EP1921274A1 - Begrenzungsvorrichtung gegen Überdrehzahl für die Turbine einer Turbomaschine und entsprechende Turbomaschine - Google Patents

Begrenzungsvorrichtung gegen Überdrehzahl für die Turbine einer Turbomaschine und entsprechende Turbomaschine Download PDF

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Publication number
EP1921274A1
EP1921274A1 EP07291199A EP07291199A EP1921274A1 EP 1921274 A1 EP1921274 A1 EP 1921274A1 EP 07291199 A EP07291199 A EP 07291199A EP 07291199 A EP07291199 A EP 07291199A EP 1921274 A1 EP1921274 A1 EP 1921274A1
Authority
EP
European Patent Office
Prior art keywords
turbine
cylinder
pin
overspeed
turbomachine
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
EP07291199A
Other languages
English (en)
French (fr)
Other versions
EP1921274B1 (de
Inventor
Jacques René Bart
Didier René André Escure
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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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1921274A1 publication Critical patent/EP1921274A1/de
Application granted granted Critical
Publication of EP1921274B1 publication Critical patent/EP1921274B1/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
    • F01D21/02—Shutting-down responsive to overspeed
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0292—Stop safety or alarm devices, e.g. stop-and-go control; Disposition of check-valves
    • 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
    • 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
    • F05D2270/04—Purpose of the control system to control acceleration (u)
    • F05D2270/042—Purpose of the control system to control acceleration (u) by keeping it below damagingly high values
    • 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
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed
    • 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
    • F05D2270/60—Control system actuates means
    • F05D2270/62—Electrical actuators

