EP2071136A2 - Bremsvorrichtung in einem Gasturbinenmotor einer Turbine für den Fall eines Wellenbruchs - Google Patents

Bremsvorrichtung in einem Gasturbinenmotor einer Turbine für den Fall eines Wellenbruchs Download PDF

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Publication number
EP2071136A2
EP2071136A2 EP08156698A EP08156698A EP2071136A2 EP 2071136 A2 EP2071136 A2 EP 2071136A2 EP 08156698 A EP08156698 A EP 08156698A EP 08156698 A EP08156698 A EP 08156698A EP 2071136 A2 EP2071136 A2 EP 2071136A2
Authority
EP
European Patent Office
Prior art keywords
braking
rotor
braking member
turbine
stator
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
EP08156698A
Other languages
English (en)
French (fr)
Other versions
EP2071136B1 (de
EP2071136A3 (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
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
Publication of EP2071136A2 publication Critical patent/EP2071136A2/de
Publication of EP2071136A3 publication Critical patent/EP2071136A3/de
Application granted granted Critical
Publication of EP2071136B1 publication Critical patent/EP2071136B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2260/00—Function
    • F05D2260/90—Braking
    • F05D2260/902—Braking using frictional mechanical forces
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2102—Glass
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/44—Resins
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/601—Fabrics
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments

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 is characterized in that it comprises a first member provided with at least one abrasive element and a second member comprising a ring-shaped element made of a material that can be eroded. by the abrasive element, the two members being secured to one of the rotor, the other of the stator and coming into contact by axial displacement of the rotor after rupture of the shaft, the abrasive element of the first member eroding the element ring shape of the second organ
  • 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 first member is integral with the stator and the second member is secured to the rotor; more particularly the rotor comprising at least one disk with a rim, the second member is integral with the rim and the first member is secured to the stator downstream of the rim.
  • the braking members By arranging the braking members outside the gas stream, the blades are preserved and the zone where this energy dissipation occurs can be located.
  • the second member is advantageously secured to the last turbine stage of the rotor and the first member of the exhaust casing.
  • the first member comprises a plurality of abrasive elements distributed around the axis of the motor.
  • the abrasive elements consist of abrasive aggregates reported, for example by sintering, on a fabric, for example glass fibers, impregnated with resin resistant to high temperature.
  • 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 which are not visible, 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 abrasive elements 110A.
  • the first braking member 110 is mounted on a stator support formed by the exhaust casing 10.
  • the support comprises an annular flange 110D with a radial flange 110B by which it is bolted to an annular rib of the casing 10 under the tongue 10A .
  • the flange 110D comprises a radial flange 110C positioned downstream of the second braking member 120.
  • the abrasive elements 110A are integral with the flange 110C.
  • the second braking member 120 is secured to the rim 63'B. More specifically for this example, the member 120 is secured to a flange 63'B1 downstream at the rim. It comprises a ring-shaped element with a radial surface 120A opposite the abrasive element 110A
  • This second braking member 120 may be attached to the flange 63'B1 of the rim 63'B, but it may 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 turbine disk rotates about its axis and the braking member 120 moves in rotation around the motor axis, parallel to the front face of the abrasive element 110A of the braking member without the touch preferably.
  • the combination of the elements 110A and 120A must allow, when the disk moves axially downstream due to the rupture of the shaft 8, the abrasive elements 110A to rub against the surface 120A.
  • the rotation associated with the pressure leads to wear of the braking member 120 by the abrasive elements 110A in the manner of a conventional abrasive tool.
  • the energy is supplied by the rotating rotor and is thus dissipated.
  • the structure and materials of the abrasive elements 110A; aggregates, substrate are determined jointly and in relation to the material of the braking member 120.
  • the abrasive material may consist of abrasive aggregates such as those known in the industry. It may be grains of ceramic material or zirconium. These are fixed, for example by sintering on a substrate such as a glass fiber cloth impregnated with resin resistant to high temperature.
  • An epoxy resin of the Pyrotek type F 51 ® and manufactured by Pyrotek is suitable for this application and withstands a temperature of up to 700 ° C.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Braking Arrangements (AREA)
EP08156698.6A 2007-05-25 2008-05-21 Gasturbinenmotor mit einer Bremsvorrichtung für den Fall eines Wellenbruchs Active EP2071136B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0703758A FR2916482B1 (fr) 2007-05-25 2007-05-25 Systeme de freinage en cas de rupture d'arbre de turbine dans un moteur a turbine a gaz

