EP0184962A1 - Gehäuseschutzring für ein Gasturbinengebläse - Google Patents

Gehäuseschutzring für ein Gasturbinengebläse Download PDF

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Publication number
EP0184962A1
EP0184962A1 EP85402398A EP85402398A EP0184962A1 EP 0184962 A1 EP0184962 A1 EP 0184962A1 EP 85402398 A EP85402398 A EP 85402398A EP 85402398 A EP85402398 A EP 85402398A EP 0184962 A1 EP0184962 A1 EP 0184962A1
Authority
EP
European Patent Office
Prior art keywords
housing
zone
wall
retention
casing
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
EP85402398A
Other languages
English (en)
French (fr)
Other versions
EP0184962B1 (de
Inventor
Alain Marie Joseph Lardellier
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0184962A1 publication Critical patent/EP0184962A1/de
Application granted granted Critical
Publication of EP0184962B1 publication Critical patent/EP0184962B1/de
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor

Definitions

  • the invention relates to a retention casing for a turbojet fan, said casing comprising, opposite the area swept by the rotor, a sealing ring and a retention structure capable of stopping the blade or the broken blade part and evacuate it.
  • the patent application European No. 0028183 proposes a solution consisting in placing between the casing and the sealing ring a retention structure made up of hollow toroids, concentric with the rotor, held by locking elements.
  • the casing then only has to provide a function of resistance to dynamic forces and damping of vibrations.
  • the invention aims to produce a retention casing having a succession of structures adapted to the different types of aggression to which they are liable to be subjected and of a fixing common to at least one retention structure and to the fittings of attachment of the accessories provided on the outside of the housing.
  • the retention case for a turbojet fan according to the invention is remarkable in this. that it consists of an assembly comprising at least one metallic outer casing and an internal lining of composite material, concentric, removable, hooped at least partially in the casing, said assembly having in the direction of flow of the air stream at least three zones of different retention characteristics, the first zone surrounding the rotor blading of the fan.
  • the single figure shows, in half section, the blower compartment of a turbojet engine.
  • the retention casing 1 has at its ends flanges 2 and 3 by which it is fixed respectively to the inlet casing and to the outlet casing (not shown) of the fan.
  • the retention casing surrounds the fan rotor 4 and retains the stationary vanes 5 of the air flow rectifier.
  • the retention casing is formed from an exterior assembly consisting of a casing / metal 6 and an internal lining 7, the wall of which, delimiting the flow channel of the air stream, is constituted at least in part by 'a composite material.
  • the lining, concentric with the casing 6, is hooped there at least partially, as will be described later.
  • the assembly has, in the direction of the flow of the air stream, (from left to right in the figure) at least three successive zones having different retention characteristics according to their position relative to the rotor blading of the blower.
  • the first zone A is located directly above the rotor vane and comprises radially from the inside to the outside a sealing ring 8 of abradable material, fixed in a housing provided in the wall of the lining 6, a annular portion of the wall of the metal casing, at least part 9 of the outer wall of which lies between two circular ribs 10, 11, carries a retention ring 12 formed by a winding of aromatic polyamide fibers embedded in a synthetic resin.
  • This part 9 is provided approximately on the front half of the first zone and is capable of slowing down and retaining the blade fragments liable to come off during the impact of material sucked in by the fan.
  • the second zone B extending behind the zone swept by the rotor, comprises from the inside towards the outside an approximately annular portion 13 formed by at least the wall of the lining 7, this wall possibly being able to be formed from two skins between which a retention structure is maintained; a retention belt 14, consisting of at least two tori 15, 16 held on the internal surface of the wall of the metal casing by supports 17; an annular portion 18 of the metal casing.
  • the third zone C extending the second zone B, of a length roughly equal to that of zone A, comprises from the inside to the outside the wall 19 of the lining 7, an empty annular space 20 and a portion 21 of the metal casing. This third zone is intended to retain in the empty space 20 the significant debris which lost their energy in the preceding zone B.
  • the parts of the wall extending upstream and downstream of these three zones will have a thickness substantially equal to that of the third zone C.
  • the wall of the metal casing has, in zone B, three circumferential rows of holes 25, 26, 27, provided for fixing the supports 17 of the toroids forming the retention belt and the fittings 29, 30 for fixing accessories and auxiliaries.
  • Another circumferential row of holes 31 is provided at the end of zone C to receive the fixings of the straightening vanes 5.
  • the inner surface of the metal casing 6 is provided, approximately perpendicular to the zone A of two cylindrical bearings 32, 33, the bore of the first bearing (in the direction fluid flow) being greater than that of the second bearing.
  • These bearing surfaces are intended to retain by hooping the removable lining 7 which is introduced through the front of the casing after the retention belt 14 has been fixed in the latter.
  • the retention belt is made up as previously described of two toroids 15 , 16 held from place to place by supports 17. These supports have an approximately trapezoidal section, the large curvilinear base of which has two notches, intended to house the toroids defining two oblique lateral tabs and a central tab capable of cooperating with means clamp 25A, 26A, 27A.
  • the side tabs are each provided with a threaded hole into which a bolt will be screwed passing through the holes of the rows 25 and 26 which will optionally maintain on the outer surface of the housing fixing fittings 29 and 30, serving as supports of accessories.
  • the central tab carries an axial passage for a bolt 27A whose end of the thread passes through a hole 27 in the central circumferential row of holes provided on the casing and in an opening provided in the central tab of the fittings.
  • the end of the thread receives a support piece which distributes the tightening forces of the nut on the central tab and involves a large portion of the metal casing.
  • the support 14 and in particular the bolt 26A passing through a hole in the row 26 ensures the fixing of a retaining fitting 34 to which is fixed by the means 38 the downstream part of the lining.
  • the toroids 15, 16 are, for example, formed from glass fiber, carbon or polyamide tubes wound, linked by a polymerizable resin.
  • the supports 17 are provided in titanium but can be made of a composite material.
  • the lining 7 carries at its upstream end a flange 35 whose periphery forms a bearing cooperating with a corresponding bearing 36 provided on the inner surface of the upstream end of the metal casing 6.
  • the lining is extended downstream by the honeycomb coating 37 of the wall of the metal casing used for acoustic damping.
  • the lining constitutes a removable, mountable and dismountable assembly from the upstream or inlet end of the fan casing, held in the upstream part by three cylindrical bearings 35, 32, 33 of decreasing diameter from upstream to downstream, and in the downstream part by fixing screws 38 on the holding fittings 34 held at one of their ends by the clamping means of the supports 17.
  • the lining is constituted according to one embodiment by a winding of organic or mineral fibers such as glass, carbon, "KEVLAR” or others, embedded in a synthetic resin.
  • the lining comprises an inner skin and an outer skin of metal or fibers fixed on a filling or retention structure formed of honeycombs or of a composite resin-mineral or organic filler material.
  • this wall construction of the lining is used in the zones which must provide a retention and / or acoustic damping function.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP85402398A 1984-12-06 1985-12-04 Gehäuseschutzring für ein Gasturbinengebläse Expired EP0184962B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8418593 1984-12-06
FR8418593A FR2574476B1 (fr) 1984-12-06 1984-12-06 Carter de retention pour soufflante de turboreacteur

