EP1995414B1 - Bremsvorrichtung für eine Turbine in einem Gasturbinenantrieb für den Fall eines Wellenbruchs - Google Patents

Bremsvorrichtung für eine Turbine in einem Gasturbinenantrieb für den Fall eines Wellenbruchs Download PDF

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Publication number
EP1995414B1
EP1995414B1 EP08156695A EP08156695A EP1995414B1 EP 1995414 B1 EP1995414 B1 EP 1995414B1 EP 08156695 A EP08156695 A EP 08156695A EP 08156695 A EP08156695 A EP 08156695A EP 1995414 B1 EP1995414 B1 EP 1995414B1
Authority
EP
European Patent Office
Prior art keywords
braking member
braking
turbine
rim
rotor
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.)
Active
Application number
EP08156695A
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English (en)
French (fr)
Other versions
EP1995414A1 (de
Inventor
Jacques René Bart
Didier René André Escure
Claude Marcel Mons
Stéphane Rousselin
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
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1995414A1 publication Critical patent/EP1995414A1/de
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Publication of EP1995414B1 publication Critical patent/EP1995414B1/de
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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
    • F01D21/006—Arrangements of brakes
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed

Definitions

  • the present invention relates to the field of gas turbine engines, in particular multiflux turbojet engines, and relates to a system which makes it possible, in the event of the breakage of a shaft of the machine, to stop it as quickly as possible. .
  • a turbojet turbojet turbofan In a turbojet turbojet turbofan, the latter is driven by the low pressure turbine.
  • the shaft connecting the fan rotor to that of the turbine breaks, the resistance torque on the turbine is abruptly canceled while the flow of engine gas continues to transmit energy to the rotor. This results in a rapid increase in the rotational speed of the rotor which is likely to reach its limit of resistance and burst with the resulting catastrophic consequences.
  • the present invention aims at a simple, effective and inexpensive solution for reducing the speed of rotation, in a gas turbine engine, of a turbine comprising a rotor driving a shaft and movable in rotation inside a stator, in case of rupture of said shaft.
  • the braking device in a gas turbine engine a turbine comprising a rotor, having at least one disc with a rim, driving a shaft and mobile in rotation with respect to a stator, is characterized by the fact that it comprises a first braking member, integral with said rim and provided with at least one cutting element, and a second braking member, integral with the stator downstream of the rim, comprising a shaped element; ring made of a material capable of being cut by the cutting element of the first braking member, the two braking members coming into contact by axial displacement of the rotor after rupture of the shaft, the cutting element of the first member braking system cutting off the ring-shaped element of the second braking member.
  • the solution of the invention therefore consists in dissipating the energy of the rotor between two members which are arranged specifically for braking. These means make it possible to increase the contact surface according to the objective aimed at and to ensure a high coefficient of friction.
  • the advantage is also to reduce the maximum speed at which the rotor must resist without bursting.
  • This diet is the one that is likely to be reached when the tree breaks.
  • the blades are preserved and the zone where this energy dissipation occurs can be located.
  • the first member is advantageously secured to the last turbine stage of the rotor and the second member of the exhaust casing.
  • the first member comprises a plurality of cutting elements distributed around the axis of the motor, and the elements are made by machining with the rim.
  • the cutting elements are knife-shaped arranged to dig the ring-shaped element with removal of material.
  • the ring-shaped element is attached to a flange mounted on the stator.
  • the invention also relates to a dual-body gas turbine engine with a low-pressure turbine section whose section is equipped with such a braking device.
  • the turbine section 1 comprises a high-pressure turbine upstream and not visible in the figure, which receives the hot gases from the combustion chamber.
  • the gases after having passed through the vane of the high-pressure turbine wheel are directed, through a fixed distributor wheel 3, onto the low-pressure turbine section 5.
  • This section 5 is composed of a rotor 6 formed here in a drum the assembly of several disks 61, 62, 63 bladed, three in this example.