Publications (3)

Publication Number Publication Date
EP2071136A2 true EP2071136A2 (de) 2009-06-17
EP2071136A3 EP2071136A3 (de) 2010-03-10
EP2071136B1 EP2071136B1 (de) 2018-07-25

Family

ID=39099813

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08156698.6A Active EP2071136B1 (de) 2007-05-25 2008-05-21 Gasturbinenmotor mit einer Bremsvorrichtung für den Fall eines Wellenbruchs

Country Status (3)

Country Link
US (1) US8161727B2 (de)
EP (1) EP2071136B1 (de)
FR (1) FR2916482B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9062560B2 (en) 2012-03-13 2015-06-23 United Technologies Corporation Gas turbine engine variable stator vane assembly

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2916483B1 (fr) * 2007-05-25 2013-03-01 Snecma Systeme de dissipation d'energie en cas de rupture d'arbre de turbine dans un moteur a turbine a gaz
DE102011086775A1 (de) * 2011-07-20 2013-01-24 Mtu Aero Engines Gmbh Verfahren zur Herstellung eines Einlaufbelags, Einlaufsystem, Strömungsmaschine sowie Leitschaufel
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
US10815824B2 (en) * 2017-04-04 2020-10-27 General Electric Method and system for rotor overspeed protection
FR3113922B1 (fr) 2020-09-08 2023-03-31 Safran Aircraft Engines Frein de turbine
EP4006316A1 (de) * 2020-11-27 2022-06-01 Rolls-Royce Deutschland Ltd & Co KG Wellenbruchsicherungssystem

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6494046B1 (en) 1998-12-14 2002-12-17 Rolls-Royce Deutschland Ltd & Co Kg Method and apparatus for recognition of a shaft rupture in a turbo-engine
EP1640564A1 (de) 2004-09-28 2006-03-29 Snecma Überdrehzahlsicherung einer Turbine

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US3490748A (en) * 1968-05-14 1970-01-20 Gen Motors Corp Fragmentation brake for turbines
FR2050550A5 (en) * 1969-06-17 1971-04-02 Commissariat Energie Atomique Governor for turbine rotors
US4498291A (en) * 1982-10-06 1985-02-12 Rolls-Royce Limited Turbine overspeed limiter for turbomachines
JPS6213479A (ja) * 1985-07-10 1987-01-22 Sumitomo Electric Ind Ltd 摩擦材料
GB2199900B (en) * 1987-01-15 1991-06-19 Rolls Royce Plc A turbopropeller or turbofan gas turbine engine
FR2640684B1 (fr) * 1988-12-15 1994-01-28 Snecma Turbomachine comportant un dispositif de freinage entre rotor de turbine et carter d'echappement
FR2773586B1 (fr) * 1998-01-09 2000-02-11 Snecma Turbomachine a freinage mutuel d'arbres concentriques
US6312215B1 (en) * 2000-02-15 2001-11-06 United Technologies Corporation Turbine engine windmilling brake
DE10218459B3 (de) * 2002-04-25 2004-01-15 Mtu Aero Engines Gmbh Verdichter in mehrstufiger Axialbauart
US7225607B2 (en) * 2004-08-27 2007-06-05 Pratt & Whitney Canada Corp. Gas turbine braking apparatus and method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6494046B1 (en) 1998-12-14 2002-12-17 Rolls-Royce Deutschland Ltd & Co Kg Method and apparatus for recognition of a shaft rupture in a turbo-engine
EP1640564A1 (de) 2004-09-28 2006-03-29 Snecma Überdrehzahlsicherung einer Turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9062560B2 (en) 2012-03-13 2015-06-23 United Technologies Corporation Gas turbine engine variable stator vane assembly

Also Published As

Publication number Publication date
FR2916482A1 (fr) 2008-11-28
US8161727B2 (en) 2012-04-24
US20090126336A1 (en) 2009-05-21
EP2071136B1 (de) 2018-07-25
FR2916482B1 (fr) 2009-09-04
EP2071136A3 (de) 2010-03-10

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