Publications (2)

Publication Number Publication Date
EP0184962A1 true EP0184962A1 (de) 1986-06-18
EP0184962B1 EP0184962B1 (de) 1988-08-03

Family

ID=9310290

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85402398A Expired EP0184962B1 (de) 1984-12-06 1985-12-04 Gehäuseschutzring für ein Gasturbinengebläse

Country Status (5)

Country Link
US (1) US4648795A (de)
EP (1) EP0184962B1 (de)
JP (1) JPS61138864A (de)
DE (1) DE3564148D1 (de)
FR (1) FR2574476B1 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995030076A1 (en) * 1994-04-29 1995-11-09 United Technologies Corporation Fan blade containment assembly
WO1995030073A1 (en) * 1994-04-29 1995-11-09 United Technologies Corporation Aircraft fan containment structure
WO2000046489A1 (en) * 1999-02-04 2000-08-10 Pratt & Whitney Canada Corp. Hardwall fan case with structured bumper
US6497550B2 (en) 2000-04-05 2002-12-24 Rolls-Royce Plc Gas turbine engine blade containment assembly
FR2925118A1 (fr) * 2007-12-14 2009-06-19 Snecma Sa Panneau de support d'abradable dans une turbomachine
US7918215B2 (en) 2006-05-08 2011-04-05 Honeywell International Inc. Compressor stage assembly lock
FR3054526A1 (fr) * 2016-07-26 2018-02-02 Safran Aircraft Engines Aeronef comportant un turboreacteur integre au fuselage arriere comportant un carenage permettant l'ejection de pales