  • the blades, comprising a blade and a foot, are mounted, generally individually, at the periphery of the discs in housings formed on the rim.
  • Stationary distributor wheels 7 are interposed between the turbine stages, each to properly orient the gas flow relative to the downstream moving blade.
  • This assembly forms the low pressure turbine section 5.
  • the rotor 6 of the low-pressure turbine is mounted on a shaft 8, concentric with the high-pressure shaft 9, which extends axially towards the front of the engine where it is integral with the fan rotor.
  • the rotating assembly is supported by appropriate bearings located in the front and rear parts of the engine.
  • the shaft 8, supported by a bearing 81 is seen in the structural casing, designated exhaust casing 10.
  • the exhaust casing is provided with fastening means for mounting on an aircraft.
  • the turbine rotor is racing and its speed reaches the maximum permitted speed before bursting, a braking device is incorporated in the turbine section.
  • This device 100 is represented on the figure 2 which is a partial perspective view of the turbine disk 63 'and the exhaust casing.
  • the disk 63 ' corresponds to the disk 63 of the figure 1 modified according to the invention.
  • the disc 63 ' has a conventional shape or the like, according to this example with a hub 63'A, a rim 63'B at its periphery and a thin radial sail 63'C between the hub and the rim.
  • the rim 63'B is provided with means for attaching the vanes which extend in a radial direction in the annular channel traversed by the engine gas.
  • the vanes and their attachment means are not part of the invention and have not been represented in their entirety in the figure a single silhouette in the section plane is visible.
  • the exhaust casing 10 is shown in its part which is vis-à-vis the disc 63 '.
  • annular platform 10A forming the inner wall of the gas channel in the extension of the platforms at the periphery of the disk 63 'of the last turbine stage.
  • Rectifier vanes 10B extend radially in the annular channel.
  • the platform 10A extends axially upstream towards the disc 63 'by an annular sealing tongue 10A'.
  • the braking device 100 of the invention comprises a first braking member 110 which consists of cutting elements 110A.
  • the first braking member 110 is secured to the rim 63'B. More precisely for this example, the member 110 is secured to a radial flange 63'B1 downstream at the rim.
  • the elements 110A are, according to the example shown, teeth inclined in the direction of rotation of the disc. Their distal end is bevel-shaped and is cut to form a cutting means, such as a chisel.
  • the cutting edge is here radial or substantially radial.
  • This first braking member (110) can be attached to the flange 63'B1 of the rim 63'B but it can also be obtained by machining together with the rim from a cast blank. In this case it is made of the same metal as the rim. Its hardness corresponds to it.
  • the second braking member 120 is mounted on the stator formed by the exhaust casing 10. It comprises an annular pool 120B bolted to an annular rib of the housing 10 under the tongue 10A '.
  • the flange 120B comprises a radial flange 120B1 positioned downstream of the first braking member 110.
  • a ring-shaped element 120A is integral with the flange 120B1. This ring element 120A is of rectangular section with a radial face perpendicular to the axis of rotation, maintained at a short distance downstream from the edges of the cutting elements (110A) forming the first braking member (110).
  • the material constituting the ring-shaped element 120A is of lower hardness than that of the cutting elements 110A. It may consist of a piece with the flange 120B but may also have been attached to the flange.
  • the turbine disk rotates about its axis and the cutting elements 110A move in rotation about the motor axis, parallel to the front face of the ring member 120A without touching it preferably.
  • the combination of the elements 110A and 120A should allow, when the disc moves axially downstream due to the breakage of the shaft 8, the cutting elements 110A to rub against the ring member 120A.
  • the rotation associated with the pressure leads to the cutting of the element 120A by the cutting elements 110A in the manner of a conventional cutting tool.
  • the energy is supplied by the rotating rotor and is thus dissipated.
  • the geometry of the cutting elements 110A; angle of the bevel, length of the cutting edge, and the material constituting them are determined jointly and in relation to the material of the annular element 120A.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Braking Arrangements (AREA)

