EP0718471A1 - Berstschutzring für eine Turbomaschine - Google Patents

Berstschutzring für eine Turbomaschine Download PDF

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Publication number
EP0718471A1
EP0718471A1 EP95402879A EP95402879A EP0718471A1 EP 0718471 A1 EP0718471 A1 EP 0718471A1 EP 95402879 A EP95402879 A EP 95402879A EP 95402879 A EP95402879 A EP 95402879A EP 0718471 A1 EP0718471 A1 EP 0718471A1
Authority
EP
European Patent Office
Prior art keywords
shield
stator
turbomachine
attachment means
rupture
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
EP95402879A
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English (en)
French (fr)
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EP0718471B1 (de
Inventor
Pierre A. Glowacki
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 Nacelles SAS
Original Assignee
Hispano Suiza SA
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Filing date
Publication date
Application filed by Hispano Suiza SA filed Critical Hispano Suiza SA
Publication of EP0718471A1 publication Critical patent/EP0718471A1/de
Application granted granted Critical
Publication of EP0718471B1 publication Critical patent/EP0718471B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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 subject of the invention is a protective shield for a turbomachine.
  • stator More precisely in front of a bladed area of a rotor which the stator surrounds, that is to say in front of a compressor or turbine section in the machine, and its function is to stop the pieces or debris of blades or rotor which would be projected towards it under the action of centrifugal forces after a rupture due to an accident.
  • US Patent 4,452,563 describes a shield formed by a continuous network of fibrous bands draped over the external face, opposite the rotor, of the stator. This design seems relatively ineffective because the fibers should tear quite easily and therefore would not give sufficient protection. We could also lay layers of honeycomb material on this external face of the stator, but, despite the increased energy absorption that such a structure would offer to slow or stop projectiles, this absorption would be localized to the place of the shock and the shield would be pierced here also quite easily.
  • European patent 0 626 502 describes a shield formed from juxtaposed plates which have the same drawbacks.
  • French Patent 2,375,443 describes a continuous ring shield which breaks its attachments when a detached blade strikes it; but the shield serves as a lining for the stator or replaces it, and it can only absorb the kinetic energy of the blade by taking a rotary movement; he doesn't have the possibility of absorbing energy by deforming, as in the invention, since it has no surrounding space to deform; Finally, it is only effective if the energy communicated is sufficient to break all of its attachments, which limits its possibilities of use.
  • the invention is based on the idea that it is advantageous to involve the whole shield in absorbing the shock by allowing it to deform and break its attachments to the stator in proportion to the energy received, and it is original in that the ring is continuous, connected to the turbomachine by attachment means calculated to rupture below a rupture limit of the shield subjected to an impact and extends in an annular space comprised between the stator and an external fairing of the turbomachine being radially separated from the stator as from the external fairing.
  • FIG. 1 represents a portion of a turbomachine which comprises a rotor 1, a stator 2 in the form of an envelope surrounding the rotor 1 and an external fairing 3 surrounding the stator 2; the stator 2 has a circular and planar flaring 4 which terminates it upstream, and which itself ends with a flange 5 fitted on the internal face of the outer fairing 3 and riveted to it.
  • the rotor 1 and the stator 2 carry alternating stages of respectively movable 6 and stationary vanes 7, as is usual for constituting turbines and compressors.
  • the shield 9 occupies it and extends in its middle: this means that it is radially separated from the external fairing 3 as from stator 2, without necessarily being equidistant from them.
  • the shield 9 is a continuous ring of ductile, metallic or other material, the advantage of which is to absorb large impact energies. It is maintained by attachment means which unite it to the flare 4. Many designs are possible, and two will be illustrated.
  • the shield 9 has one end bent into a flat and circular flange 10 in the bores of which screws 11 of longitudinal orientation have been engaged, the ends of which are retained in threads 12 drilled in the flare 4.
  • the screws 11 comprise a thinned part 13 of well-defined diameter, constituting an initiation of rupture, at the limit junction between the flare 4 and the flange 10.
  • the flange 10 is replaced by lugs 14, in the extension of the shield 9, but substantially thinner than it, in the embodiment of FIG. 3.
  • the flaring 4 is provided with a flange 15 circular and continuous, extending the shield 9 and almost contiguous to it, on which the legs 14 rest. Screws 16, this time oriented in the radial direction, unite the tabs 14 with the flange 15.
  • a breaking point is also provided, in the form of notches 19 which narrow the tabs 14 at the limit of the shield 9 and the flange 15 .
  • FIG. 4 illustrates what can happen after an impact due to a piece of rotor 17 accidentally detached in operation, such as a fragment of a turbine disc.
  • the centrifugal force projects it at high speed towards the outside: it bursts the stator 2 then embosses the shield 9.
  • the plastic deformation which results in the appearance of the bump 18 on the part of the shield 9 which it reaches causes if the kinetic energy of the piece of rotor 17 allows it, a partial or total destruction of the attachment means.
  • the thinned portion 13 of the screws 12 is sheared; in that of FIG. 3, the tabs 14 are broken, between the notches 19, here again by shearing.
  • the broken fastening elements are first of all those which are close to the bump 18. If the shock is sufficiently violent, all the fastening elements can be touched and the shield 9 then becomes free, but as care has been taken to design it with a sufficiently high resistance to piercing, it does not open in shock and continues to protect the outer fairing 3 from direct contact with the piece of rotor 17, even if it strikes it or rolls over it. This resistance essentially depends on the thickness of the shield 9 and on the breaking strength of the material which forms it.
  • the behavior and advantages of the invention can be fairly easily grasped.
  • the shield 9 does not rest directly on any surface, it can absorb energy by freely deforming over a large part of its circumference, or even all of it.
  • the stator 2 and the outer fairing 3 are sufficiently spaced to allow this deformation.
  • the total energy that the system can capture is also increased by the rupture energy of the attachment means, at the same time as this rupture allows a more extensive deformation of the shield 9 and therefore increases its energy absorption capacity.
  • FIG. 4 represents a particularly unfavorable situation, since a single large piece torn from the rotor 1 intervenes in the accident.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP95402879A 1994-12-21 1995-12-20 Berstschutzring für eine Turbomaschine Expired - Lifetime EP0718471B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9415382 1994-12-21
FR9415382A FR2728619B1 (fr) 1994-12-21 1994-12-21 Bouclier de protection d'une turbomachine

