067A (en) * 1997-07-28 1999-09-28 Abb Research Ltd. Ceramic liner

Also Published As

Publication number Publication date
BE535497A (en)
CH331954A (en) 1958-08-15
DE1052750B (en) 1959-03-12
GB790293A (en) 1958-02-05
FR1122030A (en) 1956-08-30
US2919549A (en) 1960-01-05

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