Claims (8)

  1. Bremsvorrichtung in einem Gasturbinentriebwerk, von einer Turbine, die ein Laufrad umfasst, das mindestens eine Scheibe (63') mit einem Radkranz (63'B) aufweist, eine Welle antreibt und im Verhältnis zu einem Leitrad drehmäßig bewegbar ist, wobei die Vorrichtung für den Fall eines Wellenbruchs gedacht ist, dadurch gekennzeichnet, dass sie ein erstes Bremsorgan (110), das mit dem Radkranz fest verbunden ist und mit mindestens einem Schneidelement (110A) versehen ist, und ein zweites Bremsorgan (120), das mit dem Leitrad unterhalb des Radkranzes (63'B) fest verbunden ist, das ein ringförmiges Element (120A) umfasst, das aus einem Material ausgebildet ist, das von dem Schneidelement (110A) zerschnitten werden kann, umfasst, wobei die beiden Bremsorgane durch Axialverschiebung des Laufrads nach einem Wellenbruch in Kontakt kommen, wobei das Schneidelement (110A) des ersten Bremsorgans (110) das ringförmige Element (120A) des zweiten Bremsorgans (120) zerschneidet.
  2. Vorrichtung nach Anspruch 1, wobei der Motor ein Abgasgehäuse (10) umfasst, wobei das erstes Bremsorgan (110) mit der letzten Turbinenstufe des Laufrads und das zweite Bremsorgan (120) mit dem Abgasgehäuse (10) festverbunden ist.
  3. Vorrichtung nach Anspruch 1 oder 2, wobei das erste Bremsorgan (110) eine Vielzahl von Schneidelementen (110A) umfasst, die um die Achse des Motors herum verteilt sind.
  4. Vorrichtung nach Anspruch 1, wobei die Schneidelemente (110A) des ersten Bremsorgans (110) durch Formgebung mit dem Radkranz (63'B) ausgebildet werden.
  5. Vorrichtung nach Anspruch 1, wobei die Schneidelemente (110A) des ersten Bremsorgans (110) durch Formgebung auf einem Element ausgebildet werden, das an den Radkranz (63'B) angesetzt und daran befestigt ist.
  6. Vorrichtung nach Anspruch 4 oder 5, wobei die Schneidelemente (110A) in Form von Messern vorliegen, die angeordnet sind, um das ringförmige Element (120A) des zweiten Bremsorgans mit Materialabhebung auszuhöhlen.
  7. Vorrichtung nach einem der Ansprüche 1 und 2, wobei das ringförmige Element (120A) des zweiten Bremsorgans auf einem Flansch (120B) angesetzt ist, der an dem Leitrad angebracht ist.
  8. Doppelwellen-Gasturbinentriebwerk mit einem Niederdruck-Turbinenabschnitt, wobei der Abschnitt mit einer Bremsvorrichtung nach einem der vorhergehenden Ansprüche ausgestattet ist.
EP08156695A 2007-05-25 2008-05-21 Bremsvorrichtung für eine Turbine in einem Gasturbinenantrieb für den Fall eines Wellenbruchs Active EP1995414B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0703759A FR2916483B1 (fr) 2007-05-25 2007-05-25 Systeme de dissipation d'energie en cas de rupture d'arbre de turbine dans un moteur a turbine a gaz

Publications (2)

Publication Number Publication Date
EP1995414A1 EP1995414A1 (de) 2008-11-26
EP1995414B1 true EP1995414B1 (de) 2010-07-07

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP08156695A Active EP1995414B1 (de) 2007-05-25 2008-05-21 Bremsvorrichtung für eine Turbine in einem Gasturbinenantrieb für den Fall eines Wellenbruchs

Country Status (6)