Publications (2)

Publication Number Publication Date
EP0718471A1 true EP0718471A1 (de) 1996-06-26
EP0718471B1 EP0718471B1 (de) 1999-04-14

Family

ID=9470037

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95402879A Expired - Lifetime EP0718471B1 (de) 1994-12-21 1995-12-20 Berstschutzring für eine Turbomaschine

Country Status (8)

Country Link
US (1) US5622472A (de)
EP (1) EP0718471B1 (de)
JP (1) JP2967045B2 (de)
CA (1) CA2165511A1 (de)
DE (1) DE69509053T2 (de)
FR (1) FR2728619B1 (de)
RU (1) RU2122124C1 (de)
WO (1) WO1996019641A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1849964A2 (de) * 2006-04-27 2007-10-31 Pratt & Whitney Canada Corp. Rotor Berstschutzvorrichtung mit einer Sollbruchstelle insbesondere für eine Gasturbine
CN102733868A (zh) * 2012-07-06 2012-10-17 中国航空动力机械研究所 动力机械

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH11230094A (ja) * 1997-12-16 1999-08-24 United Technol Corp <Utc> ガスタービンエンジン
US6120242A (en) * 1998-11-13 2000-09-19 General Electric Company Blade containing turbine shroud
US6375410B2 (en) 2000-02-07 2002-04-23 General Electric Company Frangible cover for turbofan engine blade removal and access
ATE358769T1 (de) * 2002-06-05 2007-04-15 Volvo Aero Corp Turbine und komponente
US6695574B1 (en) * 2002-08-21 2004-02-24 Pratt & Whitney Canada Corp. Energy absorber and deflection device
FR2869954B1 (fr) * 2004-05-05 2006-06-16 Snecma Moteurs Sa Dispositif de fixation d'un anneau bruleur dans une chambre de postcombustion d'un turboreacteur
DE102006036648A1 (de) * 2006-08-03 2008-02-07 Rolls-Royce Deutschland Ltd & Co Kg Eisschlagschutzring für das Fangehäuse einer Fluggasturbine
GB2459646B (en) * 2008-04-28 2011-03-30 Rolls Royce Plc A fan assembly
RU2461719C2 (ru) * 2010-12-14 2012-09-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Способ защиты корпуса лопаточных машин от пробиваемости при обрыве лопатки и защищенный корпус
US11280271B2 (en) 2012-10-09 2022-03-22 Raytheon Technologies Corporation Operability geared turbofan engine including compressor section variable guide vanes
RU2519677C1 (ru) * 2013-04-22 2014-06-20 Открытое акционерное общество "Авиадвигатель" Статор турбомашины
DE102013217503A1 (de) * 2013-09-03 2015-03-05 MTU Aero Engines AG Vorrichtung zur Energieabsorption, Strömungsmaschine und Verfahren zur Energieabsorption
GB2539217B (en) 2015-06-09 2020-02-12 Rolls Royce Plc Fan casing assembly
FR3058757B1 (fr) * 2016-11-14 2018-11-02 Safran Aircraft Engines Dispositif de decouplage de premiere et seconde pieces d'une turbomachine
US10487684B2 (en) 2017-03-31 2019-11-26 The Boeing Company Gas turbine engine fan blade containment systems
US10550718B2 (en) 2017-03-31 2020-02-04 The Boeing Company Gas turbine engine fan blade containment systems
DE102018113396A1 (de) * 2018-06-06 2019-12-12 Man Energy Solutions Se Berstschutzvorrichtung für eine Strömungsmaschine

