GB1079186A - Improvements in gas turbine engines - Google Patents

Improvements in gas turbine engines

Info

Publication number
GB1079186A
GB1079186A GB19092/65A GB1909265A GB1079186A GB 1079186 A GB1079186 A GB 1079186A GB 19092/65 A GB19092/65 A GB 19092/65A GB 1909265 A GB1909265 A GB 1909265A GB 1079186 A GB1079186 A GB 1079186A
Authority
GB
United Kingdom
Prior art keywords
members
gas turbine
spaced apart
metal
disposed
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
GB19092/65A
Inventor
Dennis Peter Buchanan
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 GB19092/65A priority Critical patent/GB1079186A/en
Priority to DE19661476879 priority patent/DE1476879A1/en
Publication of GB1079186A publication Critical patent/GB1079186A/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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,079,186. Gas turbine engine combustion equipment and jet pipes. ROLLS-ROYCE Ltd. April 29, 1966 [May 6, 1965], No. 19092/65. Headings F1J and F1L. In a combustion chamber or jet pipe for a gas turbine power plant in which means are provided for maintaining two overlapping tubular wall sections of the combustion chamber or jet pipe in radially spaced apart relationship, the means comprises a plurality of circumferentially spaced apart members, the members being of aerofoil section. In a first embodiment the invention is shown applied to combustion equipment of a gas turbine engine comprising tubular wall members 4, 5 disposed in radially spaced apart, axially overlapping assembly by means of aerofoil section members 6 secured to the wall members by welding. The members 6 may be formed from a strip of metal, a portion 6a Fig. 3 of metal being retained so that the members 6 are disposed at the correct spacing during assembly. The portion 6a may or may not be removed subsequently, In Fig. 7 (not shown) the spacers 6 are made as individual pieces stamped or pressed from sheet metal.
GB19092/65A 1965-05-06 1965-05-06 Improvements in gas turbine engines Expired GB1079186A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB19092/65A GB1079186A (en) 1965-05-06 1965-05-06 Improvements in gas turbine engines
DE19661476879 DE1476879A1 (en) 1965-05-06 1966-05-05 Combustion chamber and steel tube for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB19092/65A GB1079186A (en) 1965-05-06 1965-05-06 Improvements in gas turbine engines

Publications (1)

Publication Number Publication Date
GB1079186A true GB1079186A (en) 1967-08-16

Family

ID=10123657

Family Applications (1)

Application Number Title Priority Date Filing Date
GB19092/65A Expired GB1079186A (en) 1965-05-06 1965-05-06 Improvements in gas turbine engines

Country Status (2)

Country Link
DE (1) DE1476879A1 (en)
GB (1) GB1079186A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007198727A (en) * 2006-01-25 2007-08-09 Rolls Royce Plc Wall elements for gas turbine engine combustors
US8024933B2 (en) 2006-01-25 2011-09-27 Rolls-Royce Plc Wall elements for gas turbine engine combustors
US8650882B2 (en) 2006-01-25 2014-02-18 Rolls-Royce Plc Wall elements for gas turbine engine combustors
CN113894453A (en) * 2021-09-15 2022-01-07 蓝箭航天空间科技股份有限公司 Method for processing combustion chamber structure of dissimilar metal and combustion chamber

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022200842A1 (en) 2022-01-26 2023-07-27 BSH Hausgeräte GmbH Spacer element for an air duct of a household appliance

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007198727A (en) * 2006-01-25 2007-08-09 Rolls Royce Plc Wall elements for gas turbine engine combustors
US7886541B2 (en) 2006-01-25 2011-02-15 Rolls-Royce Plc Wall elements for gas turbine engine combustors
US8024933B2 (en) 2006-01-25 2011-09-27 Rolls-Royce Plc Wall elements for gas turbine engine combustors
US8650882B2 (en) 2006-01-25 2014-02-18 Rolls-Royce Plc Wall elements for gas turbine engine combustors
CN113894453A (en) * 2021-09-15 2022-01-07 蓝箭航天空间科技股份有限公司 Method for processing combustion chamber structure of dissimilar metal and combustion chamber
CN113894453B (en) * 2021-09-15 2022-06-17 蓝箭航天空间科技股份有限公司 Method for processing combustion chamber structure of dissimilar metal and combustion chamber

Also Published As

Publication number Publication date
DE1476879A1 (en) 1969-10-23

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