Definitions

  • the present invention relates to a device for limiting overspeed in a turbomachine such as an aircraft turbojet, to counteract a rupture of the turbine shaft, a rare phenomenon but whose consequences can be disastrous.
  • the rotor of the turbine is found uncoupled from the fan which limited its speed of rotation but the blades of the turbine continue to be rotated by the gas leaving the combustion chamber of the turbine engine .
  • the turbine then passes "overspeed", which subjects the rotor to excessive centrifugal forces likely to cause it to burst, with risks of perforation of the outer casing of the turbine and also of the cabin of the aircraft equipped with this turbomachine.
  • the overspeed limitation is therefore a mandatory constraint to be respected in the turbomachines.
  • the known overspeed limiting devices generally exploit the downstream displacement of the rotor of the turbine which results from the rupture of the turbine shaft and the pressure of the gases on the vanes of the rotor.
  • the known devices have the disadvantage of being relatively slow, which affects their efficiency. This is particularly disadvantageous in the case of small engines, whose lower inertia of the turbine rotor induces a risk of starting in faster overspeed.
  • the devices requiring a frank contact between parts may prove to be inoperative in case of rebound of the rotor on a fixed part or in case of orbiting of this rotor.
  • Braking devices based on friction between parts have an efficiency that is difficult to predict because they involve multiple uncertain parameters such as the temperature or the force exerted between the parts.
  • the invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the disadvantages of the known technique.
  • the invention also aims to respond more satisfactorily to the reliability and speed requirements of a device for limiting the overspeed of a turbine in a turbomachine.
  • a device for limiting turbine overspeed in a turbine engine in the event of rupture of the turbine shaft comprising shearing means for moving blades of at least one stage of the turbine, characterized in that these shearing means comprise means for projecting a pin on the path of the blades, these projection means being mounted on a casing of the turbine or turbomachine and controlled by means of detecting an overspeed of rotation of the blade; turbine or detection of a rupture of the shaft of this turbine.
  • the essential advantage of this device is that it is not dependent on the recoil of the rotor and can be triggered without waiting for this recoil to occur, which guarantees a greater speed of reaction, the speed of the device does not depend more than the response time of the projection means.
  • the operation of this device will not be penalized, unlike some previous devices, in case of rebound of the turbine or rotor orbiting.
  • the projection means comprise an explosive material capsule housed in a cylinder capable of guiding the pin during the explosion of the capsule.
  • pellets of a material capable of generating a gas under the effect of a detonation such as, for example, sodium acid, are placed near the explosive material capsule in this cylinder.
  • the cylinder is mounted outside the housing in alignment with an orifice of this casing opening on the path of the blades, and comprises an open end by which it is fixed. on the housing, its other end being closed and containing the capsule of explosive material.
  • the pin extends completely inside the cylinder when it is in rest condition, before detecting an overspeed departure or before detecting a rupture of the low pressure turbine shaft, and it comprises a body cylindrical whose one end is slidably guided in the end of the cylinder fixed on the housing, the other end of the cylindrical body having a head whose diameter is greater than that of the cylindrical body and the diameter of the open end of the cylinder; cylinder, so as to form a retaining member of the pin in the cylinder.
  • the pin in rest condition, does not disturb the flow of gas in the turbine and therefore does not affect the performance of the engine.
  • the casing orifice is closed by a cover of material resistant to the operating temperatures of the turbomachine and capable of being broken by the pin in the event of detection of a departure in overspeed, the pin preferably comprising a tip suitable for pierce this operculum, formed at the end of the cylindrical body opposite the head.
  • the pin is locked inside the cylinder in the rest position, and only the explosion and the release of gas, following an overspeed departure detection or rupture of the low pressure turbine shaft. , can, by the violent thrust exerted on the pin, bring this one to pierce the operculum to leave the cylinder.
  • this seal prevents gases passing through the turbine from entering the cylinder containing the pin and the explosive capsule.
  • the cylinder advantageously comprises a lateral fastening flange on the housing and electrical connection means of the explosive charge means for detecting an overspeed of rotation of the turbine or a rupture of the shaft of this turbine.
  • the present invention also relates to a turbomachine, such as an aircraft turbojet, equipped with an overspeed limitation device of the type described above.
  • FIG 1 shows a low pressure turbine rotor comprising four discs 12, 14, 16, 18 assembled axially to each other by annular flanges 20 and carrying blades 22 which are mounted by means of blade roots at their radially inner end in grooves in the outer periphery of the discs 12, 14, 16, 18.
  • the rotor is connected to the turbine shaft 24 via a fixed drive cone 26 by means of an annular flange 28 between the annular flanges 20 of the discs 14 and 16.
  • a device 40 for limiting the speed of the turbine according to the invention is mounted on the outer surface of an exhaust casing 34 to which is connected the turbine casing 32.
  • the device 40 thus positioned is associated on the top floor of the turbine, it is possible to use it for any floor.
  • the turbine is furthermore equipped with means for detecting an overspeed of rotation of the rotor or a rupture of the shaft 24 of this turbine, shown schematically at 36.
  • the overspeed limiting device 40 comprises a pin 42 made of very hard metal housed in a cylinder 44, which has at its end applied to the casing 34 a lateral rim 46 fixed by one or more screws 48 to a plate 50 formed on the outer surface of the housing 34, the cylinder 44 being open at its end fixed on the housing and closed at its other end.
  • the pin 42 comprises a cylindrical body 52 respectively comprising, at its two ends, a tip 56 and a head 54, the latter having a diameter greater than that of the cylindrical body 52, so as to form a retaining member of the pin in the cylinder.
  • the head 54 is in the vicinity of the closed end of the cylinder 44 while the tip 56 faces its open end.
  • An explosive charge shown schematically at 38 and optionally sodium acid pellets or other gas generating material are placed inside the cylinder, in the free space 58 between the head 54 of the pin and the closed end of the cylinder.
  • the cylinder 44 is mounted in alignment with an orifice 60 of the housing 34 which opens on the path of the blades 22 of the last stage of the rotor of the turbine.
  • This orifice 60 has a diameter slightly greater than that of the cylindrical body 52, and smaller than that of the head 54.
  • the pin 42 In the rest position shown in Figure 2, the pin 42 is housed entirely in the cylinder 44 and the orifice 60 is obstructed by a seal of a material, such as a resin or putty, resistant to operating temperatures the turbomachine and adapted to be perforated by the tip 56 of the pin 42 under the effect of a strong thrust.
  • a seal of a material such as a resin or putty
  • Electrical connection means 64 are mounted on a lateral support 62 connected to the cylinder 44 and to the lateral attachment flange 46, to enable the control of the explosive charge by the means 36 for detecting an overspeed of rotation of the turbine or of a rupture of the shaft 24 of this turbine.
  • the pin Under the effect of the strong thrust exerted by the gas on its head 54, the pin then pierces through its point 56 the seal obstructing the orifice 60, and is projected inwardly of the turbine through the orifice 60 , until the head 54 abuts against the edge of the orifice 60, as shown in FIG.
  • Part of the pin 42 is then in the path of the aforementioned moving blades 22, so that these vanes are broken against it.
  • the response time of the device according to the invention is very short: about 40 milliseconds (10 ms for the detection of the overspeed and 30 ms for the explosion of the load and the projection of the pin), while the response time devices known from the prior art is greater than 100 ms.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
EP07291199A 2006-10-30 2007-10-02 Begrenzungsvorrichtung gegen Überdrehzahl für die Turbine einer Turbomaschine und entsprechende Turbomaschine Active EP1921274B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0609502A FR2907840B1 (fr) 2006-10-30 2006-10-30 Dispositif de limitation de survitesse de turbine dans une turbomachine

