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FR2271405A1 - Jet engine reheat pipe protection device - has sleeve with flange gripped between segments allowing radial expansion - Google Patents

Jet engine reheat pipe protection device - has sleeve with flange gripped between segments allowing radial expansion

Info

Publication number
FR2271405A1
FR2271405A1 FR7342949A FR7342949A FR2271405A1 FR 2271405 A1 FR2271405 A1 FR 2271405A1 FR 7342949 A FR7342949 A FR 7342949A FR 7342949 A FR7342949 A FR 7342949A FR 2271405 A1 FR2271405 A1 FR 2271405A1
Authority
FR
France
Prior art keywords
sleeve
flange
pipe
radial expansion
protection device
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.)
Granted
Application number
FR7342949A
Other languages
French (fr)
Other versions
FR2271405B1 (en
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR7342949A priority Critical patent/FR2271405A1/en
Publication of FR2271405A1 publication Critical patent/FR2271405A1/en
Application granted granted Critical
Publication of FR2271405B1 publication Critical patent/FR2271405B1/fr
Granted 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
    • 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
    • F02K1/80—Couplings or connections
    • 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)
  • Joints Allowing Movement (AREA)

Abstract

Sheet metal sleeves inside the pipe form an annular protection space for an engine with after-burners. The upstream end of the sleeve has a crown-shaped flange. Angle section segments each have one flange secured to the pipe and extending upstream, while their other flanges shut off the annular space between sleeve and wall of pipe completely. These other flanges bear alternately against opposite sides of the sleeve flange so as to grip it between them while allowing it to slide. An annular support mounted on the wall of the pipe secures the downstream end of the sleeve while allowing sliding motion. Sliding of the sleeve flange allows for radial expansion of the sleeve, while the downstream support allows this in the axial direction.
FR7342949A 1973-12-03 1973-12-03 Jet engine reheat pipe protection device - has sleeve with flange gripped between segments allowing radial expansion Granted FR2271405A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR7342949A FR2271405A1 (en) 1973-12-03 1973-12-03 Jet engine reheat pipe protection device - has sleeve with flange gripped between segments allowing radial expansion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7342949A FR2271405A1 (en) 1973-12-03 1973-12-03 Jet engine reheat pipe protection device - has sleeve with flange gripped between segments allowing radial expansion

Publications (2)

Publication Number Publication Date
FR2271405A1 true FR2271405A1 (en) 1975-12-12
FR2271405B1 FR2271405B1 (en) 1976-10-08

Family

ID=9128593

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7342949A Granted FR2271405A1 (en) 1973-12-03 1973-12-03 Jet engine reheat pipe protection device - has sleeve with flange gripped between segments allowing radial expansion

Country Status (1)

Country Link
FR (1) FR2271405A1 (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4696431A (en) * 1985-11-29 1987-09-29 United Technologies Corporation Augmentor liner support band having finger positioners
EP0344877A1 (en) * 1988-05-31 1989-12-06 General Electric Company Heat shield for gas turbine engine frame
EP0397566A1 (en) * 1989-05-11 1990-11-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heat insulation structure for an afterburner liner or turbine transition piece
EP0778408A3 (en) * 1995-12-05 1999-04-28 United Technologies Corporation Easily replaceable hot conduit liner
EP0994304A3 (en) * 1998-10-15 2002-01-02 United Technologies Corporation Thermally compliant liner
DE102008023052A1 (en) * 2008-05-09 2009-12-03 Eads Deutschland Gmbh Combustion chamber wall for combustion chamber, has inner wall, outer wall and cooling channel located between inner wall and outer wall, where bridges are arranged and formed between inner wall and outer wall
EP1691064A3 (en) * 2005-02-14 2010-03-24 United Technologies Corporation Cooled dual wall liner closeout
US20150050139A1 (en) * 2013-08-16 2015-02-19 Rolls-Royce Plc Panel attachment system

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4696431A (en) * 1985-11-29 1987-09-29 United Technologies Corporation Augmentor liner support band having finger positioners
EP0344877A1 (en) * 1988-05-31 1989-12-06 General Electric Company Heat shield for gas turbine engine frame
EP0397566A1 (en) * 1989-05-11 1990-11-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heat insulation structure for an afterburner liner or turbine transition piece
FR2646880A1 (en) * 1989-05-11 1990-11-16 Snecma THERMAL PROTECTION SHIRT FOR POST-COMBUSTION CHANNEL OR TRANSITION OF TURBOREACTOR
US5069034A (en) * 1989-05-11 1991-12-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Heat protective lining for an afterburner or transition duct of a turbojet engine
EP0778408A3 (en) * 1995-12-05 1999-04-28 United Technologies Corporation Easily replaceable hot conduit liner
EP0994304A3 (en) * 1998-10-15 2002-01-02 United Technologies Corporation Thermally compliant liner
EP1691064A3 (en) * 2005-02-14 2010-03-24 United Technologies Corporation Cooled dual wall liner closeout
US7739872B2 (en) 2005-02-14 2010-06-22 United Technologies Corporation Cooled dual wall liner closeout
DE102008023052A1 (en) * 2008-05-09 2009-12-03 Eads Deutschland Gmbh Combustion chamber wall for combustion chamber, has inner wall, outer wall and cooling channel located between inner wall and outer wall, where bridges are arranged and formed between inner wall and outer wall
DE102008023052B4 (en) * 2008-05-09 2011-02-10 Eads Deutschland Gmbh Combustion chamber wall or hot gas wall of a combustion chamber and combustion chamber with a combustion chamber wall
US20150050139A1 (en) * 2013-08-16 2015-02-19 Rolls-Royce Plc Panel attachment system
US10001136B2 (en) * 2013-08-16 2018-06-19 Rolls-Royce Plc Panel attachment system

Also Published As

Publication number Publication date
FR2271405B1 (en) 1976-10-08

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Legal Events

Date Code Title Description
ST Notification of lapse