Families Citing this family (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4955192A (en) * 1988-12-12 1990-09-11 Sundstrand Corporation Containment ring for radial inflow turbine
US5188505A (en) * 1991-10-07 1993-02-23 General Electric Company Structural ring mechanism for containment housing of turbofan
GB2262313B (en) * 1991-12-14 1994-09-21 Rolls Royce Plc Aerofoil blade containment
US5259724A (en) * 1992-05-01 1993-11-09 General Electric Company Inlet fan blade fragment containment shield
US5267828A (en) * 1992-11-13 1993-12-07 General Electric Company Removable fan shroud panel
US5486086A (en) * 1994-01-04 1996-01-23 General Electric Company Blade containment system
US5485723A (en) * 1994-04-29 1996-01-23 United Technologies Corporation Variable thickness isogrid case
US5409349A (en) * 1994-04-29 1995-04-25 United Technologies Corporation Turbofan containment structure
US6206631B1 (en) * 1999-09-07 2001-03-27 General Electric Company Turbomachine fan casing with dual-wall blade containment structure
GB9922619D0 (en) * 1999-09-25 1999-11-24 Rolls Royce Plc A gas turbine engine blade containment assembly
US6290455B1 (en) * 1999-12-03 2001-09-18 General Electric Company Contoured hardwall containment
GB0107970D0 (en) 2001-03-30 2001-05-23 Rolls Royce Plc A gas turbine engine blade containment assembly
GB0117550D0 (en) * 2001-07-19 2001-09-12 Rolls Royce Plc Joint arrangement
GB0403941D0 (en) * 2004-02-21 2004-03-24 Rolls Royce Plc A gas turbine engine blade containment assembly
US8191254B2 (en) 2004-09-23 2012-06-05 Carlton Forge Works Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
JP2009515075A (ja) * 2005-09-20 2009-04-09 カルダレア、エル、ジェームス、ジュニア ガスタービンジェットエンジンにおけるファンケースの強化方法
FR2913053B1 (fr) * 2007-02-23 2009-05-22 Snecma Sa Procede de fabrication d'un carter de turbine a gaz en materiau composite et carter ainsi obtenu
GB2459646B (en) * 2008-04-28 2011-03-30 Rolls Royce Plc A fan assembly
GB0813821D0 (en) * 2008-07-29 2008-09-03 Rolls Royce Plc A fan casing for a gas turbine engine
FR2935017B1 (fr) * 2008-08-13 2012-11-02 Snecma Paroi interne d'une nacelle de turbomachine
GB2471466A (en) * 2009-06-30 2011-01-05 Rolls Royce Plc Fan casing for a turbofan gas turbine engine
GB2471465A (en) * 2009-06-30 2011-01-05 Rolls Royce Plc Fan casing for a turbofan gas turbine engine
FR2964145B1 (fr) * 2010-08-26 2018-06-15 Safran Helicopter Engines Procede d'accrochage de blindage sur carter de turbine et ensemble d'accrochage pour sa mise en oeuvre
GB201020143D0 (en) 2010-11-29 2011-01-12 Rolls Royce Plc A gas turbine engine blade containment arrangement
GB201103682D0 (en) * 2011-03-04 2011-04-20 Rolls Royce Plc A turbomachine casing assembly
EP2971606A4 (de) * 2013-03-15 2016-12-28 United Technologies Corp Verstärktes verbundgehäuse
GB201417416D0 (en) * 2014-10-02 2014-11-19 Rolls Royce Plc Fan track liner assembly
EP3173587B1 (de) * 2015-11-30 2021-03-31 MTU Aero Engines GmbH Gehäuse für eine strömungsmaschine, einbausicherung und strömungsmaschine
DE102016105957A1 (de) * 2016-04-01 2017-10-05 Rolls-Royce Deutschland Ltd & Co Kg Fangehäuse und Triebwerksbaugruppe mit Fangehäuse
US10260522B2 (en) * 2016-05-19 2019-04-16 Rolls-Royce Corporation Liner system
FR3060052B1 (fr) * 2016-12-14 2020-10-09 Safran Helicopter Engines Procede de fabrication d'une cartouche de blindage d'un element de turbomachine et cartouche de blindage et element de turbomachine correspondants
US10550718B2 (en) 2017-03-31 2020-02-04 The Boeing Company Gas turbine engine fan blade containment systems
US10487684B2 (en) 2017-03-31 2019-11-26 The Boeing Company Gas turbine engine fan blade containment systems
GB201816990D0 (en) * 2018-10-18 2018-12-05 Rolls Royce Plc Debris retention
GB201816989D0 (en) * 2018-10-18 2018-12-05 Rolls Royce Plc Debris retention
US11008887B2 (en) 2018-12-21 2021-05-18 Rolls-Royce Corporation Fan containment assembly having a nesting cavity