Publications (2)

Publication Number Publication Date
EP1921274A1 true EP1921274A1 (de) 2008-05-14
EP1921274B1 EP1921274B1 (de) 2009-09-02

Family

ID=37896003

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07291199A Active EP1921274B1 (de) 2006-10-30 2007-10-02 Begrenzungsvorrichtung gegen Überdrehzahl für die Turbine einer Turbomaschine und entsprechende Turbomaschine

Country Status (7)

Country Link
US (1) US8057160B2 (de)
EP (1) EP1921274B1 (de)
JP (1) JP5114797B2 (de)
CA (1) CA2608267C (de)
DE (1) DE602007002248D1 (de)
FR (1) FR2907840B1 (de)
RU (1) RU2451188C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2048330A3 (de) * 2007-10-09 2012-03-14 United Technologies Corporation Systeme und Verfahren mit mehreren Drehmomentpfaden für Gasturbinenmotoren

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2469447B (en) * 2009-04-15 2011-03-09 Rolls Royce Plc Gas turbine engine casing assembly
US9771167B2 (en) * 2013-01-16 2017-09-26 Airbus Helicopters Monitor system for monitoring the starting of a rotary wing aircraft, an aircraft, and a method using the system
JP6266775B2 (ja) 2013-07-26 2018-01-24 エムアールエイ・システムズ・エルエルシー 航空機エンジンパイロン
US10215049B2 (en) * 2015-07-17 2019-02-26 Hamilton Sundstrand Corporation Air cycle machine lockout tool
FR3049646B1 (fr) 2016-03-31 2019-04-12 Safran Aircraft Engines Dispositif de limitation de survitesse d'un rotor de turbine de turbomachine
US10801361B2 (en) 2016-09-09 2020-10-13 General Electric Company System and method for HPT disk over speed prevention
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

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH369938A (de) * 1959-07-15 1963-06-15 Saurer Ag Adolph Sicherheitsvorrichtung zur Drehzahlbegrenzung von Strömungsmaschinen
FR1486102A (fr) * 1966-07-07 1967-06-23 Lucas Industries Ltd Dispositif de sécurité pour turbine à gaz
EP1640564A1 (de) * 2004-09-28 2006-03-29 Snecma Überdrehzahlsicherung einer Turbine

Family Cites Families (6)

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Publication number Priority date Publication date Assignee Title
US3490748A (en) * 1968-05-14 1970-01-20 Gen Motors Corp Fragmentation brake for turbines
US4505104A (en) * 1982-10-06 1985-03-19 Rolls-Royce Limited Turbine overspeed limiter for turbomachines
JPS59131706A (ja) * 1982-10-06 1984-07-28 ロ−ルス−ロイス、パブリック、リミテッド、カンパニ− タ−ボ機械の過速度防止機構
SU1550186A1 (ru) * 1988-05-10 1990-03-15 Харьковское научно-исследовательское и проектно-конструкторское отделение Всесоюзного государственного научно-исследовательского, проектно-конструкторского и изыскательского института "Атомэнергопроект" Система защиты турбины от недопустимого повышени частоты вращени ротора
JPH04287803A (ja) * 1991-03-19 1992-10-13 Hitachi Ltd タービン過速度防止装置
RU2086779C1 (ru) * 1993-10-21 1997-08-10 Омское моторостроительное конструкторское бюро Устройство защиты газотурбинного двигателя

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH369938A (de) * 1959-07-15 1963-06-15 Saurer Ag Adolph Sicherheitsvorrichtung zur Drehzahlbegrenzung von Strömungsmaschinen
FR1486102A (fr) * 1966-07-07 1967-06-23 Lucas Industries Ltd Dispositif de sécurité pour turbine à gaz
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
EP2048330A3 (de) * 2007-10-09 2012-03-14 United Technologies Corporation Systeme und Verfahren mit mehreren Drehmomentpfaden für Gasturbinenmotoren

Also Published As

Publication number Publication date
JP2008111436A (ja) 2008-05-15
RU2451188C2 (ru) 2012-05-20
FR2907840B1 (fr) 2008-12-26
CA2608267C (fr) 2014-08-05
DE602007002248D1 (de) 2009-10-15
FR2907840A1 (fr) 2008-05-02
EP1921274B1 (de) 2009-09-02
US8057160B2 (en) 2011-11-15
JP5114797B2 (ja) 2013-01-09
US20080101917A1 (en) 2008-05-01
CA2608267A1 (fr) 2008-04-30
RU2007139920A (ru) 2009-05-10

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