GB878195A - Improvements in or relating to gas-turbine jet-propulsion engines - Google Patents

Improvements in or relating to gas-turbine jet-propulsion engines

Info

Publication number
GB878195A
GB878195A GB9104/59A GB910459A GB878195A GB 878195 A GB878195 A GB 878195A GB 9104/59 A GB9104/59 A GB 9104/59A GB 910459 A GB910459 A GB 910459A GB 878195 A GB878195 A GB 878195A
Authority
GB
United Kingdom
Prior art keywords
jet pipe
heat shield
clearance
heat
annular
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
GB9104/59A
Inventor
John Michael Storer Keen
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 GB9104/59A priority Critical patent/GB878195A/en
Publication of GB878195A publication Critical patent/GB878195A/en
Expired legal-status Critical Current

Links

Classifications

    • 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)
  • Exhaust Silencers (AREA)

Abstract

878,195. Gas-turbine jet-propulsion engines. ROLLS-ROYCE Ltd. March 9, 1960 [March 16, 1959], No. 9104/59. Class 110 (3). A gas-turbine jet-propulsion engine has, mounted within the jet pipe, a tubular heat shield spaced from the jet pipe by an annular clearance, a propulsion nozzle mounted at the downstream end of the jet pipe, means for supplying cooling air to the clearance and a tubular heat-insulating member mounted in the clearance so as to divide the cooling air into two portions, one of which flows between the heat-insulating member and the shield to cool the latter and the other flows between the heat-insulating member and the jet pipe and is directed on to, so as to cool, the propulsion nozzle. The invention is described with reference to a gas turbine by-pass jetpropulsion engine having a jet pipe 11 formed of three sections 12, 13, 14. The engine casing 10 has an annular passage 15 to which by-pass air is supplied by the low pressure compressor of the engine. Some of this air passes through hollow struts 16 and is discharged through ports 17 into the path of the turbine exhaust gases. A heat shield 18 is mounted within the jet pipe 11 and encloses reheat combustion equipment. The heat shield 18 is formed of tubular sections 19 to 23, the downstream end of the sections 19 to 22 being mounted within the upstream end of each of the sections 20 to 23 by means of a corrugated annular strip 24. The heat shield may be formed of metal or asbestos, or may be formed of other heatresisting substances arranged in a sheet' metal container. The heat shield is carried by a single strut 25 and at its upstream end slides on an annular member 32 carried by the strut 16. The heat shield is unconnected to the jet pipe at its downstream end and therefore may be slid into position within the jet pipe. An annular heat-insulating blanket 34 is mounted between the heat shield 18 and jet pipe 11. The blanket 34 is carried by constant 35 at its upstream end so that it also may be slid into position within the jet pipe. Cooling air from the by-pass passage 15 flows through the annular clearance 29 and then divided by the blanket 34 into two portions which flow respectively through the clearances 37, 38. The air passing through clearance 38 passes between the corrugations of the strips 24 so as to flow on to, and provide film cooling of, the internal surface of the heat shield. The air flowing through the clearance 37 will be directed through gap 50 on to the inner surface of the nozzle flaps 51. The flaps 51 are actuated by a wedge-shaped member 45 moved axially by pneumatic or hydraulic cylinders 47.
GB9104/59A 1959-03-16 1959-03-16 Improvements in or relating to gas-turbine jet-propulsion engines Expired GB878195A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB9104/59A GB878195A (en) 1959-03-16 1959-03-16 Improvements in or relating to gas-turbine jet-propulsion engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9104/59A GB878195A (en) 1959-03-16 1959-03-16 Improvements in or relating to gas-turbine jet-propulsion engines

Publications (1)

Publication Number Publication Date
GB878195A true GB878195A (en) 1961-09-27

Family

ID=9865435

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9104/59A Expired GB878195A (en) 1959-03-16 1959-03-16 Improvements in or relating to gas-turbine jet-propulsion engines

Country Status (1)

Country Link
GB (1) GB878195A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2835288A1 (en) * 2002-01-31 2003-08-01 Snecma Moteurs COOLING SYSTEM FOR A TURBOMACHINE POST-COMBUSTION NOZZLE
FR3004494A1 (en) * 2013-04-15 2014-10-17 Aircelle Sa TUYERE FOR AIRCRAFT TURBOPROPULSER WITH NON-CARBONATED BLOWER
US11098649B2 (en) * 2018-07-19 2021-08-24 The Boeing Company Self-regulating back-side pressurization system for thermal insulation blankets
CN114151228A (en) * 2022-02-09 2022-03-08 中国航发四川燃气涡轮研究院 Method for dividing binary vector spray pipe regulating sheet into discrete cold air areas

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2835288A1 (en) * 2002-01-31 2003-08-01 Snecma Moteurs COOLING SYSTEM FOR A TURBOMACHINE POST-COMBUSTION NOZZLE
EP1333172A1 (en) * 2002-01-31 2003-08-06 Snecma Moteurs Cooling system for an afterburner nozzle of a turbomachine
US6792748B2 (en) 2002-01-31 2004-09-21 Snecma Moteurs Cooling system for a gas turbine engine post-combustion jet nozzle
FR3004494A1 (en) * 2013-04-15 2014-10-17 Aircelle Sa TUYERE FOR AIRCRAFT TURBOPROPULSER WITH NON-CARBONATED BLOWER
WO2014170600A1 (en) * 2013-04-15 2014-10-23 Aircelle Nozzle for an aircraft turboprop engine with an unducted fan
US10113506B2 (en) 2013-04-15 2018-10-30 Aircelle Nozzle for an aircraft turboprop engine with an unducted fan
US11098649B2 (en) * 2018-07-19 2021-08-24 The Boeing Company Self-regulating back-side pressurization system for thermal insulation blankets
CN114151228A (en) * 2022-02-09 2022-03-08 中国航发四川燃气涡轮研究院 Method for dividing binary vector spray pipe regulating sheet into discrete cold air areas

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