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH460450A (fr) * 1964-01-15 1968-07-31 United Aircraft Corp Turbine à gaz
EP0028183A1 (de) * 1979-10-23 1981-05-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Fangbandage für das Kompressorgehäuse einer Turbomaschine
EP0030179A1 (de) * 1979-11-27 1981-06-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Fangstruktur für das Kompressorgehäuse einer Turbomaschine
GB2112349A (en) * 1981-12-21 1983-07-20 United Technologies Corp Containment structure
GB2114233A (en) * 1982-02-01 1983-08-17 United Technologies Corp Containment shell for a fan section of a gas turbine engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1485032A (en) * 1974-08-23 1977-09-08 Rolls Royce Gas turbine engine casing
FR2452601A1 (fr) * 1979-03-30 1980-10-24 Snecma Support amovible de revetement d'etancheite pour carter de soufflante de turboreacteur
JPS57126572A (en) * 1981-01-30 1982-08-06 Toshiba Corp Operation controlling method for water wheel and pump water wheel
US4452563A (en) * 1981-12-21 1984-06-05 United Technologies Corporation Containment structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH460450A (fr) * 1964-01-15 1968-07-31 United Aircraft Corp Turbine à gaz
EP0028183A1 (de) * 1979-10-23 1981-05-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Fangbandage für das Kompressorgehäuse einer Turbomaschine
EP0030179A1 (de) * 1979-11-27 1981-06-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Fangstruktur für das Kompressorgehäuse einer Turbomaschine
GB2112349A (en) * 1981-12-21 1983-07-20 United Technologies Corp Containment structure
GB2114233A (en) * 1982-02-01 1983-08-17 United Technologies Corp Containment shell for a fan section of a gas turbine engine

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995030076A1 (en) * 1994-04-29 1995-11-09 United Technologies Corporation Fan blade containment assembly
WO1995030073A1 (en) * 1994-04-29 1995-11-09 United Technologies Corporation Aircraft fan containment structure
WO2000046489A1 (en) * 1999-02-04 2000-08-10 Pratt & Whitney Canada Corp. Hardwall fan case with structured bumper
US6497550B2 (en) 2000-04-05 2002-12-24 Rolls-Royce Plc Gas turbine engine blade containment assembly
US7918215B2 (en) 2006-05-08 2011-04-05 Honeywell International Inc. Compressor stage assembly lock
FR2925118A1 (fr) * 2007-12-14 2009-06-19 Snecma Sa Panneau de support d'abradable dans une turbomachine
EP2088290A1 (de) * 2007-12-14 2009-08-12 Snecma Versteifender Gehäuseabreibbelag in einem Turbotriebwerk
US8061967B2 (en) 2007-12-14 2011-11-22 Snecma Panel for supporting abradable material in a turbomachine
CN101457771B (zh) * 2007-12-14 2012-10-10 斯奈克玛 涡轮机内的支撑可磨损材料的板
RU2477805C2 (ru) * 2007-12-14 2013-03-20 Снекма Панель-подложка для истирающегося покрытия в газотурбинном двигателе
FR3054526A1 (fr) * 2016-07-26 2018-02-02 Safran Aircraft Engines Aeronef comportant un turboreacteur integre au fuselage arriere comportant un carenage permettant l'ejection de pales
US10746044B2 (en) 2016-07-26 2020-08-18 Safran Aircraft Engines Aircraft comprising a turbojet engine integrated into the rear fuselage comprising a fairing allowing the ejection of blades

Also Published As

Publication number Publication date
DE3564148D1 (en) 1988-09-08
JPH0363669B2 (de) 1991-10-02
FR2574476B1 (fr) 1987-01-02
US4648795A (en) 1987-03-10
FR2574476A1 (fr) 1986-06-13
JPS61138864A (ja) 1986-06-26
EP0184962B1 (de) 1988-08-03

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