GB1093515A - Method of producing combustion chambers and similar components for gas turbine engines - Google Patents

Method of producing combustion chambers and similar components for gas turbine engines

Info

Publication number
GB1093515A
GB1093515A GB1545166A GB1545166A GB1093515A GB 1093515 A GB1093515 A GB 1093515A GB 1545166 A GB1545166 A GB 1545166A GB 1545166 A GB1545166 A GB 1545166A GB 1093515 A GB1093515 A GB 1093515A
Authority
GB
United Kingdom
Prior art keywords
passages
gas turbine
sheet
combustion chambers
rolling
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
GB1545166A
Inventor
Martin Land
Paul Anthony Stuart Charles
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
Priority to GB1545166A priority Critical patent/GB1093515A/en
Publication of GB1093515A publication Critical patent/GB1093515A/en
Expired legal-status Critical Current

Links

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D53/00—Making other particular articles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Forging (AREA)

Abstract

1,093,515. Making gas turbine combustion chambers. ROLLS-ROYCE Ltd. April 16, 1966, No. 15451/66. Heading B3A. [Also in Division F1] A method of forming cooling fluid passages in material to be used for a gas turbine engine flame tube or jet pipe comprises the steps of forming passages of 0À036 inch in a flat sheet of the material of 4 times the finished thickness by means of an electron beam or spark erosion such that the passages are inclined at an angle of approximately 55‹ to the normal to the sheet and then rolling or forging the sheet to reduce its thickness to the required value. The rolling or forging operation increases the angle of inclination of the passages with the normal to approximately 80‹ and changes their cross-sectional shape from circular to substantially elliptical with a reduced width of 0À010 in. The flat sheet is then formed to the required component shape and welded by an electron beam. The method enables the passages to be formed by a more robust short and larger diameter electrode.
GB1545166A 1966-04-06 1966-04-06 Method of producing combustion chambers and similar components for gas turbine engines Expired GB1093515A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1545166A GB1093515A (en) 1966-04-06 1966-04-06 Method of producing combustion chambers and similar components for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1545166A GB1093515A (en) 1966-04-06 1966-04-06 Method of producing combustion chambers and similar components for gas turbine engines

Publications (1)

Publication Number Publication Date
GB1093515A true GB1093515A (en) 1967-12-06

Family

ID=10059381

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1545166A Expired GB1093515A (en) 1966-04-06 1966-04-06 Method of producing combustion chambers and similar components for gas turbine engines

Country Status (1)

Country Link
GB (1) GB1093515A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0290370A1 (en) * 1987-05-04 1988-11-09 United Technologies Corporation Coolable thin metal sheet
EP0335481A1 (en) * 1988-04-01 1989-10-04 General Electric Company Wall having cooling passage
FR2635577A1 (en) * 1988-08-17 1990-02-23 Rolls Royce Plc COMBUSTION CHAMBER FOR GAS TURBINE ENGINE
WO1992016798A1 (en) * 1991-03-22 1992-10-01 Rolls-Royce Plc Gas turbine engine combustor
EP0592161A1 (en) * 1992-10-06 1994-04-13 ROLLS-ROYCE plc Gas turbine engine combustor
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
WO1995025932A1 (en) * 1989-08-31 1995-09-28 Alliedsignal Inc. Turbine combustor cooling system
FR2735561A1 (en) * 1995-06-14 1996-12-20 Snecma COMBUSTION CHAMBER COMPRISING A MULTI-PERFORATED ANNULAR WALL

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0290370A1 (en) * 1987-05-04 1988-11-09 United Technologies Corporation Coolable thin metal sheet
EP0335481A1 (en) * 1988-04-01 1989-10-04 General Electric Company Wall having cooling passage
AU607566B2 (en) * 1988-04-01 1991-03-07 General Electric Company Wall having cooling passage
FR2635577A1 (en) * 1988-08-17 1990-02-23 Rolls Royce Plc COMBUSTION CHAMBER FOR GAS TURBINE ENGINE
US5000005A (en) * 1988-08-17 1991-03-19 Rolls-Royce, Plc Combustion chamber for a gas turbine engine
WO1995025932A1 (en) * 1989-08-31 1995-09-28 Alliedsignal Inc. Turbine combustor cooling system
WO1992016798A1 (en) * 1991-03-22 1992-10-01 Rolls-Royce Plc Gas turbine engine combustor
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
EP0592161A1 (en) * 1992-10-06 1994-04-13 ROLLS-ROYCE plc Gas turbine engine combustor
FR2735561A1 (en) * 1995-06-14 1996-12-20 Snecma COMBUSTION CHAMBER COMPRISING A MULTI-PERFORATED ANNULAR WALL
EP0752560A1 (en) * 1995-06-14 1997-01-08 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Combustor having an annular wall with a multitude of staggered cooling slits
US5713207A (en) * 1995-06-14 1998-02-03 Societe National D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Annular combustion chamber with a perforated wall

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