Country Link
US (1) US8127525B2 (de)
EP (1) EP1995414B1 (de)
CA (1) CA2631620C (de)
DE (1) DE602008001684D1 (de)
FR (1) FR2916483B1 (de)
RU (1) RU2469194C2 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011086775A1 (de) 2011-07-20 2013-01-24 Mtu Aero Engines Gmbh Verfahren zur Herstellung eines Einlaufbelags, Einlaufsystem, Strömungsmaschine sowie Leitschaufel
FR2987085B1 (fr) * 2012-02-20 2014-03-21 Snecma Procede de securisation du fonctionnement d'une turbomachine
FR3026774B1 (fr) * 2014-10-07 2020-07-17 Safran Aircraft Engines Turbomachine comportant un dispositif de freinage du rotor de soufflante.
US10190440B2 (en) 2015-06-10 2019-01-29 Rolls-Royce North American Technologies, Inc. Emergency shut-down detection system for a gas turbine
FR3049646B1 (fr) * 2016-03-31 2019-04-12 Safran Aircraft Engines Dispositif de limitation de survitesse d'un rotor de turbine de turbomachine
RU2647944C1 (ru) * 2017-03-07 2018-03-21 Акционерное общество "ОДК-Авиадвигатель" Газотурбинный двигатель с биротативным вентилятором
FR3079550B1 (fr) 2018-03-27 2020-10-23 Safran Aircraft Engines Arbre de turbine d'une turbomachine et procede de protection contre une survitesse dudit arbre
CN108742350B (zh) * 2018-06-28 2021-04-06 芜湖泰领信息科技有限公司 清洁刷头自动更换方法及智能扫地机
GB201820823D0 (en) * 2018-12-20 2019-02-06 Rolls Royce Plc Gas turbine engine
FR3107318B1 (fr) 2020-02-17 2022-01-14 Safran Aircraft Engines Turbomachine d’aéronef à double flux équipée d’un dispositif d’arrêt en survitesse du rotor

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3075741A (en) * 1957-06-04 1963-01-29 Fairchild Stratos Corp Overspeed safety device for turbine wheels
US2966333A (en) * 1957-06-27 1960-12-27 Fairchild Engine & Airplane Overspeed safety device for turbine wheels
US4498291A (en) * 1982-10-06 1985-02-12 Rolls-Royce Limited Turbine overspeed limiter for turbomachines
US4505104A (en) * 1982-10-06 1985-03-19 Rolls-Royce Limited Turbine overspeed limiter for turbomachines
FR2640684B1 (fr) * 1988-12-15 1994-01-28 Snecma Turbomachine comportant un dispositif de freinage entre rotor de turbine et carter d'echappement
RU9012U1 (ru) * 1997-11-05 1999-01-16 Комсомольский-на-Амуре государственный технический университет Турбина
DE19857552A1 (de) 1998-12-14 2000-06-15 Rolls Royce Deutschland Verfahren zum Erkennen eines Wellenbruches in einer Strömungskraftmaschine
US7225607B2 (en) * 2004-08-27 2007-06-05 Pratt & Whitney Canada Corp. Gas turbine braking apparatus and method
FR2875842B1 (fr) * 2004-09-28 2010-09-24 Snecma Moteurs Dispositif de limitation de survitesse de turbine dans une turbomachine
FR2916482B1 (fr) * 2007-05-25 2009-09-04 Snecma Sa Systeme de freinage en cas de rupture d'arbre de turbine dans un moteur a turbine a gaz

Also Published As

Publication number Publication date
CA2631620A1 (fr) 2008-11-25
FR2916483B1 (fr) 2013-03-01
EP1995414A1 (de) 2008-11-26
US20080289315A1 (en) 2008-11-27
FR2916483A1 (fr) 2008-11-28
CA2631620C (fr) 2015-02-24
DE602008001684D1 (de) 2010-08-19
RU2008120784A (ru) 2009-11-27
US8127525B2 (en) 2012-03-06
RU2469194C2 (ru) 2012-12-10

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