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698514A (en) * 1927-05-20 1929-01-08 Westinghouse Electric & Mfg Co Restraining guard for rotors
US3093361A (en) * 1958-07-07 1963-06-11 Bristol Siddeley Engines Ltd Engines
US3602602A (en) * 1969-05-19 1971-08-31 Avco Corp Burst containment means
GB1466385A (en) * 1974-11-21 1977-03-09 Rolls Royce Containment shields for gas turbine engines
FR2375443A1 (fr) * 1976-12-23 1978-07-21 Gen Electric Dispositif de retenue des pales pour turbomachine
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
EP0358141A1 (de) * 1988-09-06 1990-03-14 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Berstschutzring aus Faserwerkstoff
WO1992007180A1 (en) * 1990-10-22 1992-04-30 Sundstrand Corporation Radial turbine containment ring system
GB2262313A (en) * 1991-12-14 1993-06-16 Rolls Royce Plc Gas turbine aerofoil blade containment structure
DE4223496A1 (de) * 1992-07-17 1994-01-20 Asea Brown Boveri Vorrichtung zum Reduzieren der kinetischen Energie von berstenden Teilen
EP0626502A1 (de) * 1993-04-07 1994-11-30 ROLLS-ROYCE plc Gehäuseanordnung für ein Gasturbinentriebwerk

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3097824A (en) * 1958-11-26 1963-07-16 Bendix Corp Turbine, wheel containment
GB2288639B (en) * 1994-04-20 1998-10-21 Rolls Royce Plc Ducted fan gas turbine engine nacelle assembly

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698514A (en) * 1927-05-20 1929-01-08 Westinghouse Electric & Mfg Co Restraining guard for rotors
US3093361A (en) * 1958-07-07 1963-06-11 Bristol Siddeley Engines Ltd Engines
US3602602A (en) * 1969-05-19 1971-08-31 Avco Corp Burst containment means
GB1466385A (en) * 1974-11-21 1977-03-09 Rolls Royce Containment shields for gas turbine engines
FR2375443A1 (fr) * 1976-12-23 1978-07-21 Gen Electric Dispositif de retenue des pales pour turbomachine
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
EP0358141A1 (de) * 1988-09-06 1990-03-14 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Berstschutzring aus Faserwerkstoff
WO1992007180A1 (en) * 1990-10-22 1992-04-30 Sundstrand Corporation Radial turbine containment ring system
GB2262313A (en) * 1991-12-14 1993-06-16 Rolls Royce Plc Gas turbine aerofoil blade containment structure
DE4223496A1 (de) * 1992-07-17 1994-01-20 Asea Brown Boveri Vorrichtung zum Reduzieren der kinetischen Energie von berstenden Teilen
EP0626502A1 (de) * 1993-04-07 1994-11-30 ROLLS-ROYCE plc Gehäuseanordnung für ein Gasturbinentriebwerk

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1849964A2 (de) * 2006-04-27 2007-10-31 Pratt & Whitney Canada Corp. Rotor Berstschutzvorrichtung mit einer Sollbruchstelle insbesondere für eine Gasturbine
EP1849964A3 (de) * 2006-04-27 2010-11-10 Pratt & Whitney Canada Corp. Rotor Berstschutzvorrichtung mit einer Sollbruchstelle insbesondere für eine Gasturbine
US8166746B2 (en) 2006-04-27 2012-05-01 Pratt & Whitney Canada Corp. Rotor containment element with frangible connections
CN102733868A (zh) * 2012-07-06 2012-10-17 中国航空动力机械研究所 动力机械

Also Published As

Publication number Publication date
CA2165511A1 (en) 1996-06-22
EP0718471B1 (de) 1999-04-14
US5622472A (en) 1997-04-22
FR2728619A1 (fr) 1996-06-28
FR2728619B1 (fr) 1997-01-24
JPH08232683A (ja) 1996-09-10
DE69509053D1 (de) 1999-05-20
JP2967045B2 (ja) 1999-10-25
WO1996019641A1 (fr) 1996-06-27
RU2122124C1 (ru) 1998-11-20
DE69509053T2 (de) 1999-10-07

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